СИСТЕМА (ВАРИАНТЫ) И СПОСОБ (ВАРИАНТЫ) ДЛЯ ПОВЫШЕНИЯ ВЫХОДНОЙ МОЩНОСТИ ТУРБИНЫ, А ТАКЖЕ СИСТЕМА ЗАЩИТЫ ВХОДНОГО КАНАЛА ГАЗОВОЙ ТУРБИНЫ ОТ КОРРОЗИИ

FIELD: engines and pumps. ^ SUBSTANCE: method and system to increase gas turbine engine output. Proposed system comprises rinsing unit to inject sprayed water into gas turbine engine to remove contaminating material from at least one blade and at least one water injection unit to inject sprayed water into gas turbine intake airflow under control of computerised simulator of dynamic fluid medium transfer intended for increasing mass of aforesaid air flow. Note here gas turbine engine output can notably increase. ^ EFFECT: possibility to use under multiple operating conditions. ^ 88 cl, 14 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 369 762 (13) C2 (51) МПК F02C 9/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21), (22) Заявка: 2007133830/06, 10.09.2007 (24) Дата начала отсчета срока действия патента: 10.09.2007 (72) Автор(ы): ВАГНЕР Томас (US), СЕЗАР Карлос (VE) R U (73) Патентообладатель(и): ГЭЗ ТЕРБАЙН ИФФИШЕНСИ СВИДЕН АБ (SE) (30) Конвенционный приоритет: 11.09.2006 US 11/519,575 31.08.2007 US 11/897,879 (43) Дата публикации заявки: 20.03.2009 2 3 6 9 7 6 2 2 3 6 9 7 6 2 R U (56) Список документов, цитированных в отчете о поиске: US 3976661 А, 24.08.1976. US 5868860 А, 02.09.1999. US 6718771 В1, 13.04.2004. US 6644935 А1, 03.10.2002. RU 2000458 С, 07.09.1993. WO 05/120953 А1, 22.12.2005. WO 05/077554 A1, 25.08.2005. WO 05/121509 A1, 25.12.2005. SU 1767205 A, 07.10.1992. SU 1755965 A1, 23.08.1992. SU 319745 A, 02.11.1971. C 2 C 2 (45) Опубликовано: 10.10.2009 Бюл. № 28 Адрес для переписки: 129090, Москва, ул.Б.Спасская, 25, стр.3, ООО "Юридическая фирма Городисский и Партнеры", пат.пов. А.В.Мицу, рег.№ 364 (54) СИСТЕМА (ВАРИАНТЫ) И СПОСОБ (ВАРИАНТЫ) ДЛЯ ПОВЫШЕНИЯ ВЫХОДНОЙ МОЩНОСТИ ТУРБИНЫ, А ТАКЖЕ СИСТЕМА ЗАЩИТЫ ВХОДНОГО КАНАЛА ГАЗОВОЙ ТУРБИНЫ ОТ КОРРОЗИИ (57) Реферат: Способ и система для повышения мощности на валу газотурбинных двигателей, которые можно использовать во многих режимах ...

СИСТЕМА И СПОСОБ ДЛЯ СНИЖЕНИЯ СОДЕРЖАНИЯ ВРЕДНЫХ ВЕЩЕСТВ В ВЫХЛОПНЫХ ГАЗАХ ДВИГАТЕЛЯ

... 1. Система (10) для снижения содержания вредных веществ в выхлопных газах двигателя, содержащая: ! - топливный элемент (12), выполненный с возможностью выработки электрической энергии и выхлопного газа, содержащего водяной пар, во время работы топливного элемента, ! - топливный бак (38) для хранения топлива, которое во время работы подается в двигатель (44), ! - конденсационное устройство (32), соединенное с выхлопным отверстием (16) топливного элемента (12) для подачи выхлопного газа топливного элемента, содержащего водяной пар, в конденсационное устройство (32), при этом конденсационное устройство (32) выполнено с возможностью перевода водяного пара, содержащегося в выхлопном газе топливного элемента, в жидкое агрегатное состояние путем конденсации, и с возможностью ввода в топливо воды, образующейся в процессе конденсации, для получения водно-топливной смеси, и ! - трубопровод (96) для водно-топливной смеси, соединенный с двигателем (44) для подачи водно-топливной смеси в двигатель ( ...

Gas-Dampfturbinenanlage

GAS TURBINE ENGINE

... 1,273,766. Gas turbine plant. STRUTHERS SCIENTIFIC & INTERNATIONAL CORP. July 2, 1970 [July 2, 1969], No.33453/69. Heading F1G. The invention relates to a gas turbine engine in which means are provided to bleed off air from the compressor for external use, means being provided for generating steam by utilizing heat in the exhaust gases from the turbine, the steam so generated being admitted directly into the combustion chamber and so into the turbine so as to compensate for the air bled off from the compressor. The engine shown is a modified gas turbine jet engine, the jet nozzle having been removed. The engine comprises compressor 1, combustion chamber 4 and turbine 2 which drives the compressor through shaft 23. The air intake duct 5 is provided with de-icing equipment 20 which may be supplied with air from the compressor through line 26 controlled by valve 21. A steam generator 3 is located in the exhaust duct 6 of the turbine, the outlet duct 10 of the steam generator being connected ...

Gas turbine engine system with a condenser

In one aspect, the system comprises a compressor system 44, a combustor 6, a turbine system 8, vapour generating means 29 having a dry-run capability, for transferring heat to a fluid to be vaporised when not being run dry, a bypass damper 16 and a condenser 18. In one operational position of the damper 16 (during start up) working fluid can bypass the condenser (via line 28) while in another position of the damper 16 the working fluid passes through the condenser. Vapour (eg. steam) may be fed from the outlet 26 of the vapour generating means to the combustor 6, compression system 44 or turbine system 8. An intercooler 40, water treatment area 20, and storage tank 24 may be provided. In another aspect, heating means 50 may be provided for transferring heat from the intercooler 40 to the working fluid downstream of the condenser to suppress visible exhaust plume. The fluid for transferring heat form the intercooler to the heating means may be water, or air, in which case the heating means ...

Method of and apparatus for temporarily increasing the output of propulsive gases from a combustion chamber

... 644,719. Gas turbine plant. NAAMLOOZE VENNOOTSCHAP DE BATAAFSCHE PETROLEUM MAATSCHAPPIJ. May 14, 1948, No. 13284. Convention date, May 14, 1947. [Class 110(iii)] [Also in Group XII] To increase the output of a combustion chamber for a gas turbine plant of the kind in which an air stream is divided during normal operation into primary air which enters the combustion zone and secondary air which mixes with the combustion products leaving the combustion zone, means are provided to pass substantially the whole of said air stream into the combustion zone, to increase the fuel supply to the combustion zone and to add water or other volatile cooling,liquid in such quantity that the temperature of the mixture does not exceed that during normal operation. A combustion chamber for a jet propulsion gas turbine plant, Fig. 1, comprises an outer casing 4, a flame tube 5 and a fuel supply 12. A slide or sleeve valve 6 is arranged around the flame tube 5. In the normal position shown, Fig. 1, the air ...

Gas turbine powere generation system

In a gas turbine power generation system a multiple stage air compressor 8 delivers air at 15 to 30 atmospheres and 100 C, intercooling 7 maintaining stage temperatures at about 100 C. and a stage compression ratio of around two. A minor portion 31 of said air is cooled (cooler 6) and used for turbine (5) blade cooling and the remaining air stream 30 is saturated with water (saturator 15) and used for combustion (combustor 2) after passing through a recuperator 10, 12, 14 in an exhaust gas heat recovery duct 9 of the turbine 5. The combustion chamber 2, produces gases within a temperature range 1300 C. to 1600 C. (firing temperature of 1600-1800{C. are also mentioned) to drive the turbine and generate electricity. Fuel gas for the combustor 2 is utilised in the intercooler 7 prior to passing to a saturator 19, heat exchange coils 20, 21, 23, 25, quench unit 22 and saturator 24.

Method and apparatus for the rapid startup and rapid increase in output of a gas turbine plant

GAS TURBINE ENGINE

Gas-steam turbine plant

... 1,088,784. Gas turbine plant; gas turbine combustion chambers. SULZER BROTHERS Ltd. June 15, 1966 [May 6, 1966], No.26634/66. Headings F1G and F1L, A turbine plant has a combustion chamber 4 with means for maintaining a water film on the internal wall surface 6 so that steam is produced by the heat of combustion, the steam mixing with the combustion gases within the combustion chamber and flowing through a pipe 8 to drive the plant turbines 46, 47. Turbine 47 drives a generator 15. Combustion air is supplied to the burner 5 of the combustion chamber by turbine driven compressors 1, 3 having an intercooler 2 which pre-heats the water being pumped to the combustion chamber and to an additional water injection point 7 downstream of the combustion chamber. The amount of water injected at 7 is controlled by a temperature sensing unit 9. The exhaust from turbine 47 passes through a heat exchanger 48 to effect further pre-heating of the water. Demineralizers 12, 14 are provided in the water line ...

Oxy-fuel power generation and optional carbon dioxide sequestration

A turbine system 100 comprising an oxy-fuel gas turbine generator comprising a combustion chamber and a turbine. Liquid oxygen is pumped to a liquid oxygen feed connected to the combustion chamber, liquid fuel is pumped to a liquid fuel feed connected to the combustion chamber, wherein oxygen and fuel are injected into and combusted in the combustion chamber in the presence of steam which is fed into the combustion chamber via a steam feed. Exhaust fluids are expanded through the turbine to drive an electrical generator. Water and/or steam from the exhaust fluids is separated and recirculated as steam to the steam feed of the combustion chamber by way of an integrated recuperator and separator. The integrated recuperator and separator comprises an evaporator heat exchanger, an economiser heat exchanger, a first stage condenser and a second stage condenser. The second stage condenser comprises a separated carbon dioxide outlet, a separated water outlet, and a cooling water outlet.

INTERNAL-COMBUSTION ENGINE FUER HYDROGEN GAS.

MECHANISM FOR WATER INJECTION WITH GAS TURBINES

GAS TURBINE POWER AUGMENTING SPRAY NOZZLE ASSEMBLY

Energy generating installation

SKID ARCHITECTURE FOR A POWER AUGMENTATION SYSTEM

A fluid delivery skid with a pre-fill system for supplying fluid has one or more stages including a first valve and a second valve, each having an open and closed position. The stages have active and inactive states to provide a desired flow rate of fluid to a n apparatus for distribution of the fluid. In an active state, fluid is received in the stag e and pressurized with the first valve open and the second valve closed. Further, in an active state, fluid is released with the first valve closed and the second open. In an inactive state, at least the second valve is closed. A control unit is connected to a pump unit and controls operation of the pump to regulate the stages to supply pressure at a level determined to achieve the desired flow rate.

GAS TURBINE CYCLE EQUIPMENT, EQUIPMENT FOR RECOVERING CO2 FROM FLUE GAS, AND METHOD FOR RECOVERING EXHAUST HEAT FROM COMBUSTION FLUE GAS

By using a combustion exhaust gas (18) from a power turbine (16), a high-pressure secondary compressed air (12C) is subjected to heat exchange in a first heat exchange unit (19A) of an exhaust heat recovery device (19), and by using resultant heat-exchanged exhaust gas (18A), a low-pressure primary compressed air (12A) is subjected to heat recovery in a second heat exchange unit (19B) of an air saturation tank (31). Then, a primary compressed air (12B) that has been subjected to heat recovery in the second heat exchange unit (19B) is introduced into a secondary air compressor (22) to increase the pressure of the air, and then the high-pressure air is subjected to heat recovery in the first heat exchange unit (19A), producing a secondary compressed air (12D). The secondary compressed air (12D) is introduced into a combustor (14) and combusted using fuel.

GAS TURBINE SYSTEMS AND METHODS EMPLOYING A VAPORIZABLE LIQUID DELIVERY DEVICE

Systems and methods utilizing turbines, including a compressor turbine with a vaporizable liquid delivery device, are presented. A compressor turbine uses the evaporation of a vaporizable liquid at or near thermal equilibrium from the vaporizable liquid delivery device during the compression. The vapor created thereby typically carries the thermal energy discharged after the gas turbine cycle. The amount of liquid vaporized during compression, the length of time vaporization takes, the proximity to thermal equilibrium at which vaporization occurs, the amount of thermal energy recovered by recuperation, and the temperature at the inlet of the combustion chamber are generally interrelated parameters that can be controlled to increase efficiency.

GAS TURBINE SYSTEM

The present invention is equipped with: a combustor (2) having a fuel injection nozzle (4) that injects hydrogen gas (H) and pure water (W); a water storage tank (12) that stores the pure water (W) supplied to the combustor (2); a gas compression device (10) that boosts the pressure of the hydrogen gas (H) supplied to the combustor (2); a fuel supply passage (6) that guides the pressurized hydrogen gas (H) to the combustor (2); and a pressure introduction passage (16), which connects the water storage tank (12) and the fuel supply passage (6), and pressurizes the pure water (W) by means of the pressurized hydrogen gas (H).

PROCESS AND APPARATUS FOR ACHIEVING POWER AUGMENTATION IN GAS TURBINES VIA WET COMPRESSION

A power augmentation apparatus and process for effectively adding a mass flo w of water to the working fluid acquired by the compressor of an industrial ga s turbine, and especially for adding a mass flow of water to a fully-humidifie d working fluid for reducing the work of compression performed by the compress or and achieving a net augmentation of the power produced by the turbine, said apparatus and process preferably including the use of a spray rack group assembly having at least one spray rack water pipe and at least one spray ra ck water nozzle which assembly is ideally positioned a distance away from the compressor inlet. Water mass flow is added preferably in increments which correspond to the spray rack water pipes and associated nozzles. Monitoring of the temperature profile of fluid-cooled rotor blades in the turbine section with an optical pyrometer to detect clogging of cooling pathways in those rotor blades from impurities in the added water, monitoring of the working fluid's ...

GAS TURBINE POWER AUGMENTATION

A method and apparatus for increasing power output and efficiency of gas turbines. Power output is enhanced and NOx emissions are lowered while heat rate penalties are minimized by adding nitrogen or a mixture of nitrogen and water vapor to the gas turbine in conjunction with the use of low pressure steam.

Verfahren zum Betrieb von Gasturbinenanlagen und Einrichtung zur Ausführung des Verfahrens.

Verfahren zum Betrieb von Gasturbinenanlagen.

Einrichtung zur Startschuberhöhung von Turbostrahltriebwerken, insbesondere zum Antrieb von Flugzeugen.

Verfahren zum Ausnützen von Hochdruckgasen einer natürlichen Gasquelle in einer Gasturbinenanlage und Einrichtung zum Durchführen des Verfahrens.

Gasturbinenanlage.

Gasturbinenanlage

Gasturbinenanlage mit Wassereinspritzung

Gas-Dampfturbinenanlage

Gas turbine inlet nebula system with electricalhydrodynamic atomization (EHD)

Es wird ein Gasturbinen-Einlass-Nebelsystem unter Anwendung elektrohydrodynamischer (EHD) Zerstäubung offengelegt. In einer Ausführungsform enthält das Einlass-Nebelsystem: ein Gasturbinensystem (100) mit einem Lufteinlasskanal (118) und mehrere mit einer Wasserversorgung (134) verbundene elektrohydrodynamische (EHD) Düsen (132), wobei die mehreren EHD-Düsen (132) dafür eingerichtet sind, einen Wassersprühnebel zum Verringern einer Temperatur von in den Einlassluftkanal (118) eingesaugter Einlassluft zu erzeugen. In einer weiteren Ausführungsform enthält ein Einlass-Nebelsystem für ein Gasturbinensystem: mehrere elektrohydrodynamische (EHD) Düsen und eine Wasserversorgung in Fluidverbindung mit den mehreren EHD-Düsen.

Procedure for injecting water into a multi-level axial compressor of a gas turbine.

Bei einem Verfahren zum Einspritzen von Wasser in einen mehrstufigen Axialverdichter (10) einer Gasturbine wird mit geringem apparativem Aufwand eine deutliche Leistungssteigerung auch unter sich ändernden Randbedingungen dadurch erreicht, dass das Wasser an mehreren Punkten entlang des Axialverdichters eingespritzt wird, und dass der eingespritzte Wasser-Massenstrom an den einzelnen Einspritzpunkten (18ad) nach Massgabe von Umgebungsbedingungen und Betriebsparametern der Gasturbine derart gesteuert wird, dass sich eine vergleichmässigte Belastung in den einzelnen Stufen des Axialverdichters (10) ergibt.

Combination power station with a device for the printing supply to a spray inlet temperature reduction from gas turbines as well as procedures to its enterprise.

Eine Vorrichtung zur Zufuhr von Wasser an ein Nebelsystem für einen Einlass einer Gasturbine (140) schliesst eine Umleitung von erhitztem Speisewasser aus einem Kreis an eine Pumpe (170) ein, wobei die Pumpe Hochdruckspeisewasser an das Nebelsystem zuführt. Es werden ein Kombikraftwerk sowie ein Verfahren zur Zufuhr von Wasser geschaffen.

Combination power station with a device for the printing supply to a spray inlet temperature reduction from gas turbines as well as procedures to its enterprise.

Eine Vorrichtung zur Zufuhr von Wasser an ein Nebelsystem für einen Einlass einer Gasturbine (140) schliesst eine Umleitung von vom Gasturbinenabgas erwärmten Speisewasser aus einem Kreis an eine Pumpe (170) ein, wobei die Pumpe (170) Hochdruckspeisewasser an das Nebelsystem zuführt. Es werden ein Kombikraftwerk sowie ein Verfahren zur Zufuhr von Wasser geschaffen.

Method is for humidifying suction air of gas turbine and involves air flowing over air channel in which it is accelerated, water being sprayed on air in channel

The method is for humidifying suction air of a gas turbine. The air flows over an air channel (1) in which it is accelerated. Water is sprayed onto the air in the channel. The temperature (75) and the relative humidity (76) of the suction air are measured prior to the water being fed. By means of the measurement values obtained, the amount of water to be fed to the suction air per weight unit is calculated. The temperature (74) of the suction air is additionally measured after the acceleration in the air channel and the measurement value is used as correction parameter for calculating the amount of water to be fed to the suction air per weight unit. In this manner, the maximum amount of water which may be fed to the suction air is accurately calculated, without condensation occurring at any point in the air channel.

Method for controlling a gas turbine and gas turbine for driving a load transient condition.

Die Erfindung betrifft ein Verfahren zur Steuerung eines Übergangszustandes einer Gasturbine (10) sowie eine Gasturbine zum Antrieb einer Last mit einer Steuereinrichtung zur Steuerung des Betriebs der Gasturbine (10) während eines Übergangszustands. Das Verfahren beinhaltet das Empfangen einer Anforderung an die Gasturbine (10) zum Antrieb einer erhöhten Last. Die erhöhte Last ist grösser als eine Last, die von der Gasturbine (10) beim Empfang der Anforderung angetrieben wird. Das Verfahren beinhaltet ausserdem das Bestimmen, ob eine Temperatur eines in einer Brennkammer (20) der Gasturbine (10) zu zündenden Brennstoffs niedriger ist als eine Zieltemperatur des in die Brennkammer (20) zum Antrieb der erhöhten Last einzuführenden Brennstoffs. Abhängig von dieser Feststellung beinhaltet das Verfahren die Steuerung der Einführung eines Zusatzstoffs in die Brennkammer (20) der Gasturbine (10), wenn die Temperatur des Brennstoffs niedriger ist als die Zieltemperatur, um so einen zweckentsprechenden ...

Device and procedure for the cooling of air.

Es wird eine Vorrichtung (10) zum Kühlen von Luft innerhalb einer Luftströmung in Richtung eines Einlasses (9) einer Gasturbine geschaffen, und diese schliesst eine Druckwasserverrohrungs- und Düsenvorrichtung (17) zur Erzeugung eines Wassersprühnebels (13) in die Luftströmung zu dem Einlass (9) und ein Verdampfungselement (14) ein, um den Wassersprühnebel (13) aufzunehmen und eine Druckbeaufschlagung der Luft in der Luftströmung zu bewirken.

Device and procedure for the inlet evaporative cooling loaded by pressure of gas turbine engines.

Es wird eine Vorrichtung zum Kühlen von Luft für einen Einlass (9) einer Gasturbine geschaffen und diese schliesst eine Druckwasserverrohrungs- und Düsenvorrichtung (17) zur Erzeugung eines Wassersprühnebels (13) in eine Luftströmung zu dem Einlass (9); und ein Verdampfungsmedium (14) ein, um den Sprühnebel (13) aufzunehmen und eine Druckbeaufschlagung der Luft in der Luftströmung zu bewirken.

Procedure for the controlling of the transient condition of a gas turbine.

Gemäss einem Aspekt betrifft die Erfindung ein Verfahren zur Steuerung eines Übergangszustandes einer Gasturbine (10). Das Verfahren beinhaltet das Empfangen einer Anforderung an die Gasturbine (10) zum Antrieb einer erhöhten Last. Die erhöhte Last ist grösser als eine Last, die von der Gasturbine (10) beim Empfang der Anforderung angetrieben wird. Das Verfahren beinhaltet ausserdem das Bestimmen, ob eine Temperatur eines in einer Brennkammer (20) der Gasturbine (10) zu zündenden Brennstoffs niedriger ist als eine Zieltemperatur des in die Brennkammer (20) zum Antrieb der erhöhten Last einzuführenden Brennstoffs. Abhängig von dieser Feststellung beinhaltet das Verfahren die Steuerung der Einführung eines Zusatzstoffs in die Brennkammer (20) der Gasturbine (10), wenn die Temperatur des Brennstoffs niedriger ist als die Zieltemperatur, um so einen zweckentsprechenden Wobbe-Index einer Brennstoffkombination zur Förderung eines im Wesentlichen kontinuierlichen Übergangs der Gasturbine (10) ...

Axial compressor with an injection device to a nozzles of a liquid.

Bei einem Axialverdichter (10) zur Verdichtung von Luft, insbesondere für eine Gasturbine, weist der Axialverdichter (10) einen um eine Maschinenachse drehbaren Rotor (11) mit einer Mehrzahl von Laufschaufeln (14) sowie ein den Rotor (11) konzentrisch und mit Abstand umgebendes Gehäuse (13) auf. Das Gehäuse (13) bildet zusammen mit dem Rotor (11) einen ringförmigen Gaskanal (12) und ausserhalb des Gaskanals (12) weist dieses eine ringförmige und konzentrische Zapfluftkammern (16) auf, wobei die Zapfluftkammer mindestens einen Zapfluftschlitz (17) aufweist. Dieser Schlitz steht mit dem Gaskanal (12) in Wirkverbindung, wobei der Axialverdichter (10) mit wenigstens einer Einspritzvorrichtung (18; 18´) zum Eindüsen einer Flüssigkeit ausgerüstet ist. Diese Einspritzvorrichtung (18; 18´) umfasst mindestens eine Düse (22), welche über den Zapfluftschlitz (17) die Flüssigkeit in den Gaskanal (12) eindüst.

turbine control system and power generating system.

Es wird ein Turbinensteuerungssystem bereitgestellt, das das Unterfrequenzverhalten von Gasturbinen mit Hilfe einer schnell reagierenden Leistungserhöhung verbessert. Das System umfasst einen Speicher (112), der eine Mischung von Antriebsbrennstoff wie zum Beispiel Ethanol oder Methanol und entmineralisiertem Wasser in einem vorgegebenen Verhältnis unter Druck speichert, welches dem Gasturbinenkompressor (122) bereitgestellt wird, um den Massenstrom zur Turbine zu erhöhen, wenn ein Sensor einen Unterfrequenzzustand des Stromnetzes feststellt.

Method of operating a gas turbine.

Verfahren zum Betreiben einer Gasturbine, mit den Schritten: Ermitteln eines Soll-Zustandes an einer Turbinenstufe (84); Ermitteln einer Ist-Heissgaspfadtemperatur; Ermitteln einer Soll-Heissgaspfadtemperatur an der Turbinenstufe (84); Entnahme eines Luftstroms aus einer Verdichterstufe (82); Abschätzen einer dem Luftstrom hinzuzufügenden geschätzten Fluidmenge, um eine Soll-Heissgaspfadtemperatur an der Turbinenstufe zu erreichen; Hinzufügen eines Fluids in einer Menge im Wesentlichen gleich der geschätzten Fluidmenge zu dem Luftstrom, um einen Feuchtluftstrom zu erzeugen; und Einspritzen des Feuchtluftstroms in eine Düse an der Turbinenstufe (84). Das Verfahren ermöglicht die Lebensdauerverlängerung von Heissgaspfadkomponenten.

Liquid fuel-heating and Water injection manifold pressure relief vent combined cycle power plant.

Die Erfindung betrifft ein Flüssigbrennstoff-Erwärmungs- und Wassereinspritzsystem für ein Kombikraftwerk (200), bei welchem eine Kesselspeisewasserpumpe (290) einem Abhitzedampferzeuger (270) Speisewasser zuführt und das erwärmte Speisewasser in einer Flüssigbrennstoff-Erwärmungseinrichtung (235) zur Flüssigbrennstofferwärmung verwendet wird. Das Speisewasser von der Kesselspeisewasserpumpe (280) wird ferner zur Wassereinspritzung (255) in eine Brennkammer (220) verwendet.

SYSTEM AND METHOD OF ENERGY PRODUCTION, USING ION TRANSFER DEVICE

System and method for augmenting turbine power output

Improvements with the turbomotors with combustion

STEAM INJECTION SYSTEM FOR A GAS TURBINE

Thermal machine e.g. gas turbine, for e.g. propulsion of microdrone, has main and secondary combustion chambers situated in cylindrical central volume delimited at base by rotors and at lateral surface by walls

The machine has main and secondary combustion chambers (19, 20) situated in a cylindrical central volume delimited at base by low pressure and high pressure rotors (3, 4) and at lateral surface by inner, intermediate and outer walls (22, 23, 24). The walls (23, 24) define an annular outer gas circulation conduit (25) connecting an outlet of a low pressure compressor (15) to an inlet of a high pressure compressor (16). The walls (22, 23) define an annular inner gas circulation conduit (26) connecting an outlet of the compressor (16) to an inlet of the chamber (19).

CONTROL SYSTEM AND METHOD FOR GAS TURBINE INLET-AIR WATER-SATURATION AND SUPERSATURATION SYSTEM

METHOD TO INCREASE POWER OF COMBINED-CYCLE POWER PLANT, AND COMBINED-CYCLE POWER PLANT TO EXECUTE SAME

The present invention relates to a method to temporarily increase the power of a gas turbine (11), a part of combined-cycle power plant (10). Exhaust gas of the gas turbine (11) is used in a heat recovery vapor generator (13) to generate vapor for a water/vapor cycle having a vapor turbine (12), comprising: a high pressure vapor turbine (20); a medium pressure turbine (21); and a low pressure turbine (22). The method comprises a step for injecting vapor from the water/vapor cycle to the gas turbine (11) at a preset injection pressure. Vapor with a lower pressure than the preset injection pressure is obtained from the water/vapor cycle and pressure obtained from the water/vapor cycle goes through a compression step by an individual compressing means (14) to reach the preset injection pressure. And the compression vapor is injected into the gas turbine (11), thus improving efficiency. Preferably, the individual compressing means (14) comprises at least one vapor operating ejector. COPYRIGHT ...

Förfarande för drift av en gasturbinkraftanläggning och gasturbinkraftanläggning

Exhaust gas recirculation type combined plant

An exhaust gas recirculation type gas turbine apparatus includes a compressor for compressing air, a combustion chamber for burning fuel and compression air exhausted from the compressor, a gas turbine driven by exhaust gas from the combustion chamber, a recirculation path for recirculating a part of the exhaust gas to an intake of the compressor, a recirculation amount control unit for adjusting the amount of exhaust gas to be returned to the intake of the compressor corresponding to a change in load of the gas turbine, and a spray unit for introducing liquid droplets into the interior of the compressor in which mixing gas, consisting of gas turbine exhaust gas passing through the recirculation path and air, flows so as to vaporize the introduced liquid droplets appearing to flow in the compressor.

Gas turbine installation

Disclosed is a gas turbine power generating system capable of achieving a high output power and a high power generating efficiency under conditions with a small amount of supplied water and less change in design of a gas turbine.A fine water droplet spraying apparatus (11) is disposed in a suction air chamber (22) on the upstream side of an air compressor (2), and a moisture adding apparatus (7) for adding moisture to high pressure air supplied from the compressor (2) is disposed. A regenerator (5) for heating the air to which moisture has been added by using gas turbine exhaust gas as a heat source is also provided. With this configuration, there can be obtain an effect of reducing a power for the compressor (2) and an effect of increasing the output power due to addition of moisture to air (20) for combustion. Further, since the used amount of fuel is reduced by adopting a regenerating cycle, the power generating efficiency is improved.

Annular injection apparatus for wet compression

A technical object of the present invention is to provide an annular injection apparatus for wet compression which enables sprayed droplets to maximally evaporate without being drained as condensate water, thereby reducing compression work of the compressor. To this end, the annular injection apparatus for wet compression according to the present invention is an annular injection apparatus for wet compression which is used for a compressor including a nose cone and a bell mouth in an inlet of a flow path, in which droplets are sprayed to a portion except for portions directed toward the nose cone and the bell mouth.

THERMAL ENERGY STORAGE AND HEAT EXCHANGER

Thermal energy storage and heat exchanger, distinctive in that it comprises: a number of hardened concrete thermal energy storage elements; a housing, into which said elements have been arranged; an active heat transfer and storage medium in the volume between said elements and said housing, in the form of either: a stagnant liquid or phase change material, or a dynamic fluid arranged to flow in the volume between said elements and said housing; at least one means for delivery of thermal energy to the thermal energy storage; at least one means for taking out thermal energy from the thermal energy storage; and thermal insulation. 1. A thermal energy storage and heat exchanger comprising:a number of hardened concrete thermal energy storage elements;a housing, into which the elements have been arranged;an active heat transfer and storage medium in the volume between the elements and the housing, in the form of either: a stagnant liquid or phase change material, or a dynamic fluid arranged to flow in the volume between the elements and the housing;at least one means for delivery of thermal energy to the thermal energy storage; at least one means for taking out thermal energy from the thermal energy storage; and thermal insulation.2. The thermal energy storage and heat exchanger according to claim 1 , comprising:a dynamic fluid, chosen amongst thermal oils, exhaust gas, air, flue gas, combustion gas, inert gas, other gas, molten salts and molten metals, as active heat transfer and storage medium in the volume between the elements and the housing,at least one inlet for the dynamic fluid to the housing, andat least one outlet for the dynamic fluid from the housing.3. The thermal energy storage and heat exchanger according to claim 1 , comprising:a stagnant liquid chosen amongst thermal oils, molten salts and molten metals or phase change material, as active heat transfer and storage medium in the volume between the elements and housing; anda heat exchanger embedded in some ...

Gas turbine engine

Device for water or steam injection into the working medium of a gas turbine

In einer Gasturbinenanlage, bestehend aus einem Kompressor (1), einer oder mehreren Brennkammern (2), einer Hochdruckgasturbine (3) und einer Nutzleistungsturbine (24), wird Wasser oder Wasserdampf in den Strom der von dem Kompressor (1) komprimierten Verbrennungsluft eingespritzt. Die Einspritzdüsen (22) sind in einem Krümmer (20) eines außenliegenden Verbindungsgehäuses (18) angeordnet, das aus einem radialen, mit dem Austritt des Kompressors (1) verbundenen Gehäuseteil (19) und aus einem axialen, mit dem Eintritt der Brennkammer (2) verbundenen Gehäuseteil (21) besteht.

EXTENDED GAS TURBINE PROCESS HAVING AN EXPANDER

添加剤送給システム及び方法

HUMID AIR GAS TURBINE, CONTROLLER OF HUMID AIR GAS TURBINE, AND METHOD OF CONTROLLING HUMID AIR GAS TURBINE

PROBLEM TO BE SOLVED: To make compatible the low NOx with the flame stability of a combustor before and after starting the addition of moisture to a humid air gas turbine. SOLUTION: This humid air gas turbine comprises a compressor; a humidificator 4 for generating humid air by adding moisture to the compressed air supplied from the compressor; a combustor 2; a turbine 3; a recuperator 5 for effecting heat exchange between the exhaust gas from the turbine and the humid air; an economizer 22 for effecting heat exchange between the exhaust gas from the recuperator and water; and a system for supplying the water heated by the economizer to the humidifier 4. The humid air gas turbine further comprises a temperature measurement device for measuring the temperature of exhaust gas discharged from the economizer; and a controller for adjusting the amount of moisture to be supplied to the humidifier according to a temperature signal from the temperature measurement device. COPYRIGHT: (C)2009,JPO ...

СИСТЕМА И СПОСОБ ДЛЯ ПОВЫШЕНИЯ ВЫХОДНОЙ МОЩНОСТИ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Система для повышения выходной мощности газотурбинного двигателя, имеющего воздуховод, расположенный перед газотурбинным двигателем, включающим камеру сгорания и компрессор, содержит насосный агрегат. К насосному агрегату подключен блок управления, предназначенный для регулирования числа оборотов насоса, устройство для промывки и, по меньшей мере, одно устройство для впрыска жидкости. Устройство для промывки содержит, по меньшей мере, одну форсунку и, по меньшей мере, один клапан, предназначенный для регулирования расхода жидкости, подводимой, по меньшей мере, к одной форсунке. По меньшей мере, одна форсунка устройства для промывки предназначена для впрыска струи распыленной жидкости так, чтобы эта струя падала на лопатки компрессора и смачивала эти лопатки, тем самым, обеспечивая удаление осажденного материала с лопаток. Устройство для впрыска жидкости также соединено с насосным агрегатом и содержит, по меньшей мере, одну форсунку и, по меньшей мере, один клапан, предназначенный для регулирования ...

СПОСОБ ПРЕОБРАЗОВАНИЯ ТЕПЛОВОЙ ЭНЕРГИИ В МЕХАНИЧЕСКУЮ В ГАЗОТУРБИННОМ ДВИГАТЕЛЕ И ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ

Использование: в газотурбинных двигателях. Сущность изобретения: термодинамическое состояние вводимого по меньшей мере в первую турбинную ступень 8 рабочего тела изменяют, расширяя и закручивая до ввода в нее относительно продольной оси газотурбинного двигателя, с последующим охлаждением рабочего тела с измененным термодинамическим состоянием. охлаждение рабочего тела с измененным термодинамическим состоянием производят воздухом под давлением, по меньшей мере равным давлению рабочего тела с измененным термодинамическим состоянием. Газотурбинный двигатель имеет по меньшей мере две размещенные в проточной части турбинные ступени 8, 9, компрессор 3 и источник 1 нагретого рабочего тела, имеющий зону H расширения и закрутки нагретого тела и расположенную за ней зону 2 смешения нагретого рабочего тела с охладителем. Зона 2 смешения нагретого рабочего тела с охладителем сообщается с проточной частью компрессора, давление которой по меньшей мере равно давлению рабочего тела в зоне 2 смешения. 2 ...

ТУРБИННАЯ УСТАНОВКА, РАБОТАЮЩАЯ НА ВЛАЖНОМ ВОЗДУХЕ

Изобретение направлено на сокращение времени, необходимого для запуска, и предотвращение чрезмерного увеличения тепловых нагрузок на лопатках турбины. Турбинная установка, работающая на влажном воздухе, включает в себя компрессор; камеру сгорания; турбину; блок рекуперации тепла выхлопных газов для рекуперации тепла выхлопных газов турбины для получения высокотемпературной влаги; систему подачи топлива, имеющую клапан регулировки расхода топлива; блок получения температуры выхлопных газов для получения температуры выхлопных газов, выпускаемых во время приведения в движение турбины; блок вычисления показателя влажности газа сгорания для определения показателя влаги, содержащейся в газе сгорания; блок вычисления верхнего предела температуры выхлопных газов для установления верхнего предела температуры выхлопных газов на основе показателя влажности газа сгорания и отношения давлений; блок вычисления разности температур выхлопных газов для определения разности между верхним пределом температуры ...

СИСТЕМА ЗАЩИТЫ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ ВЕРТОЛЕТА

Группа изобретений относится к технике защиты от перегрузки вертолетных двигателей. Система защиты от перегрузки включает компьютер для хранения данных и устройство ввода, например клавиатуру, для ввода профиля безопасной температуры для запуска газотурбинного двигателя. Предусмотрен температурный датчик для измерения фактической температуры на выходе турбины во время запуска газотурбинного двигателя вертолета. Фактическая температура сравнивается с профилем безопасной температуры, и вода и/или спирт инжектируются в двигатель в случае, когда фактическая температура превышает безопасную температуру. Раскрыто применение размещенного на земле резервуара для использования во время запуска и бортового резервуара для использования во время полета. Группа изобретений позволяет исключить «горячие запуски» газотурбинного двигателя и режимы его перегрузки в процессе полета вертолета. 3 н. и 6 з.п. ф-лы, 4 ил.

СПОСОБ ФОРСИРОВАНИЯ ТУРБОРЕАКТИВНОГО ДВИГАТЕЛЯ

FIELD: engines and pumps. SUBSTANCE: method of forcing the turbojet engine, consisting of an input device, a turbocharger, in which the turbine blades are cooled by air drawn from a compressor, the output device. The input to the compressor is supplied with water. Water is supplied to the flight speed more than 3.2 Mach numbers at the gas temperature before the turbine blades of more than 2300 K, and the compressor rotational speed exceeding more than 1.3 times the speed of the compressor under takeoff. EFFECT: method allows aircraft with turbojet engines todevelop hypersonic flight speed, can be used as interceptor aircraft. 3 cl, 5 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 616 137 C1 (51) МПК F02C 3/30 (2006.01) F02C 7/143 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ На основании пункта 1 статьи 1366 части четвертой Гражданского кодекса Российской Федерации патентообладатель обязуется заключить договор об отчуждении патента на условиях, соответствующих установившейся практике, с любым гражданином Российской Федерации или российским юридическим лицом, кто первым изъявил такое желание и уведомил об этом патентообладателя и федеральный орган исполнительной власти по интеллектуальной собственности. (21)(22) Заявка: 2016122300, 06.06.2016 06.06.2016 (73) Патентообладатель(и): Письменный Владимир Леонидович (RU) Дата регистрации: 12.04.2017 Приоритет(ы): (22) Дата подачи заявки: 06.06.2016 1127856 A, 18.09.1968. RU 2296872 C9, 10.04.2007. RU 2289705 C2, 20.12.2006. (45) Опубликовано: 12.04.2017 Бюл. № 11 Адрес для переписки: 416506, Астраханская обл., г. Ахтубинск-6, ул. Жуковского, 26, кв. 54, Письменному В.Л. 2 6 1 6 1 3 7 (56) Список документов, цитированных в отчете о поиске: GB 685944 A, 14.01.1953. GB R U (24) Дата начала отсчета срока действия патента: (72) Автор(ы): Письменный Владимир Леонидович (RU) 2 6 1 6 1 3 7 R U (57) Формула изобретения 1. Способ форсирования турбореактивного ...

АРХИТЕКТУРА УЗЛА ДЛЯ СИСТЕМЫ УВЕЛИЧЕНИЯ МОЩНОСТИ

... 1. Узел подачи текучей среды, выполненный для системы увеличения мощности, содержащий: ! одну или более ступеней, имеющих активное состояние и неактивное состояние, причем каждая из ступеней содержит, по меньшей мере, первый и второй клапаны, причем каждый первый и второй клапаны имеют открытое и закрытое положения; ! при этом в активном состоянии текучая среда принимается в первую ступень, сжимается до первого заданного уровня и выпускается, при этом, когда первый клапан находится в открытом положении и второй клапан находится в закрытом положении, текучая среда принимается в ступень и сжимается, и при этом, когда первый клапан находится в закрытом положении и второй клапан находится в открытом положении, текучая среда выпускается; и ! при этом в неактивном состоянии, по меньшей мере, один второй клапан находится в закрытом положении, чтобы, по меньшей мере, существенная часть текучей среды не выпускалась из ступени. ! 2. Узел по п.1, в котором первый клапан питает первый насос, а второй ...

СИСТЕМА (ВАРИАНТЫ) И СПОСОБ (ВАРИАНТЫ) ДЛЯ ПОВЫШЕНИЯ ВЫХОДНОЙ МОЩНОСТИ ТУРБИНЫ, А ТАКЖЕ СИСТЕМА ЗАЩИТЫ ВХОДНОГО КАНАЛА ГАЗОВОЙ ТУРБИНЫ ОТ КОРРОЗИИ

... 1. Система для повышения выходной мощности газовой турбины, содержащая: насосный блок; блок управления, соединенный с насосным блоком и выполненный с возможностью регулирования работы насосного блока в соответствии с заданной функцией компьютерного анализа динамического переноса текучей среды на основе, по меньшей мере, одного определяемого параметра для образования модели управления; промывочный блок, соединенный с насосным блоком и содержащий, по меньшей мере, одну форсунку и, по меньшей мере, один клапан для управления расходом воды, подаваемой в, по меньшей мере, одну форсунку; по меньшей мере, один блок впрыска воды, соединенный с насосным блоком и содержащий, по меньшей мере, одну форсунку и, по меньшей мере, один клапан для управления расходом воды, подаваемой в, по меньшей мере, одну форсунку; и блок мониторинга погоды, соединенный с блоком управления и указывающий, по меньшей мере, один из определяемых параметров. 2. Система по п.1, дополнительно содержащая блок сбора воды, соединенный ...

ТЕПЛОВОЙ ДВИГАТЕЛЬ С ВЫСОКИМ КПД

... 1. Тепловой двигатель, содержащий два независимых ротора (3, 4, 4'), предпочтительно коаксиальных (XX), каждый из которых установлен соответственно в одном из двух картеров (5, 6, 6'), при этом первый ротор (3) входит в состав ступени (1) низкого давления, а второй ротор (4, 4') входит в состав ступени (2, 2') высокого давления, при этом каждая ступень (1, 2, 2'), оборудованная своим ротором (3, 4, 4') и соответствующими неподвижными органами (9, 10, 13, 14, 89, 91, 92, 93) подготовки текучей среды в комбинации со средствами сжатия газов, называемыми компрессором (15, 16, 90), и средствами расширения газов, называемыми детандером (17, 18, 90); и по меньшей мере, одну камеру (19, 20) сгорания, отличающийся тем, что указанная, по меньшей мере, одна камера сгорания расположена в центральном по существу цилиндрическом объеме, ограниченном по своим основаниям двумя роторами (3, 4, 4') и их картерами (5, 6, 6'), и по своей боковой поверхности первой стенкой (22), по существу цилиндрической и ...

Performance increasing method for piston IC engine and gas turbine

The performance increased is realised by combustion of fuel, to which water has been added. The water is admitted mostly as steam into the suction manifold of the IC engine or gas turbine. Pref. the steam vol. is max. the same as that of the fuel. Typically the steam is generated by the engine, or turbine, waste heat. The engine has at least one exhaust elbow (1), surrounded by a housing (2) with at leat one nozzle (3), pointed onto the elbow, coupled by a pipe (4) to a pump (5) delivery side.

Vorrichtung an der Öffnung von Düsentriebwerk

Um die Luftfahrtsicherheit zu verbessern und den Verbrauch von Treibstoff zu verringern gibt es eine Geräteschaft, um Wasser zu verdampfen, unter Druck zu setzen und in den äußeren Düsen (1) passend auszurichten. Das Wasser führt man durch eine Wasserleitung (3) und Wasserpumpe (2) in den hinteren Teil (12) des Düsentriebwerks (1), um es mit einem Wärmewechsler (16) aufzuheizen. Dabei nutzt man die durch den Betrieb des Düsentriebwerks entstandene Restwärme. Den entstandenen Wasserdampf führt man durch einen Thermostaten (4) und eine Rohrleitung (5) in einen mit Rückschlagventil ausgerüsteten Druckbehälter (7), Dazu gehört auch ein die Strömung steuerndes Regelventil (8), wodurch die Flügel und die Turbine gedreht werden. Aus der Turbine (10) führt man den unter Druck gesetzten Wasserdampf mit einer Rohrleitung (11) in den vorderen Rand des Düsentriebwerks (1) an die Düsen (12) und somit ans Ziel.

A gas turbine engine

GAS TURBINE ENGINE

A gas turbine engine comprising a compression means, combustion means, a first turbine, and a second turbine is provided with improved thermal efficiency and power output through bypassing a portion of the engine operating fluid from a first engine position downstream of at least a portion of the compression means and upstream of a control area of the first turbine and injecting at least a portion of the bypassed flow downstream of the control area of the first turbine. High pressure steam is injected at a position between the engine position initiating the bypass and the engine position injecting the bypass into the fluid stream. The amount of steam injected is substantially equivalent in mass flow to the removed fluid.

Thrust generator

Improvements in thrust augmenting devices for aircraft gas turbine engines

... 756,264. Generating combustion products under pressure. GENERAL MOTORS CORPORATION. July 20, 1954 [July 31, 1953], No. 21121/54. Class 51(1). In an aircraft gas turbine engine having a combustion chamber comprising an outer casing 22 and an inner flame tube 24, a ring, manifold 40 is disposed in the space between the outer casing and the flame tube and has apertures 42 in register with apertures 30 in the flame tube wall whereby evaporative coolant fluid such as water or water-alcohol may be injected into the flame tube so as to augment the thrust of the engine. Fluid is supplied from a manifold 36 through ducts 38 to each of a plurality of combustion chambers disposed in circular formation, the ducts 38 each connecting by a fitting 52 to a ring manifold 40. The manifold 40 is supported by means of two pins 44 projecting radially inwardly from the outer casing 22 which engage slidingly in 'sleeves 48 secured to the manifold so as to allow for expansion. The invention is applicable to aircraft ...

Engines

An engine comprises a first heat exchanger 3 cooling air upstream of turbomachinery component(s) 4, received from air intake 2a via a first flow path 10. A second flow path 12 bypasses the heat exchanger. A flow control arrangement 13 comprises first and second relatively movable portions to selectively obstruct the second flow path, e.g. pre-cooling airflow at hypersonic flight speeds, but only precooling a portion of intake air at subsonic flight speeds. Hinged vanes (24, figure 9), or linearly moveable intake cone may selectively block an annual gap 22, or inner and outer structures (14, 15, figure 15) may rotate to misalign slots (28, 29). A disclosed engine has first flow path cooling compressor inner radial portion (e.g. blade roots) and second airflow path extends through compressor outer radial portion (e.g. blade tips). A disclosed engine has a precooler upstream a lower-pressure compressor and an intercooler (second heat exchanger) upstream a higher-pressure compressor. A disclosed ...

Gas steam turbine system

Nozzles for water injection in a turbine engine

Power process utilizing humidified combusted air to gas turbine

METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINES

A method for operating a gas turbine engine (10) including a compressor (14, 16), a combustor (18), and a turbine (20, 22, 24), coupled together in serial flow arrangement, and a fuel heating system (50) including a heat exchanger (70) and an economizer (80). The method includes channeling fuel through the heat exchanger, channeling a working fluid through the heat exchanger to facilitate regulating the operating temperature of the fuel and the operating temperature of the working fluid, and channeling the fuel and the working fluid into the gas turbine engine combustor to facilitate increasing a fuel efficiency of the gas turbine engine.

INTERNAL COMBUSTION ENGINE OF HYDROGEN GAS

A hydrogen gas internal combustion engine provided with a hydrogen jet gas nozzle and water spray jet nozzle in the combustion chamber to directly jet hydrogen gas and water spray therein. The sprayed water is instantly vaporized to steam by igniting the hydrogen gas thereby utilizing the combustion/explosion energy of the hydrogen gas and the steam in a combustion to obtain mechanical dynamic energy.

TURBINE WASH PORT FOR A GAS TURBINE ENGINE

An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings.

GAS TURBINE SYSTEM

The present invention is equipped with: a combustor (2) having a fuel injection nozzle (4) that injects hydrogen gas (H) and pure water (W); a water storage tank (12) that stores the pure water (W) supplied to the combustor (2); a gas compression device (10) that boosts the pressure of the hydrogen gas (H) supplied to the combustor (2); a fuel supply passage (6) that guides the pressurized hydrogen gas (H) to the combustor (2); and a pressure introduction passage (16), which connects the water storage tank (12) and the fuel supply passage (6), and pressurizes the pure water (W) by means of the pressurized hydrogen gas (H).

DEVICE AND METHOD FOR TEMPORARILY INCREASING POWER

L'invention concerne le domaine des turbomachines, et plus spécifiquement un dispositif (13) et un procédé d'augmentation temporaire de puissance d'au moins une première turbomachine (5A). Ce dispositif (13) comprend un réservoir (14) de liquide réfrigérant et un premier circuit d'injection (16A), connecté audit réservoir (14) et débouchant sur au moins une tuyère d'injection (22) apte à être installée en amont d'au moins un étage de compresseur (8) de la première turbomachine (5A). Ce premier circuit d'injection (16A) comporte au moins une première vanne de passage (23) configurée pour s'ouvrir quand une surpression excède un seuil prédéterminé par rapport à une pression en aval d'au moins un étage de compresseur (8) d'une deuxième turbomachine (5B), de manière à permettre l'écoulement du liquide réfrigérant vers ladite tuyère d'injection (22) du premier circuit d'injection (16A).

Hydrogen Fuelled Gas Turbine

POWER PROCESS UTILIZING HUMIDIFIED COMBUSTED AIR TO GAS TURBINE

A process for producing mechanical power utilizing compressed humidified hot air and a fuel, which are mixed together and combusted and the resulting hot combustion gas is expanded through a gas turbine. The air is initially compressed and intercooled against a water stream, and then further compressed and passed directly to a heat recovery unit where it is humidified using the water from the compressed air intercooling step. The compressed humidified air is further heated and combined with a fuel in a combustor, and the resulting hot combustion gas is expanded through a gas turbine to produce mechanical power needed for driving the air compression. The hot turbine exhaust gas is cooled against the compressed humidified air stream and against the water stream, and then discharged to the atmosphere. By eliminating a usual separate air aftercooling and saturator unit upstream of the air combined humidifying and heating step, process thermal efficiency for the present process is increased ...

TO INCREASE THE EFFECTIVENESS AND SPEED CONTROL GAS TURBINE BY MEANS OF USE OF AUXILIARY AIR SYSTEM

СПОСОБ ГЕНЕРАЦИИ МОЩНОСТИ, КОМБИНИРОВАННАЯ ЭНЕРГЕТИЧЕСКАЯ УСТАНОВКА ДЛЯ ЕГО ОСУЩЕСТВЛЕНИЯ, ГАЗОВАЯ ТУРБИНА И СПОСОБ АДАПТАЦИИ ГАЗОВЫХ ТУРБИН К РАБОТЕ С ЧАСТИЧНЫМ ОКИСЛЕНИЕМ ТОПЛИВА (ВАРИАНТЫ)

Энергетическая газотурбинная установка для выработки энергии посредством газотурбинного цикла, в которой более эффективное использование тепловой энергии достигается сжиганием выхлопных газов (109), а частичное окисление указанных выхлопных газов (109) достигается подачей достехиометричеких количеств воздуха и пара в каталитический реактор (107) с образованием первой стадии окисления, за которой в указанной турбине (103) следует дополнительное окисление, происходящее в энергетической турбине (104) или за ней, причем указанная энергетическая турбина, в свою очередь, установлена за каталитическим реактором (107). Каталитическое частичное окисление может быть осуществлено благодаря подаче инициирующего агента, преимущественно водорода. Особенностью способа согласно изобретению является то, что водород, подаваемый на вход реактора через инжектор (113), производится путем утилизации части газа, уходящего из реактора, энергетической турбины или реактора реформинга предназначенного для преобразования ...

[...] for a gas turbine

Improvements with the adjusting devices of the temperature of gases

GAS TURBINE

HIGH EFFICIENCY THERMAL ENGINE

Methods and apparatus for water injection in a turbine engine

Methods and apparatus for injecting water into a turbine engine are described. In one embodiment, water injection apparatus is provided for injecting water into the gas flow through the engine, e.g., at a high pressure and/or low pressure compressor inlet. The water injection apparatus includes a plurality of nozzles arranged so that water injected into the gas flow by the nozzles results in substantially uniformly reducing the temperature of the gas flow at the high pressure compressor outlet.

System and method for augmenting power output from a gas turbine engine

The present invention discloses a method and system for augmenting shaft output of stationary gas turbines that can be used in multiple modes of operation. The system comprises a washing unit ( 25, 27, 28 ) adapted to inject a spray ( 26 ) of atomized liquid so as to impinge on the compressor blades ( 12 ) in order to wet said blades ( 12 ), thereby obtaining a release of fouling material from said blades ( 12 ); and at least one liquid injection unit ( 21, 23, 24, 29, 210, 212, 214, 215, 216 ) adapted to inject a spray ( 22, 211, 213 ) of atomized liquid into an air stream of said turbine duct ( 101 ) or at the gas turbine ( 10 ) in order to increase a mass flow of said air flow, wherein the power output from said gas turbine engine can be augmented. With the invention follows also benefits such as fuel savings and improved environmental performance by reduction of emissions.

Combustor fuel supply assembly and related method

A system includes a turbine fuel supply system (40). The turbine fuel supply system includes a first turbine fuel mixer (52) configured to mix a first liquid fuel (42) and a first deaerated water (15) to generate a first fuel mixture. The first fuel mixture is configured to combust in a combustor (16) of a gas turbine engine (10). The turbine fuel supply system also includes a deaerated water flow path (70) configured to route the first deaerated water (15) to the first turbine fuel mixer (52) and a liquid fuel flow path configured to route the first liquid fuel to the first turbine fuel mixer (52).

Gas turbine equipment utilizing high humidity

A gas turbine equipment utilizing.high humidity, for preventing generation of white smoke throughout a year, and for restraining radiation of extra heat so as to restrain lowering of heat efficiency, the equipment comprising a humidifying device (6) for humidifying compressed gas for combustion, a heat recovery device for recovering exhaust heat from a gas turbine (1) or the compressed air so as to heat humidifying water in the humidifying device (6), a recuperator (7) for recovering exhaust heat from the gas turbine (1) and heating the compressed gas for combustion, a dehumidifying device (10) for dehumidifying and recovering moisture in the exhaust gas having passed through the recuperator (7), and an exhaust gas reheater (11) for heating the exhaust gas after dehumidification, and further comprising a temperature measuring device (27) for measuring a temperature of the exhaust gas passing through the exhaust gas reheater (7), and a heating temperature adjusting means for increasing the ...

Gas turbine power plant

Process and apparatus for achieving power augmentation in gas turbines via wet compression

The net output of an industrial gas turbine (101) including an axial-flow multistage compressor (103) having an inlet (102) for acquiring a working fluid comprising air, is augmented using a process comprising the step of providing, to the working fluid acquired by the axial-flow compressor (103), droplets of a liquid which possesses a high latent of vaporization to reduce the temperature increase of the working fluid caused by compression and to thereby achieve an increase in the net output of the gas turbine (101) as measured against the net output of the gas turbine (101) under comparable conditions but without said liquid being provided. The droplets are provided by droplet-addition means (201) located a sufficient distance away from the compressor inlet (102) whereby, in the event of any element of said means breaks away and is carried with the inlet air towards the compressor inlet, that element is gravitationally pulled to a lower surface (136) of an inlet duct (133) to the compressor ...

Internal combustion engine for hydrogen gas

A hydrogen gas internal combustion engine has a hydrogen gas jet nozzle (6) and a water spray jet nozzle (7) arranged to jet hydrogen gas (8) and water spray (9) directly into the combustion chamber (10) in which air has been compressed. The water is instantly vaporized to steam by the igniting hydrogen gas so that the combustion explosion energy of the hydrogen gas and the energy generated by the vaporizarion of the steam are used in combination to obtain mechanical energy. This system is applicable to different types of internal combustion engines, e.g. reciprocating piston engines, rotary engines, and gas turbines.

DRAIN DISCHARGE EQUIPMENT FOR COMPRESSOR AND GAS TURBINE SYSTEM

PROBLEM TO BE SOLVED: To provide a gas turbine system which can achieve stably operation and high efficiency. SOLUTION: The gas turbine system includes a compressor for compressing air with liquid sprayed, a combustor which is disposed in a some part of a pipe branched from a some part of a drain capture pipe connected to a discharge part of the compressor, and combusts the fuel mixed with compressed air from the compressor, and a turbine to be driven with combustion gas combusted in the combustor. The gas turbine system further includes a separator which is disposed in a some part of the drain capture pipe connected between stages and/or to a discharge part of the compressor, and separates drain from the compressor into compressed air and liquid drain. The separator has a means for intermittently discharging the liquid drain separated by the separator to a discharge system. COPYRIGHT: (C)2012,JPO&INPIT ...

Radial staging method and configuration of a liquid injection system for power plants

A turbine power plant employs a radial staging of a liquid injection system to provide a uniform fluid distribution, for use in wet compression. The liquid injection system can be actuated to inject liquid to various radial regions of an air intake case of the turbine power plant. During a stage one actuation, liquid is directed to a first radial region of the air intake case. During a stage two actuation, liquid is directed to the first radial region and also to a second radial region of the air intake case.

Method for injecting water into a multistage axial compressor of a gas turbine

A method is disclosed for injecting water into a multistage axial compressor of a gas turbine. With low equipment cost, a significant power enhancement can be achieved, even under changing boundary conditions, by water being injected at a plurality of points along the axial compressor, and by the injected water mass flow being controlled at the individual injection points in accordance with ambient conditions and operating parameters of the gas turbine in such a way that an evened-out loading in the individual stages of the axial compressor can be created.

System for turbine combustor fuel assembly

A system includes a gas turbine engine having a combustor, a liquid fuel supply coupled to the combustor, and a water supply coupled to the liquid fuel supply. The water supply is configured to flow water through the liquid fuel supply while the liquid fuel supply is not in use to flow a liquid fuel.

Gas turbine power plant with a gas turbine installation, and method for operating a gas turbine power plant

A gas turbine power plant and a method for operating a gas turbine power plant are provided. The power plant includes a gas turbine installation which may supply a mains supply network with electric power and includes a compressor and an associated first gas turbine. Differing from previous gas turbine installations, the compressor of the gas turbine installation and the first gas turbine of the gas turbine installation are decoupled from each other. A second turbine is provided which drives compressor. As a result, the compressor of the gas turbine installation is operated independently of the first gas turbine. Influences on the mains supply network side, such as generating deficiencies in the main supply network, which act upon the first gas turbine as a result of speed reduction, are also not able to have an impact upon the compressor which is decoupled from the first gas turbine.

Gas Turbine System, Control Device for Gas Turbine System, and Control Method for Gas Turbine System

Provided is a gas turbine system capable of dealing with a request for output increase even when high-pressure hot water generated using solar thermal energy cannot be used according to the operating state of the gas turbine system. A gas turbine system which sucks in intake air from an air intake duct by a compressor and drives a gas turbine by combustion gas obtained by burning air and fuel by a combustor, said gas turbine system being provided with pipes for generating high-pressure hot water by providing a solar collecting tube that utilizes solar heat and spraying the high-pressure hot water into the intake air sucked in by the compressor, and pipes for spraying normal temperature water into the intake air sucked in by the compressor.

Solar Assisted Combined Cycle Power Plant

Disclosed is a solar assisted combined cycle power plant having a compressor that pressurizes combustion air, a combustor that mixes and burns the combustion air and gas turbine fuel to generate a high-temperature combustion gas, a gas turbine that drives the compressor by using the combustion gas, an exhaust heat recovery steam generator that obtains steam from thermal energy of a gas exhausted from the gas turbine, and a steam turbine that is driven by using the steam obtained by the exhaust heat recovery steam generator. The solar assisted combined cycle power plant includes a solar collector to turn supplied water to warm water; a heat accumulator that stores pressurized hot water from the solar collector and the exhaust heat recovery steam generator; and a spray device that handles the pressurized hot water as spray water and sprays the spray water onto the air to be taken into the compressor. 1. A solar assisted combined cycle power plant having a compressor that pressurizes combustion air , a combustor that mixes and burns the combustion air and gas turbine fuel to generate a high-temperature combustion gas , a gas turbine that drives the compressor by using the combustion gas , an exhaust heat recovery steam generator that obtains steam from thermal energy of a gas exhausted from the gas turbine , and a steam turbine that is driven by using the steam obtained by the exhaust heat recovery steam generator , the solar assisted combined cycle power plant comprising:a solar collector that uses thermal energy of sunlight to turn supplied water to warm water;a heat accumulator that stores pressurized hot water derived from the solar collector and the exhaust heat recovery steam generator; anda spray device that handles the pressurized hot water, which is stored in the heat accumulator, as spray water and sprays the spray water onto the air to be taken into the compressor.2. A solar assisted combined cycle power plant having a compressor that pressurizes combustion ...

Combustion burner

A combustion burner 10 A according to one embodiment of the present invention includes: a fuel nozzle 110 ; a burner tube 120 forming the air passage 111 between the burner tube 120 and the fuel nozzle 110 ; swirler vanes (swirler vanes) 130 arranged in a plurality of positions in the circumferential direction on the external circumferential surface of the fuel nozzle 110 , each extending along the axial direction of the fuel nozzle 110 , and gradually curving from upstream toward downstream; and a liquid fuel injecting hole 133 A from which a liquid fuel is injected to a surface of each of the swirler vanes 130 . The combustion burner 10 A also includes multi-purpose injecting holes 11 - 1 to 11 - 3 as a cooling unit that cools a part of a vane pressure surface 132 a of the swirler vane 130 on which the liquid fuel LF hits. Water is injected through the multi-purpose injecting holes 11 - 1 to 11 - 3 to form a water film 15 A on the vane pressure surface 132 a , whereby a combustion temperature is reduced and formation of carbon deposit is prevented.

GAS TURBINE INLET FOGGING SYSTEM USING ELECTROHYDRODYNAMIC (EHD) ATOMIZATION

A gas turbine inlet fogging system using electrohydrodynamic (EHD) atomization is disclosed. In one embodiment, the inlet fogging system includes: a gas turbine system including an air inlet duct, and a plurality of electrohydrodynamic (EHD) nozzles coupled to a water supply, the plurality of EHD nozzles configured to provide a water-spray for reducing a temperature of inlet air drawn into the air inlet duct. In another embodiment, an inlet fogging system for a gas turbine system includes: a plurality of electrohydrodynamic (EHD) nozzles, and a water supply in fluid communication with the plurality of EHD nozzles. 1. An apparatus comprising:a gas turbine system including an air inlet duct; anda plurality of electrohydrodynamic (EHD) nozzles coupled to a water supply, the plurality of EHD nozzles configured to provide a water-spray for reducing a temperature of inlet air drawn into the air inlet duct.2. The apparatus of claim 1 , wherein the plurality of EHD nozzles are positioned one of:proximate the air inlet duct, orin series downstream of the air inlet duct.3. The apparatus of claim 1 , wherein water droplets of the water-spray provided by the plurality of EHD nozzles include a sauter mean diameter (SMD) in a range of about 1 to 5 micrometer.4. The apparatus of claim 1 , wherein each of the plurality of EHD nozzles further include:a capillary tube connected to an electric potential, the capillary tube in fluid communication with the water supply; anda counter-electric potential positioned substantially adjacent the capillary tube.5. The apparatus of claim 4 , wherein the capillary tube includes an electrically conductive material.6. The apparatus of claim 4 , further comprising a power source for providing distinct voltages to the capillary tube and at least one of:the counter-electric potential,an electrode positioned in series downstream of the capillary tube, ora compressor device of the gas turbine system.7. The apparatus of claim 1 , wherein the plurality of ...

Combined cycle power plant and method for operating such a combined cycle power plant

The invention relates to a combined cycle power plant including a gas turbine the exhaust gas outlet of which is connected to a heat recovery steam generator, which is part of a water/steam cycle, whereby, for having a large power reserve and at the same time a higher design performance when operated at base load, the gas turbine is designed with a steam injection capability for power augmentation. For having a large power reserve at improved and optimized design performance when the plant is being operated at base load, the gas turbine includes at least one combustor, and a compressor for providing cooling air for that gas turbine, which is extracted from the compressor and cooled down in at least one cooling air cooler. The steam for steam injection is generated in said cooling air cooler, whereby said steam is injected into an air side inlet or outlet of said cooling air cooler and/or directly into said at least one combustor. The heat recovery steam generator is equipped with a supplementary firing, which is at least a single stage supplementary firing to increase the high pressure steam production and providing augmentation power as power reserve to a grid when required.

SYSTEM AND METHOD FOR A WATER INJECTION SYSTEM

A system includes a compressor configured to compress a gaseous stream, an exhaust gas cooler configured to cool an exhaust gas from combustion with a cooling water, and a water injection system configured to inject the cooling water from the exhaust gas cooler into at least one of a compressor inlet of the compressor, a stage of the compressor, between stages of the compressor, or an inlet duct coupled to the compressor inlet of the compressor, or any combination thereof. 1. A system , comprising:a compressor configured to compress a gaseous stream;an exhaust gas cooler configured to cool an exhaust gas from combustion with a cooling water; anda water injection system configured to inject the cooling water from the exhaust gas cooler into at least one of a compressor inlet of the compressor, a stage of the compressor, between stages of the compressor, or an inlet duct coupled to the compressor inlet of the compressor, or any combination thereof.2. The system of claim 1 , comprising the inlet duct configured to convey the gaseous stream to the inlet of the compressor.3. The system of claim 1 , wherein the compressor comprises an oxidant compressor configured to compress an oxidant to produce a compressed oxidant.4. The system of claim 3 , comprising: a combustor section having one or more combustors configured to generate combustion products by combusting a fuel with the compressed oxidant, wherein the exhaust gas comprises the combustion products, and the exhaust gas cooler is configured to cool the combustion products; and', 'a turbine section having one or more turbine stages, wherein the one or more turbine stages are driven by the combustion products., 'a gas turbine engine, comprising5. The system of claim 4 , comprising an exhaust gas extraction system coupled to the gas turbine engine claim 4 , and a hydrocarbon production system coupled to the exhaust gas extraction system6. The system of claim 5 , wherein the gas turbine engine is a stoichiometric exhaust ...

Turbomachine system including an inlet bleed heat system and method of operating a turbomachine at part load

A turbomachine system includes a compressor portion having at least one compressor extraction, a turbine portion operatively connected to the compressor portion, and a combustor assembly including at least one combustor fluidically connected to the compressor portion and the turbine portion. A heat recovery steam generator (HRSG) is fluidically connected to the turbine portion, and an air inlet system is fluidically connected to the compressor portion. An inlet bleed heat (IBH) system is fluidically connected to each of the compressor portion, the air inlet system and the HRSG. An inlet bleed heat (IBH) system includes a first conduit having a first valve fluidically connecting the compressor extraction and the air inlet system, and a second conduit including a second valve connecting one of the HRSG and a secondary stream source with the first conduit.

Method and apparatus for increasing useful energy/thrust of a gas turbine engine by one or more rotating fluid moving (agitator) pieces due to formation of a defined steam region

A gas turbine engine comprising a housing coupled to an upstream source of hot gas and superheated water droplets, the housing having a centerline, an annular bay section positioned radially away from the centerline and protruding in an upstream direction, a rotatable shaft positioned along the centerline, a fluid mover coupled to the rotating shaft and positioned to receive the hot gas and superheated water droplets from the upstream source and to move the hot gas and superheated water droplets radially toward the annular bay section of the housing, a separator plate that is fixedly coupled to the housing; and an extractive turbine assembly positioned downstream from the separator plate and the annular bay section. The superheated water droplets mix thoroughly with the hot gas inside the annular bay section causing the water droplets to covert to steam, and the steam flows to the extractive turbine, increasing an efficiency of turbine rotation.

Method of increasing the safety of a power plant, and a power plant suitable for implementing the method

The present invention relates to a method of increasing the safety of a power plant provided with at least one heat engine and a gearbox (BTP), the engine driving the gearbox (BTP), the gearbox (BTP) having a lubrication system implemented using an aqueous medium stored in a reserve, in which method a fluid comprising water is injected into the heat engine to increase the power developed by the heat engine without increasing the temperature of a member of the heat engine or to decrease the temperature without modifying the power developed by the engine, the fluid being taken from the reserve.

SYSTEM AND METHOD FOR REDUCED TURBINE DEGRADATION BY CHEMICAL INJECTION

A gas turbine injection system having a gas turbine with an inlet section, a compressor section, at least one combustor in a combustion section, and a turbine section is disclosed. Air supply piping, water supply piping, and chemical reactant supply piping is in fluid communication with the injection system. A mixing chamber is in fluid communication with at least one of the water supply piping, air supply piping, and the chemical reactant supply piping to produce a chemical mixture. Chemical mixture supply piping is in fluid communication with the mixing chamber and at least one spray nozzle configured to selectively combine the chemical mixture with the air and inject an atomized chemical mixture into at least one section of the turbine. 1. A gas turbine injection system , comprising:a gas turbine having an inlet section, a compressor section, at least one combustor in a combustion section, and a turbine section;air supply piping in fluid communication with a supply of air and at least one spray nozzle;water supply piping in fluid communication with a supply of water;chemical reactant supply piping in fluid communication with the supply of a chemical reactant;a mixing chamber in fluid communication with the water supply piping and the chemical reactant supply piping, the mixing chamber configured to receive water from the water supply piping and the chemical reactant from the chemical reactant supply piping to produce a chemical mixture; andchemical mixture supply piping in fluid communication with the mixing chamber and the at least one spray nozzle, the at least one spray nozzle configured to selectively combine the chemical mixture with the air and inject an atomized chemical mixture into at least one section of the turbine.2. The injection system of claim 1 , further comprising a retractable manifold in fluid communication with at least one retractable spray nozzle claim 1 , the chemical mixture supply piping claim 1 , and the air supply piping.3. The ...

SYSTEMS AND METHODS FOR POWER PRODUCTION INCLUDING ION TRANSPORT COMPONENTS

The present disclosure relates to systems and methods for power production utilizing an ion transfer membrane (ITM) unit. An air stream and a fuel stream can be passed through the ITM unit so that the fuel is at least partially oxidized or combusted to form an outlet stream comprising CO. The COstream can be compressed and expanded to generate power. 1. A system for power production comprising:{'sub': '2', 'a power production turbine configured for expanding a working stream comprising recycled COto produce a turbine exhaust stream and to produce power;'}an oxygen-containing stream source configured to provide an oxygen-containing stream;a fuel source configured for input of a fuel into the turbine exhaust stream;{'sub': '2', 'an ion transport membrane system (ITM) configured for receiving the turbine exhaust stream with the input fuel and configured for receiving the oxygen-containing stream, the ITM being effective for diffusion of oxygen from the oxygen-containing stream into the turbine exhaust stream with the input fuel to at least partially combust at least a portion of the input fuel and to provide a heated CO-containing stream; and'}{'sub': 2', '2, 'a recuperator heat exchanger configured for transferring heat from the CO-containing stream to the working stream comprising the recycled CO.'}2. The system of claim 1 , further comprising a separator configured to receive the CO-containing stream from the recuperator heat exchanger and output a stream of substantially pure CO.3. The system of claim 2 , further comprising at least one compressor configured to compress at least a portion of the substantially pure COand provide the recycled CO.4. The system of claim 1 , further comprising at least one added heat source configured for adding heat to the working stream comprising the recycled COin addition to the heat transferred from the CO-containing stream.5. The system of claim 1 , further comprising one or both of an oxygen-containing stream pre-heater ...

Steam Micro Turbine Engine

A steam micro turbine engine is improved from a conventional micro turbine engine by evaporating water into steam in the exhaust heat exchanger, then injecting steam into combustion steam chamber after the fuel is completely burned. A steam micro turbine engine controller monitors the temperatures of the engine, adjusts fuel and water injection amount to maintain the optimal turbine exit temperature. The apparatus can reduce fuel consumption and emission by taking advantage of the waste heat and turning water into steam to generate extra useful work. This steam micro turbine engine could reach 60% efficiency instead of 30% in existing micro turbine engine. This engine can be used in household furnace electric co-generation systems, series hybrid electric vehicles and portable electric generators since its size is small with simplified components, relatively low operating temperature and much lower cost than traditional micro turbine engine. 1. A steam micro turbine engine , comprising:compressor motor means, combustion steam chamber means, turbine means, exhaust heat exchanger means, exhaust condenser means, water solenoid means, fuel solenoid means, steam injector means to inject steam into said combustion steam chamber means to generate super-heated steam as primary working fluid with more than 50% in mass of the exhaust gases; compressor means to inject compressed heated air into said combustion steam chamber means; fuel nozzle means for delivering fuel into said combustion steam chamber means; spark plug means to ignite air fuel mixture; steam vacuum pump means to create negative pressure in the said exhaust heat exchanger means and high pressure at the said steam injector means; a control unit to control said compressor motor means speed to maintain a constant rich air to fuel ratio, control said fuel solenoid means of fuel injection amount and control water solenoid means of water injection amount to maintain turbine exit temperature at less than 200 degrees ...

HUMID AIR TURBINE POWER, WATER EXTRACTION, AND REFRIGERATION CYCLE

Various embodiments relate to combined heat and power (CHP) systems. A CHP system can include a turbine system, a turbocharger system, and a refrigeration system. The refrigeration system can receive combustion products from the turbine system and compressed air from the turbocharger system. The refrigeration system can cool the combustion products and the compressed air to generate a cooled combustion product mixture that is provided to the turbine system. The turbine system can further comprise a fuel cell. This abstract is intended as a scanning tool for purposes of searching in the particular art and is not intended to be limiting of the present disclosure. 1. A combined heat and power (CHP) system , comprising:a turbine system comprising a high pressure compressor, a high pressure turbine, a combustor, and a recuperator, wherein the turbine system provides a combustion product stream;a turbocharger system comprising a low pressure compressor and a low pressure turbine, wherein the turbocharger system receives at least a portion of the combustion product stream from the turbine system and provides a compressed air stream; anda refrigeration system comprising a hot gas heat exchanger and a cold gas heat exchanger in fluid communication therewith, wherein the refrigeration system receives at least a portion of the combustion product stream from the turbine system and at least a portion of the compressed air stream from the turbocharger system;wherein the refrigeration system combines and cools the combustion product stream and the compressed air stream to generate a cooled combustion product mixture that is provided to the turbine system; andwherein the refrigeration system further generates steam that is provided to the turbine system.2. The CHP system of claim 1 , wherein the cooled combustion product mixture is provided to the high pressure compressor of the turbine system.3. The CHP system of claim 1 , wherein the steam from the refrigeration system is ...

Device for temporarily increasing turbomachine power

A device for temporarily increasing power in order to increase the power from at least one first turbine engine and from at least one second turbine engine, the device including a tank of coolant liquid, a first injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the first turbine engine, a second injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the second turbine engine, each of the first and second injection circuits including at least one first valve and at least one second valve arranged upstream from said at least one first valve, and a bridge pipe connecting together the first injection circuit and the second injection circuit upstream from their respective first valves and downstream from their respective second valves.

METHOD AND SYSTEM FOR GAS TURBINE POWER AUGMENTATION USING STEAM INJECTION

A method of augmenting power output by a gas turbine engine includes channeling fuel into the gas turbine engine at a predetermined fuel flow rate to generate a first power output. Steam is then injected into the gas turbine engine at a first steam flow rate, and a firing temperature bias is determined based at least on the first steam flow rate. The predetermined fuel flow rate is then adjusted based on the determined firing temperature bias such that the gas turbine engine generates a second power output greater than the first power output. 1. A method of augmenting power output by a gas turbine engine , said method comprising:channeling fuel into the gas turbine engine at a predetermined fuel flow rate to generate a first power output;injecting steam into the gas turbine engine at a first steam flow rate;determining a firing temperature bias based at least on the first steam flow rate; andadjusting the predetermined fuel flow rate based on the determined firing temperature bias such that the gas turbine engine generates a second power output greater than the first power output.2. The method in accordance with further comprising determining a second steam flow rate based at least on the first steam flow rate.3. The method in accordance with claim 2 , wherein determining a firing temperature bias further comprises determining the firing temperature bias based on the determined second steam flow rate.4. The method in accordance with further comprising measuring a temperature of air at a compressor inlet claim 2 , wherein the second steam flow rate is based on the measured compressor inlet air temperature and the first steam flow rate.5. The method in accordance with further comprising measuring a mass flow rate of air within the gas turbine engine claim 1 , wherein the first steam flow rate is based on the measured mass flow rate.6. The method in accordance with claim 1 , wherein adjusting the predetermined fuel flow rate based on the determined firing temperature ...

Systems and Methods for Wheel Space Temperature Management

The present application provides a gas turbine engine intended to be used in part in hot ambient conditions. The gas turbine engine may include a compressor, a turbine with a wheel space adjacent to a number of rotor wheels, and a wheel space water cooling system in communication with the wheel space to provide a flow of water thereto. 1. A gas turbine engine , comprising:a compressor;a turbine;the turbine comprising a wheel space adjacent to a plurality of rotor wheels; anda wheel space water cooling system in communication with the wheel space to provide a flow of water thereto.2. The gas turbine engine of claim 1 , wherein the compressor comprises a compressor discharge case with one or more bore holes therethrough.3. The gas turbine engine of claim 2 , wherein the wheel space water cooling system comprises a water line extending through one of the one or more bore holes in whole or in part.4. The gas turbine engine of claim 3 , wherein the water line comprises a concentric line.5. The gas turbine engine of claim 2 , wherein the one or more bore holes in the compressor discharge case are plugged to prevent a flow of air to the wheel space.6. The gas turbine engine of claim 3 , wherein the water line comprises a thermal barrier coating.7. The gas turbine engine of claim 1 , wherein the wheel space water cooling system comprises a source of water.8. The gas turbine engine of claim 1 , wherein the wheel space water cooling system comprises a pump.9. The gas turbine engine of claim 1 , wherein the wheel space cooling system comprises a discharge nozzle.10. The gas turbine engine of claim 9 , wherein the discharge nozzle comprises a counter-flow position claim 9 , a cross-flow position claim 9 , or an angled position.11. The gas turbine engine of claim 1 , wherein the flow of water comprises a flow of water in a liquid state and/or a flow of water in a gaseous state.12. The gas turbine engine of claim 11 , wherein the flow of water comprises the gaseous state during ...

NATURAL GAS LIQUEFACTION INSTALLATION ARRANGED AT THE SURFACE OF AN EXPANSE OF WATER, AND ASSOCIATED COOLING METHOD

The installation () comprises: —at least one air-cooled heat exchanger (), the air-cooled heat exchanger () comprising a tube bundle capable of accepting a flow () that is to be cooled, and a fan capable of causing a flow of air to circulate across the bundle of tubes; —a water spraying assembly (). The desalination assembly () comprises a salt water pickup () in the expanse of water (), the desalination assembly () being coupled downstream to the water-spraying assembly (). The water spraying assembly () comprises at least one spray nozzle opening into the bundle of tubes, the or each spray nozzle being directed towards the tubes of the tube bundle so as to spray liquid demineralised water coming from the desalination assembly () into contact with the tubes of the tube bundle. 1. A natural gas liquefaction installation , arranged at the surface of a body of water , comprising:at least one air-cooled heat exchanger, the at least one air-cooled heat exchanger including a tube bundle configured to receive a flow that is to be cooled, and a fan configured to cause a flow of air to circulate across the tube bundle;a water-sprayer;a desalinizer including a salt water pickup in the body of water, the desalinizer being coupled downstream to the water sprayer,the water-sprayer including at least one spray nozzle emerging in the tube bundle, the at least one spray nozzle being directed towards tubes of the tube bundle so as to spray liquid demineralized water coming from the desalinizer into contact with the tubes of the tube bundle.2. The installation according to claim 1 , wherein the tube bundle has several levels of tubes claim 1 , the water-sprayer including at least a first spray nozzle emerging across from the tubes of a first level of tubes and at least one second spray nozzle emerging across from tubes of a second level of tubes.3. The installation according to claim 2 , wherein the air-cooled heat exchanger includes an enclosure defining an inner circulation pipe ...

Systems for Supplying Liquid Fuel to a Combustion System, in Particular a Gas Turbine, including a Device for Generating an Emulsion and for Distributing the Emulsion Flow Rate

Liquid fuel supply system () for a combustion system (), in particular a gas turbine, including at least one storage tank () for liquid fuel supplying at least one injector () connected to a combustion chamber () of the combustion system (), said liquid fuel supply system () including a first piping section () disposed downstream of the tank () and a second piping section () disposed downstream of the first piping section () and upstream of fuel nozzle () in each combustion chamber (), said first piping section () including at least one pressurizing means (), and at least one injecting point or entering () for a water-soluble product, and the second piping section () including a mixing and distribution flow device () configured to create an emulsion and distributing the emulsion flow rate to at least one piping () connected to said nozzle (). 1. Liquid fuel supply system for a combustion system , comprising at least one storage tank for liquid fuel capable of supplying at least one nozzle connected to a combustion chamber of the combustion system , said liquid fuel supply system comprising a first piping section disposed downstream of the tank and a second piping section disposed downstream of the first piping section and upstream of said nozzle , said first piping section including at least one pressurizing means , and at least one point of injection or entry of a water-soluble product , wherein the second piping section comprises a device for mixing and distribution of flow and in that the flow regime upstream of said device is configured to create an emulsion and spread the emulsion flow to at least one piping connected to said nozzle.2. Liquid fuel supply system according to claim 1 , wherein the first piping section is configured to obtain at the inlet of mixing and flow distribution device a flow regime having a Reynolds number greater than or equal to 2000.3. Liquid fuel supply system according to claim 1 , wherein the first piping section is configured to ...

Gas turbine cycle equipment, equipment for recovering co2 from flue gas, and method for recovering exhaust heat from combustion flue gas

By using a combustion flue gas ( 18 ) from a power turbine ( 16 ), a high-pressure secondary compressed air ( 12 C) is subjected to heat exchange in a first heat exchange unit ( 19 A) of an exhaust heat recovery device ( 19 ), and by using resultant heat-exchanged flue gas ( 18 A), a low-pressure primary compressed air ( 12 A) is subjected to heat recovery in a second heat exchange unit ( 19 B) of a saturator ( 31 ). Then, a primary compressed air ( 12 B) that has been subjected to heat recovery in the second heat exchange unit ( 19 B) is introduced into a secondary air compressor ( 22 ) to increase the pressure of the air, and then the high-pressure air is subjected to heat recovery in the first heat exchange unit ( 19 A), producing a secondary compressed air ( 12 D). The secondary compressed air ( 12 D) is introduced into a combustor ( 14 ) and combusted using fuel.

Advanced Humid Air Gas Turbine System

One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. 1. An advanced humid air gas turbine system comprising:a gas turbine system that includesa compressor for compressing air,a compressed air header for mixing high-pressure air introduced from the compressor with steam to generate humidified combustion air,a combustor for mixing combustion air from the compressed air header with fuel for sake of combustion so as to generate combustion gas, anda turbine driven by the combustion gas that is generated by the combustor;a heat recovery steam generator for generating steam by use of exhaust gas from the turbine;a water recovery system disposed on a downstream side of the heat recovery steam generator, the water recovery system recovering moisture contained in the exhaust gas;a first steam system for supplying steam, coming from the heat recovery steam generator, to the compressed air header; anda second steam system for supplying steam, coming from the heat recovery steam generator, to the heat recovery steam generator or the water recovery system,wherein when the gas turbine system is starting up, shut down, or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the second steam system communicate with the heat recovery steam generator.2. The advanced humid air gas turbine system according to claim 1 ,wherein the second steam system is coupled to a steam nozzle for jetting steam into an exhaust gas passage of the heat recovery steam generator.3. The advanced humid air gas turbine system according to claim 1 ,wherein the heat recovery steam generator has a box-shaped casing, the casing having at a bottom portion thereof an ...

Turbine inlet air cooling systems with condensate water recovery

A method and system for enhancing power generated by a gas turbine system. The system may include a turbine inlet cooling system and a wet compression air fogging system. Air entering the gas turbine system is cooled by the turbine inlet cooling system and the wet compression air fogging system. The wet compression air fogging system may increase the mass flow rate of the air entering the gas turbine system at the compressor.

GAS TURBINE EFFICIENCY AND POWER AUGMENTATION IMPROVEMENTS UTILIZING HEATED COMPRESSED AIR AND STEAM INJECTION

The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include systems and methods for preheating piping of a power augmentation system and directing flows of hot compressed air, steam or a combination thereof into the gas turbine engine. 1. A power augmentation system for a gas turbine engine comprising:a gas turbine engine comprising a compressor coupled to a turbine by a shaft, the compressor and the turbine in fluid communication with one or more combustors through a compressor discharge case;a heat recovery steam generator in fluid communication with the gas turbine engine;steam injection piping connecting the gas turbine engine to the heat recovery steam generator, the steam injection piping further comprising a steam injection valve and an isolation valve; a fueled engine;', 'a multi-stage intercooled compressor coupled to the fueled engine;', 'a recuperator in fluid communication with the multi-stage intercooled compressor and the fueled engine;', 'wherein the recuperator heats air from the multi-stage intercooled compressor with exhaust heat from the fueled engine to produce hot compressed air; and,, 'an auxiliary air compression system comprisingan air vent and air vent valve in communication with the steam injection piping;wherein the steam injection valve, isolation valve, and air injection valve selectively permit a flow of steam from the heat recovery steam generator or air from the auxiliary air compression system, through the steam injection piping, and to the gas turbine engine.2. The power augmentation system of further comprising valving for selectively directing air from the compressor discharge case through the steam injection piping.3. The power augmentation system of claim 2 , wherein air from the compressor ...

APPLICATION OF PROBABILISTIC CONTROL IN LIQUID-FUELED GAS TURBINE TUNING, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value and an actual emissions value for each GT; adjusting at least one of a fuel flow or a water flow for each GT to an adjusted water/fuel ratio in response to the actual emissions value deviating from an emissions level associated with the base load level, while maintaining the respective adjusted output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition, while maintaining the adjusted water/fuel ratio. 1. A system comprising: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT;', 'commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value and an actual emissions value for each GT;', 'adjusting at least one of a fuel flow or a water flow for each GT to an adjusted water/fuel ratio in response to the actual emissions value deviating from an emissions level associated with the base load level, while maintaining the respective adjusted output; and', 'adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition, while maintaining the adjusted water/fuel ratio., 'at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including2. The system of claim 1 , ...

PURGING LIQUID FUEL NOZZLES AND SUPPLY TUBING WITH THE ASSISTANCE OF A FLOW DIVIDER

A fuel delivery system for a gas turbine engine that employs a technique for purging fuel delivery tubes in an effective manner. The fuel delivery system includes at least one multifunction valve that has a flow through position and a bi-directional purge position. The fuel delivery system also includes at least one flow divider that is positioned downstream from the multifunction valve and divides the flow of fuel from the valve into a number of the fuel delivery tubes, where a separate fuel delivery tube is provided for each combustor in the engine. The flow divider includes a pump element for all of the fuel delivery tubes that can operate in a forward and a reverse direction. Purge water provided downstream from the flow divider for each of the fuel delivery tubes can be pumped by the flow divider when the multifunction valve is in the purge position. 1. A fuel delivery system for providing fuel to a plurality of combustors in a gas turbine engine , said fuel delivery system comprising:a fuel line receiving a liquid fuel;at least one control valve provided along the fuel line and controlling the flow of the fuel therethrough;at least one multifunction valve provided along the fuel line downstream from the control valve and including a flow-through position, a drain position and a purge position;at least one flow divider provided along the fuel line downstream from the multifunction valve, said flow divider directing the fuel in the flow line into a plurality of flow delivery tubes where a separate one of the flow tubes is coupled to a separate one of the combustors, said at least one flow divider including a separate pump element for each flow tube that is controlled to allow flow in both a forward direction and a reverse direction;a separate water injection line coupled to each of the flow tubes downstream from the at least one flow divider; anda drain coupled to the at least one multifunction valve, wherein water injected at a certain pressure into the flow ...

Two-Shaft Gas Turbine Having Steam Injection Mechanism

A two-shaft gas turbine having a steam injection mechanism, comprising: a compressor having an inlet guide vane, a combustor, turbines, a heat recovery steam generator, a steam valve to control a flow rate of steam to be supplied to the combustor, a fuel valve to control a flow rate of fuel to be supplied to the combustor, characterized in that, the two-shaft gas turbine further comprising: a rotational frequency meter, a flow rate meter to measure the flow rate of the steam to be supplied to the combustor from the heat recovery steam generator, an inlet guide vane position gauge provided to the compressor, a steam valve position gauge, and a control system calculates and outputs command signals to operate openings of the fuel valve, the steam valve, and the inlet guide vane based on measurement signals obtained by the rotational frequency meter, the inlet guide vane position gauge, or the steam valve position gauge, and an output increase command value to the gas turbine. 1. A two-shaft gas turbine having a steam injection mechanism , comprising: a compressor having an inlet guide vane to control a flow rate of air to be introduced ,a combustor to mix the air compressed by the compressor with fuel and combust the air with the fuel to generate a combustion gas,a turbine having a high pressure turbine driven by the combustion gas generated in the combustor and a low pressure turbine disposed on a downstream side of the high pressure turbine,a heat recovery steam generator to generate steam using an exhaust gas discharged from the low pressure turbine as a heat source,a steam system to supply the combustor with the steam generated by the heat recovery steam generator,a fuel valve provided to a fuel system to supply the combustor with the fuel and control a flow rate of the fuel to be supplied to the combustor,a steam valve provided to the steam system and control a flow rate of the steam to be supplied from the heat recovery steam generator to the combustor through ...

Advanced Humid Air Gas Turbine System

One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. The gas turbine system includes a compressor, the compressed air header for generating humidified combustion air, a combustor for generating combustion gas, and the turbine. When the gas turbine system is starting up, shut down or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the second steam system communicate with the heat recovery steam generator. 1. An advanced humid air gas turbine system comprising:a gas turbine system that includesa compressor for compressing air,a compressed air header for mixing high-pressure air introduced from the compressor with steam to generate humidified combustion air,a combustor for mixing combustion air from the compressed air header with fuel for sake of combustion so as to generate combustion gas, anda turbine driven by the combustion gas that is generated by the combustor;a heat recovery steam generator for generating steam by use of exhaust gas from the turbine;a water recovery system disposed on a downstream side of the heat recovery steam generator, the water recovery system recovering moisture contained in the exhaust gas;a first steam system for supplying steam, coming from the heat recovery steam generator, to the compressed air header;a second steam system for supplying steam, coming from the heat recovery steam generator, to the heat recovery steam generator or the water recovery system; anda steam nozzle;wherein when the gas turbine system is starting up, shut down, or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the ...

TURBINE ENGINE ASSEMBLY AND METHOD OF OPERATING

A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture formed at least partially from a primary fuel including methane. The assembly also includes a fuel reformer configured to produce a secondary fuel, wherein the fuel reformer is further configured to channel a flow of secondary fuel towards the rotating detonation combustor such that the fuel-air mixture further includes the secondary fuel. 1. A turbine engine assembly comprising:a rotating detonation combustor configured to combust a fuel-air mixture formed at least partially from a primary fuel comprising methane; anda fuel reformer configured to produce a secondary fuel, wherein said fuel reformer is further configured to channel a flow of the secondary fuel towards said rotating detonation combustor such that the fuel-air mixture further comprises the secondary fuel.2. The turbine engine assembly in accordance with further comprising a flow controller coupled between said rotating detonation combustor and said fuel reformer claim 1 , said flow controller configured to regulate the flow of the secondary fuel channeled towards said rotating detonation combustor based on an operating condition of the turbine engine assembly.3. The turbine engine assembly in accordance with claim 2 , wherein said flow controller is further configured to channel the flow of the secondary fuel towards said rotating detonation combustor at least one of during startup of said turbine engine assembly claim 2 , or as a rotational speed of said turbine engine assembly increases towards a steady state operating condition.4. The turbine engine assembly in accordance with claim 3 , wherein said flow controller is further configured to progressively reduce an amount of the secondary fuel channeled towards said rotating detonation combustor as the rotational speed of said turbine engine assembly increases towards the steady state operating condition.5. The turbine engine assembly in ...

GAS TURBINE ENGINE AND METHODS OF OPERATING SAME

A gas turbine engine that includes an inlet volume flow control appliance and methods of operating the same are provided. The method includes operating the gas turbine engine with the inlet volume flow control appliance supplying a compressor inlet volume flow that is below a maximum compressor inlet volume flow. A mass flow of a liquid agent is added to a compressor gas mass flow while the gas turbine engine is operated with a compressor inlet volume flow below a maximum compressor inlet volume flow. The mass flow of a liquid agent may be controlled as a function of the pitch of variable inlet guide vanes. The method further comprises adjusting the volume flow control appliance to increase the compressor inlet volume flow and increasing the mass flow of liquid agent added to the compressor gas mass flow while the inlet volume flow control appliance increases the compressor inlet volume. 1. A method for operating a gas turbine engine , the gas turbine engine including an inlet volume flow control appliance suitable to control a compressor gas mass flow , said method comprising:operating the gas turbine engine with the inlet volume flow control appliance set to operate the gas turbine engine with a compressor inlet volume flow below a maximum compressor inlet volume flow;{'sub': 'Liq', 'adding a mass flow ({dot over (m)}) of a liquid agent to a compressor gas mass flow while the inlet volume flow control appliance is set to operate the gas turbine engine with a compressor inlet volume flow below the maximum compressor inlet volume flow;'}adjusting the inlet volume flow control appliance to change the compressor inlet volume flow; andcontrolling the mass flow of liquid agent at least during a part of the process of adjusting the volume flow control appliance, wherein controlling the mass flow of liquid agent comprises at least one of increasing the mass flow of liquid agent added to the compressor gas mass flow when the inlet volume flow control appliance is adjusted ...

GAS TURBINE EFFICIENCY AND POWER AUGMENTATION IMPROVEMENTS UTILIZING HEATED COMPRESSED AIR

The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include systems and methods for preheating a steam injection system. 1. A system for preheating a power augmentation system of a power plant comprising:a gas turbine engine comprising a compressor coupled to a turbine by a shaft, the compressor and the turbine in fluid communication with one or more combustors;a heat recovery steam generator;steam injection piping connecting the gas turbine engine to the heat recovery steam generator, the steam injection piping comprising a steam injection valve and an isolation valve; and,an air vent and an air vent valve in communication with the steam injection piping;wherein the isolation valve and air vent valve are configured to selectively permit flow of air from the compressor, through the steam injection piping, and to the air vent, thereby preheating the steam injection piping.2. The system of further comprising a compressor discharge plenum for receiving compressed air from the compressor and with which one or more combustors are in fluid communication.3. The system of claim 2 , wherein the flow of air is taken from the compressor discharge plenum.4. The system of claim 1 , wherein the heat recovery steam generator utilizes heated exhaust from the gas turbine engine for the production of steam.5. The system of claim 1 , wherein the steam injection valve controls flow of steam from the heat recovery steam generator and to the steam injection piping.6. The system of claim 1 , wherein the isolation valve controls a flow of steam to the gas turbine engine and a flow of compressed air from the gas turbine engine.7. The system of claim 1 , wherein steam produced by the heat recovery steam generator is used in part by an external process.8. A ...

Systems and methods for increasing power output in a waste heat driven air brayton cycle turbocharger system

Various systems and methods are provided for a turbocharger system. In one example, a system for use with a power generator having a rotary machine including a combustor comprises: a heat exchanger positioned to receive exhaust gases from the combustor; and a turbocharger system, comprising: a low pressure compressor fluidly coupled to the heat exchanger and adapted to supply gases to the heat exchanger; a low pressure turbine and a high pressure turbine each fluidly coupled to the heat exchanger and adapted to receive gases from the heat exchanger; a high pressure compressor fluidly coupled to the rotary machine and the low pressure compressor, adapted to receive gases from the low pressure compressor and supply compressed air to the rotary machine; and a water injector adapted to inject water into a flow path between the low pressure compressor and the heat exchanger.

GAS TURBINE

A gas turbine () of the present invention is a gas turbine which uses a hydrogen gas as a fuel, and comprises a combustor () which includes a fuel injection nozzle (), and has a combustion chamber () in an interior of the combustor; a steam supply unit () which supplies steam to the combustor () to decrease a combustion temperature; and an air drier () which removes the steam from air to be supplied to the combustor () to dry the air. 1. A gas turbine which uses a hydrogen gas as a fuel , the gas turbine comprising:a combustor which includes a fuel injection nozzle, and has a combustion chamber in an interior of the combustor;a steam supply unit which supplies steam to the combustor to decrease a combustion temperature; andan air drier which removes the steam from air to be supplied to the combustor to dry the air.2. The gas turbine according to claim 1 ,wherein the air drier includes a heat exchange section which takes heat from the air to be supplied to the combustor by heat exchange with the hydrogen gas to cool the air, and condenses the steam contained in the air to remove the steam.3. The gas turbine according to claim 2 ,wherein the steam supply unit includes a steam generator which heats water supplied to the steam supply unit to generate the steam to be supplied to the combustor, andwherein at least a part of the water to be supplied to the steam supply unit is condensed water generated from the air having been cooled by the heat exchange with the hydrogen gas in the heat exchange section. The present invention relates to a gas turbine which uses a hydrogen gas as a fuel.A gas turbine which uses a hydrogen gas as a fuel has an advantage that carbon dioxide or carbon monoxide resulting from combustion is not discharged and an exhaust gas is clean. (see Patent Literature 1).Patent Literature 1: Japanese Translation of PCT Application Publication No. 2010-535303In the gas turbine which uses the hydrogen gas as the fuel, water is generated through a chemical ...

Hybrid Propulsion System

An aeronautical propulsion system including a turbine engine having a fan and an electric motor drivingly coupled to at least one of the fan or the turbine engine. The aeronautical propulsion system additionally includes a fuel cell for providing electrical energy to the electric motor, the fuel cell generating water as a byproduct. The aeronautical portion system directs the water generated by the fuel cell to the turbine engine during operation to improve an efficiency of the aeronautical propulsion system. 1. A gas turbine engine comprising:a core turbine engine;a fan mechanically coupled to the core turbine engine;an electric motor mechanically coupled to at least one of the core turbine engine and the fan; anda fuel cell for providing electrical energy to the electric motor, the fuel cell generating water as a byproduct, the gas turbine engine directing the water generated by the fuel cell to the core turbine engine during operation of the gas turbine engine to improve an efficiency of the gas turbine engine.2. The gas turbine engine of claim 1 , wherein the gas turbine engine directs the water generated by the fuel cell to the core turbine engine for intercooling the core turbine engine.3. The gas turbine engine of claim 1 , wherein the core turbine engine includes a compressor section claim 1 , wherein the compressor section of the core turbine engine includes a first compressor and a second compressor located downstream of the first compressor claim 1 , and wherein the gas turbine engine directs the water generated by the fuel cell to a location between the first and second compressors.4. The gas turbine engine of claim 1 , wherein the core turbine engine includes a compressor section and a turbine section claim 1 , wherein the gas turbine engine provides the turbine section with cooling air from the compressor section claim 1 , and wherein the gas turbine engine directs the water generated by the fuel cell to the cooling air from the compressor section.5. ...

HIGH SPEED PROPULSION SYSTEM WITH INLET COOLING

A cooling system for a turbine engine including a heat exchanger in fluid communication with a first fluid inlet stream and disposed upstream and in fluid communication with a core engine. The heat exchanger operative to cool the first fluid inlet stream. The heat exchanger including a heat exchanger inlet for input of a heat exchanging medium for exchange of heat from the first fluid inlet stream to the heat exchanging medium. The heat exchanger further including a heat exchanger outlet for discharge of a heated output stream into one of a turbine of a downstream engine, an augmentor or a combustor of the core engine. The heated output stream provides an additional flow to the downstream engine. A turbine engine including the cooling system is disclosed. 1. A turbine engine including a cooling system , the turbine engine comprising:a core engine configured to receive a first fluid stream and discharge an exhaust flow stream;a bypass flow turbomachine disposed to receive a second fluid stream and the exhaust flow stream from the core engine and discharge a secondary exhaust flow stream, the bypass flow turbomachine including an augmentor; and a heat exchanger inlet for receiving a heat exchanging medium for exchange of heat from the first fluid stream to the heat exchanging medium; and', 'a heat exchanger outlet for discharging a heated output stream, wherein the heated output stream provides an additional flow into the bypass flow turbomachine., 'an inlet heat exchanger in fluid communication with the first fluid stream and disposed upstream and in fluid communication with the core engine, the inlet heat exchanger operative to cool the first fluid stream, the inlet heat exchanger comprising2. The turbine engine of claim 1 , further comprisinga core engine isolator; anda bypass flow turbomachine isolator, wherein an incoming fluid stream is split into the first fluid stream flowing through the core engine isolator and the second fluid stream flowing through the ...

A METHOD FOR OPERATING A GAS TURBINE

The gas turbine comprises a compressor, a combustor, and a turbine. The method comprises: compressing air with the compressor and feeding compressed air continuously to the combustor, feeding fuel to the combustor, continuously firing the mixture of fuel and gas in the combustor, feeding combustion gases from the combustor to the turbine, and supplying at least a portion of the total amount of fuel that is supplied to the combustor intermittently. 1. A method for operating a gas turbine comprising a compressor , a combustor , and a turbine , the method comprising:compressing air with the compressor and feeding compressed air continuously to the combustor,supplying fuel to the combustor,continuously firing the mixture of fuel and gas in the combustor,feeding combustion gases from the combustor to the turbine,supplying at least a portion of the total amount of fuel that is supplied to the combustor intermittently to the combustor,characterized bysupplying steam intermittently to the combustor.2. The method according to claim 1 , characterized by supplying a first portion of fuel continuously to the combustor and supplying a second portion of fuel intermittently to the combustor.3. The method according to claim 1 , characterized by supplying a first portion of fuel continuously directly to the combustor and supplying a second portion of fuel intermittently directly to the combustor.4. The method according to claim 1 , characterized by supplying a first portion of fuel continuously from a first fuel inlet to the combustor and supplying a second portion of fuel intermittently from a second fuel inlet to the combustor.5. The method according to claim 1 , characterized by supplying a first portion of fuel continuously from a first fuel inlet directly to the combustor and supplying a second portion of fuel intermittently from a second fuel inlet directly to the combustor.6. The method according to claim 2 , characterized by supplying the second portion fuel to the combustor ...

SYSTEMS AND METHODS FOR POWER PRODUCTION INCLUDING ION TRANSPORT COMPONENTS

The present disclosure relates to systems and methods for power production utilizing an ion transfer membrane (ITM) unit. An air stream and a fuel stream can be passed through the ITM unit so that the fuel is at least partially oxidized or combusted to form an outlet stream comprising CO. The COstream can be compressed and expanded to generate power. 1. A system for power production comprising:a power production turbine;an oxygen-containing stream source configured to provide an oxygen-containing stream;a fuel source configure to provide a fuel stream;{'sub': '2', 'an ion transport membrane system (ITM) configured for receiving the oxygen-containing stream and configured for receiving the fuel stream, the ITM being effective for diffusion of oxygen from the oxygen-containing stream into the fuel stream to at least partially combust at least a portion of the fuel stream and to provide a heated CO-containing stream.'}2. The system of claim 1 , further comprising a recuperator heat exchanger configured for withdrawing heat from the heated CO-containing stream to form a cooled CO-containing stream.3. The system of claim 2 , further comprising a compressor configured for compressing at least a portion of cooled CO-containing stream to form a compressed stream of CO.4. The system of claim 3 , wherein the recuperator heat exchanger is configured for transferring at least a portion of the heat withdrawn from the heated CO-containing stream to the compressed stream of CO.5. The system of claim 1 , wherein the oxygen-containing stream source is air.6. The system of claim 1 , wherein the oxygen-containing stream source is an exhaust stream from a gas turbine.7. The system of claim 1 , wherein the ITM comprises a diffusion membrane that is in the form of a tube claim 1 , the diffusion membrane having an outer surface configured for contacting the oxygen-containing stream and an inner surface configured for contacting the fuel stream.8. The system of claim 7 , wherein one or ...

Gas Turbine Combustor and Steam Injected Gas Turbine

A gas turbine combustor includes a tubular combustion liner that has a plurality of dilution holes disposed circumferentially at a section downstream in a direction of flow of combustion gas, a combustor casing that encloses the combustion liner, a liner flow sleeve disposed between the combustion liner and the combustor casing, to define with the combustion liner an air flow path through which compressed air flows, the liner flow sleeve having a plurality of steam injection holes, and a steam distribution mechanism disposed on an outer peripheral side of the liner flow sleeve. The steam distribution mechanism distributes received injection steam to the steam injection holes. At least some of the steam injection holes are disposed so to face at least some of the dilution holes. The steam injection holes facing the respective dilution holes are each formed so as to spurt the injection steam toward the corresponding dilution hole.

METHOD OF INCREASING THE SAFETY OF A POWER PLANT, AND A POWER PLANT SUITABLE FOR IMPLEMENTING THE METHOD

The present invention relates to a method of increasing the safety of a power plant provided with at least one heat engine and a gearbox (BTP), the engine driving the gearbox (BTP), the gearbox (BTP) having a lubrication system implemented using an aqueous medium stored in a reserve, in which method a fluid comprising water is injected into the heat engine to increase the power developed by the heat engine without increasing the temperature of a member of the heat engine or to decrease the temperature without modifying the power developed by the engine, the fluid being taken from the reserve. 1. A power plant provided with at least one heat engine and with a gearbox and a reserve , the heat engine driving the gearbox , wherein the reserve is hydraulically connected via a hydraulic connection to the gearbox and to each heat engine to lubricate the gearbox and to increase the power of the heat engine without increasing its temperature or to reduce the temperature of the heat engine without reducing its power , the power plant including at least one main closure means between each heat engine and the reserve , and at least one secondary closure means between the gearbox and the reserve , the power plant including a control member for controlling the main and secondary closure means.2. A power plant according to claim 1 , wherein each main closure means comprises a main admission valve claim 1 , and each secondary closure means comprises a secondary admission valve.3. A power plant according to claim 1 , wherein claim 1 , for the gearbox including at least one member to be lubricated claim 1 , the hydraulic connection includes a duct opening out into an injection nozzle directed towards the member claim 1 , the nozzle being suitable for injecting a fluid from the reserve in the form of a jet or a mist.4. A power plant according to claim 1 , wherein for the heat engine being a turbine engine having a free turbine and a gas generator claim 1 , and for the gas generator ...

GAS TURBINE PLANT

A gas turbine plant includes a connection line configured to connect an outlet of a compressor high-pressure stage and an inlet of a turbine via a combustor, a bypass line configured to cause some or all of air compressed at a compressor low-pressure stage to bypass the compressor high-pressure stage and to be supplied to the connection line, and an adjustment device configured to adjust a flow rate of the air flowing through the bypass line. A plurality of types of fluid are supplied to the connection line in addition to the air compressed by the compressor, and during operation of the gas turbine plant, supply of at least one type of fluid of the plurality of types of fluid to the connection line is stopped according to an operating state of the gas turbine plant. 1. A gas turbine plant comprising:a compressor including a compressor low-pressure stage for compressing air, and a compressor high-pressure stage for further compressing the air compressed at the compressor low-pressure stage;a combustor configured to mix and combust the air compressed by the compressor and fuel;a turbine configured to be driven by combustion gas generated in the combustor;a connection line configured to connect an outlet of the compressor high-pressure stage and an inlet of the turbine via the combustor;a bypass line configured to cause some or all of the air compressed at the compressor low-pressure stage to bypass the compressor high-pressure stage and to be supplied to the connection line; andan adjustment device configured to adjust a flow rate of the air flowing through the bypass line, whereina plurality of types of fluid are supplied to the connection line in addition to the air compressed by the compressor, andduring operation of the gas turbine plant, supply of at least one type of fluid of the plurality of types of fluid to the connection line is stopped according to an operating state of the gas turbine plant.2. The gas turbine plant according to claim 1 , whereinwhen the ...

COMBUSTOR AND GAS TURBINE

A combustor having a plurality of nozzles (main nozzles) to supply fuel disposed, includes a water supplier that is connected to all or part of the plurality of nozzles to supply water to each of fuel pipes, wherein the water supplier varies a supply amount of water for each of the nozzles to which the water is supplied. 1. A combustor having a plurality of nozzles to supply fuel disposed , the combustor comprising:a water supplier that is connected to all or part of the plurality of nozzles to supply water to each of fuel pipes,wherein the water supplier varies a supply amount of water for each of the nozzles to which the water is supplied.2. The combustor according to claim 1 , wherein the nozzles are main nozzles disposed around a pilot nozzle in the circumferential direction.3. The combustor according to claim 1 , wherein the water supplier comprises:a variable water supply unit that varies the supply amount of water; anda control unit that previously stores water supply information in which the supply amount of water depending on an operating condition of the combustor is set, and controls the variable water supply unit on the basis of the operating condition of the combustor and the water supply information.4. A gas turbine comprising the combustor according to .5. The combustor according to claim 2 , wherein the water supplier comprises:a variable water supply unit that varies the supply amount of water; anda control unit that previously stores water supply information in which the supply amount of water depending on an operating condition of the combustor is set, and controls the variable water supply unit on the basis of the operating condition of the combustor and the water supply information.6. A gas turbine comprising the combustor according to .7. A gas turbine comprising the combustor according to .8. The combustor according to claim 2 , wherein the plurality of the main nozzles alternately makes the supply amount of water different from each other.9. ...

GAS TURBINE HOT AIR INJECTION POWER AUGMENTATION UTILIZING COMPRESSED STORED AIR

Gas turbine power plants augmented with an air injection system for hot air injection to augment power and are used to drive sensitive cogeneration processes are fitted with compressed air storage capability to more smoothly ramp on air injection in the event of sudden and unexpected interruption of the air injection system. Utilizing stored hot air injection prior to starting an air injection system significantly reduces the start-up time of the air injection system. 1. A method of reducing start time of an auxiliary air injection system on a gas turbine engine , the method comprising:operating a gas turbine engine having a compressor, a compressor discharge plenum, a combustor, and a turbine;compressing air with an auxiliary air compressor to a pressure higher than that of the compressor discharge plenum;storing the compressed air of the auxiliary air compressor in a storage tank;heating the stored compressed air in the storage tank to form hot compressed air in the storage tank; andinjecting the hot compressed air from the storage tank at a flow rate into the gas turbine engine sufficient to increase the power output of a gas turbine power plant, for a period of time; and,reducing the flow of the hot compressed air from the storage tank while simultaneously increasing a flow of hot compressed air being generated by an auxiliary air injection system.2. The method according to claim 1 , wherein the flow of the hot compressed air from the storage tank is reduced and the compressed air from the air injection system is increased in such a way to deliver a constant mass flow of compressed air from a combination of the storage tank and the air injection system to the gas turbine engine.3. The method according to claim 1 , wherein a rate of the hot compressed air initially flowing from the storage tank is at approximately a rate of the compressed air being delivered from the auxiliary air compressor.4. The method according to claim 1 , wherein the storage tank is heated ...

Advanced Humid Air Turbine System and Exhaust Gas Treatment System

An exhaust gas treatment system for an advanced humid air turbine system includes: an exhaust gas flow path through which an exhaust gas discharged from a gas turbine system flows; a water recovery unit that is connected to the exhaust gas flow path and that cools the exhaust gas that flows in from the exhaust gas flow path to recover water content contained in the exhaust gas; and a bypass flow path through which part of the exhaust gas from the exhaust gas flow path flows so as to avoid cooling in the water recovery unit. The bypass flow path has a downstream end disposed at a position downstream in a flow direction of the exhaust gas with respect to a zone in which the exhaust gas is cooled in the water recovery unit. 1. An exhaust gas treatment system for an advanced humid air turbine system , the exhaust gas treatment system treating water content contained in an exhaust gas discharged from a gas turbine system in which a working fluid is humidified , comprising:an exhaust gas flow path through which the exhaust gas discharged from the gas turbine system flows;a water recovery unit connected to the exhaust gas flow path, the water recovery unit being configured to cool an exhaust gas that flows in from the exhaust gas flow path by a refrigerant to thereby recover water content contained in the exhaust gas; andat least one bypass flow path through which part of the exhaust gas from the exhaust gas flow path flows so as to avoid cooling by the refrigerant in the water recovery unit, the at least one bypass flow path having a downstream end disposed at a position downstream in a flow direction of the exhaust gas with respect to a zone in which the exhaust gas is cooled in the water recovery unit.2. The exhaust gas treatment system for an advanced humid air turbine system according to claim 1 , wherein the at least one bypass flow path comprises a bypass line having an upstream side connected to the exhaust gas flow path and a downstream side connected to the water ...

Turbine for use with at least two working fluids

The present invention is related to a multiple-inlet turbine casing (16) for a turbine rotor (60) which comprises a first fluid supply channel (70) configured to direct a first working fluid onto the turbine rotor (60) and a second fluid supply channel (74) configured to direct a second working fluid to impart torque on the turbine rotor (60) in the same direction as the direction in which torque is imparted on the turbine rotor (60) by the first working fluid. The first working fluid is an exhaust gas from an internal combustion engine and the second fluid may be steam and the turbine may be an inverted-Brayton-cycle turbine for recovery of waste energy from the exhaust gas of said internal combustion engine. Thus, the number of turbine rotors is reduced in comparison to a system comprising a single turbine for each distinct working fluid.

MULTI-ENGINE POWER PLANT HAVING AN EMERGENCY FLUID INJECTION SYSTEM, AND AN AIRCRAFT

A power plant () having a first and second turboshaft engines () and an emergency system () for injecting fluid into said engines (). First and second pressurization pipes () connect a tank () to each gas generator of the engines. In addition, the system () includes an injector device () for each engine, which device comprises an injector pipe () connecting said tank () to at least one injector nozzle (). A distributor () is arranged on each injector pipe (), each valve () feeding one of the engines while being connected to the gas generator of the other engine. 1. A power plant having a first turboshaft engine and a second turboshaft engine each having a gas generator , said power plant including an emergency system for injecting fluid into said engines , said system including a tank containing an aqueous fluid , wherein the power plant includes:a first pressurization pipe and a second pressurization pipe respectively connecting the tank to a first gas generator of the first engine and to a second gas generator of the second engine in order to pressurize said fluid in said tank with gas taken from each of the gas generators;one injector member per engine, each member comprising at least an injector nozzle for injecting said fluid, a first injector device having a first injector pipe connecting said tank to a first injector member of the first engine, a second injector device having a second injector pipe connecting said tank to a second injector member of the second engine; anda distributor arranged on each injector pipe, a first distributor of the first injector pipe communicating with the second pressurization pipe so that a failure of the second engine causes the first distributor to open, and a second distributor of the second injector pipe communicating with the first pressurization pipe so that the failure of the first engine causes the second distributor to open.2. A power plant according to claim 1 , wherein said tank includes an overpressure valve for ...

DEVICE AND METHOD FOR TEMPORARILY INCREASING POWER

A device and a method of temporarily increasing power of at least a first turbine engine is disclosed. The device includes a coolant liquid tank and a first injection circuit connected to the tank and leading to at least one injection nozzle suitable for being installed upstream from at least one compressor stage of the first turbine engine. This first injection circuit includes at least a first flow valve configured to open when a pressure exceeds a predetermined threshold compared with a downstream pressure from at least one compressor stage of a second turbine engine so as to enable the coolant liquid to flow towards the injection nozzle of the first injection circuit. 1. A device for temporarily increasing the power of at least a first turbine engine , the device comprising:a tank of coolant liquid; anda first injection circuit connected to said tank and leading to at least one injection nozzle suitable for being installed upstream from at least one compressor stage of the first turbine engine;wherein the first injection circuit includes at least a first flow valve configured to open when pressure upstream from said first flow valve exceeds downstream pressure from at least one compressor stage of a second turbine engine by an amount greater than a predetermined threshold, so as to allow the coolant liquid to flow towards said injection nozzle of the first injection circuit, and wherein said device further includes at least one pressurization circuit suitable for being connected to at least one compressor stage of the first turbine engine for pressurizing said tank and including a check valve to avoid depressurizing the tank.2. The device according to claim 1 , further including a second injection circuit connected to said tank claim 1 , leading to at least one injection nozzle claim 1 , and including at least one flow valve configured to open when pressure exceeds a predetermined threshold relative to a downstream pressure from at least one compressor stage ...

METHOD AND APPARATUS FOR INCREASING USEFUL ENERGY/THRUST OF A GAS TURBINE ENGINE BY ONE OR MORE ROTATING FLUID MOVING (AGITATOR) PIECES DUE TO FORMATION OF A DEFINED STEAM REGION

A system for increasing useful energy output includes a source of hot combustion gas, such as from a gas turbine engine, and an apparatus that is disposed downstream of and receives the hot combustion gas and acts thereon to optimize electricity/thrust energy output of the system. The apparatus includes a housing that is coupled to the source and receives the hot combustion gas and also includes a rotatable shaft centrally disposed within the housing. A rotatable fluid moving device is coupled to the rotatable shaft and is configured such that the rotatable fluid moving device moves the hot combustion gas into a shape within the housing such that useful energy output/thrust is increased. Optionally, the system includes a spray nozzle that discharges water droplets upstream of the rotatable fluid moving device in a high temperature environment such that the action of the rotatable fluid moving device generates water vapor (steam) having a particular profile (e.g., annular shaped). 1. A gas turbine engine that includes a compressor and a combustion chamber that generates hot thrust gas , the gas turbine engine comprising:a first housing section;a first rotatable shaft disposed within the first housing section;a turbine blade assembly that is downstream of the combustion chamber and is rotatable with the first rotatable shaft within the first housing section, the turbine blade assembly including a plurality of turbine blades; and a second housing section that is coupled to and in fluid communication with the first housing section for receiving the hot trust gas from the turbine blade assembly;', 'a second rotatable shaft centrally disposed within the unit housing;', 'a rotatable fluid moving device that is coupled to the second rotatable shaft and configured such that the rotatable fluid moving device acts on the hot thrust gas from the turbine blade assembly and directs the hot thrust gas in a radially outward direction to cause the hot trust gas to assume a ...

Gas turbine plant with improved flexibility

A gas turbine plant includes a gas turbine having a compressor, a combustion chamber and an expander; and a water-steam circuit which is thermally connected to the gas turbine such that during the operation of the gas turbine, waste gas drawn off therefrom transfers heat to the water-steam circuit in order to generate steam. The water-steam circuit is further thermally connected to a heat accumulator which in turn is thermally connected to a container for storing water. The container is fluidically coupled to the gas turbine such that water can be supplied from the container to the gas turbine during the operation of the latter in order to increase output. A flash valve is connected between the container and the gas turbine, the valve being designed to reduce the pressure of the water taken from the container to a lower pressure level.

METHOD FOR INCREASING THE POWER OF A COMBINED-CYCLE POWER PLANT, AND COMBINED-CYCLE POWER PLANT FOR CONDUCTING SAID METHOD

The invention relates to a method for temporary increasing the power of a gas turbine, which is part of a combined-cycle power plant, wherein the exhaust gas of the gas turbine is used in a heat recovery steam generator to generate steam for a water/steam cycle including a steam turbine with a high pressure steam turbine, an intermediate pressure steam turbine and a low pressure steam turbine, whereby the method comprises the step of injecting steam from the water/steam cycle at a predetermined injection pressure into the gas turbine. The efficiency is improved by taking steam of a lower pressure than the predetermined injection pressure from the water/steam cycle, increasing the pressure of the steam taken from the water/steam cycle to the predetermined injection pressure by subjecting it in separate compressing means to a compression step, and injecting the compressed steam into the gas turbine. 1. A method for temporary increasing the power of a gas turbine , which is part of a combined-cycle power plant , wherein the exhaust gas of said gas turbine is used in a heat recovery steam generator to generate steam for a water/steam cycle including a steam turbine with a high pressure steam turbine , an intermediate pressure steam turbine and a low pressure steam turbine , said method comprising;injecting steam from said water/steam cycle at a predetermined injection pressure into said gas turbine, wherein steam of a lower pressure than said predetermined injection pressure is taken from said water/steam cycle, that the pressure of said steam taken from said water/steam cycle is increased to said predetermined injection pressure by subjecting it in separate compressing means to a compression step, and that said compressed steam is injected into said gas turbine.2. The method as claimed in claim 1 , wherein said separate compressing means comprises at least one steam-driven ejector with a fixed or variable steam nozzle.3. The method as claimed in claim 2 , wherein said ...

FEEDFORWARD SYSTEMS AND METHODS FOR SPRAY INTERCOOLING FLUID FLOWS

A system for a gas turbine includes a control system comprising a processor. The processor is configured to receive a signal indicating spray intercooling fluid demand of the gas turbine. The processor is configured to determine a rate of change of the spray intercooling fluid demand. The processor is configured to control flow of a nitrogen oxide (NO) minimization fluid that reduces NOemissions from the gas turbine based at least in part on the rate of change of the spray intercooling fluid demand. 1. A system for a gas turbine , comprising: receive a signal indicating spray intercooling fluid demand of the gas turbine;', 'determine a rate of change of the spray intercooling fluid demand; and', {'sub': X', 'X, 'control flow of a nitrogen oxide (NO) minimization fluid that reduces NOemissions from the gas turbine based at least in part on the rate of change of the spray intercooling fluid demand.'}], 'a control system comprising a processor configured to2. The system of claim 1 , wherein the processor is configured to determine the rate of change of the spray intercooling fluid demand by utilizing a first order lag filter.3. The system of claim 2 , wherein the first order lag filter comprises a transfer function of Y(s)/X(s)=Ks/(ts+1) claim 2 , wherein Y(s) is the output in the Laplace domain claim 2 , and X(s) is the input in the Laplace domain claim 2 , t is a time constant claim 2 , and K is a gain.4. The system of claim 1 , wherein the processor is configured to enable the gas turbine to remain in regulatory emissions compliance during a delay in time between a change in the NOminimization fluid entering the combustor and feedback from NOemissions generated by the gas turbine.5. The system of claim 1 , wherein the processor is configured to determine the rate of change of the spray intercooling fluid demand based on a compared value derived by comparing a previous fluid demand sample with a current fluid demand sample.6. The system of claim 5 , wherein the ...

REDUCING THE LOAD CONSUMED BY GAS TURBINE COMPRESSOR AND MAXIMIZING TURBINE MASS FLOW

The invention is applicable to industrial gas turbines to reduce the load consumed by the gas turbine compressor and to maximize the turbine mass flow. 12-. (canceled)3. A process for reducing a compressor load consumption of a gas turbine comprising the steps of:injecting a high pressure cold water into a compressor to reduce an air outlet temperature and pressure above a saturation point before leaving the compressor.4. The process according to claim 3 , further including the steps of adjusting a temperature of the high pressure cold water being injected into the compressor in order to increase the improvement in gas turbine overall efficiency.5. A system to reduce a compressor load consumption of a gas turbine comprising:an electric generator;a turbine having a first end operatively connected to the electric generator;a compressor connected to a second end of the turbine;an injection device located between the turbine and the compressor;wherein the injection device includes nozzles to inject a high pressure cold water into the compressor.6. the system according to claim 5 , further including a temperature controlling device connected to the injection device to control the temperature of the high pressure cold water. This application is a national stage entry of PCT/IB2013/054458 filed May 30, 2013, under the International Convention claiming priority over European Union Patent Application No. GC 2012-22727 filed Nov. 6, 2012.This invention is applicable to industrial gas turbines, and looking into reducing the load consumed by gas turbine COMPRESSOR and maximizing turbine MASS FLOW.Improving gas turbines overall efficiency efforts have no limit, and more efforts are taking placed in this field, as this will lead to increase in power generated by gas turbine and reduces fuel consumption for that power.The main problem avoiding gas turbine overall efficiency improvement is that, air compressor alone consumes most of the power being generated by the turbine. ...

Systems and Methods for Variable Water Injection Flow Control

Embodiments of the disclosure can include systems and methods for variable water injection flow control. For example, an operator of a gas turbine system may be enabled to adjust a water injection flow rate (and/or an inlet guide vein (IGV) and/or a firing temperature) of the gas turbine system to optimize performance during current conditions. In one embodiment, a provided method can include: receiving a water injection flow reference comprising one or more conditions of the gas turbine system; receiving water injection flow data from a sensor monitoring the gas turbine system; calculating a water injection flow rate value that characterizes one or more conditions based at least in part on the water injection flow reference and the water injection flow data; and adjusting a water injection flow rate of the gas turbine system to the calculated water injection flow rate value. 1. A method comprising:receiving, by a computing device processor, a water injection flow reference comprising one or more conditions of a gas turbine system;receiving, by a computing device processor, water injection flow data from a sensor monitoring the gas turbine system;calculating, by a computing device processor, a water injection flow rate value that characterizes one or more conditions based at least in part on the water injection flow reference and the water injection flow data; andadjusting, by a computing device processor, a water injection flow rate of the gas turbine system to the calculated water injection flow rate value.2. The method of claim 1 , wherein calculating the water injection flow rate that characterizes one or more conditions comprises:calculating a water injection flow rate that increases power output of the gas turbine system.3. The method of claim 1 , wherein calculating the water injection flow rate that characterizes one or more conditions comprises:calculating a water injection flow rate that increases efficiency of the gas turbine system.4. The method of claim ...

Method and appliance for rapidly increasing output and maintaining additional output for limited period of gas turbine plant

To increase the output water, as additional working medium from storage tank (6), is fed, by gravity or pumped, into the gas turbine (1). A valve (9) controls the flow of the water the temperature of which is controlled by a heat exchanger or other suitable device. Steam can also be used as the additional working medium both media being obtained from a waste heat boiler (13) heated by the turbine exhaust gases (30)

Gas turbine assembly especially for a power unit has cooling component between two combustion chambers in the gas turbine

A gas turbine assembly, especially for a power unit, comprises a compressor (2) and two downstream combustion chamber (3,4) in series followed by a turbine (5). There is a cooling unit (12) between the two combustion chambers. An independent claim is also included for an operating process for the above.

Gas turbine system using high-humidity air and its exhaust gas treatment system

Method of and device for increasing power output of gas turbine by wet compression

FIELD: gas turbines. SUBSTANCE: according to method, drops of liquid chosen from alcohols, water and their mixtures are added to working medium of compressor containing air. Number of indicated drops is sufficient to provide working medium getting into intake hole of compressor which contains at least three quarters of percent of water in form of admixture to fully wet air. Liquid is added to flow in point higher than compressor intake hole. Liquid is delivered during period of time exceeding that required for periodical cleaning of inner parts from deposited particles by means of which temperature rise in working medium caused by compression is reduced. EFFECT: increased useful power of turbine. 13 cl, 9 dwg СЗ ЬсС ПЧ с» (19) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ ВИ `” 2 178 532 (51) МПК” (13) С2 Е 02 С 7/30 (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 98122426/06, 02.05.1997 (24) Дата начала действия патента: 02.05.1997 (30) Приоритет: 14.05.1996 $ 08/645,781 18.09.1996 0$ 08/715,675 (46) Дата публикации: 20.01.2002 (56) Ссылки: КЦ 2053399 СЛ, 27.01.1996. КУЛАГИН И.И. Основы теории авиационных газотурбинных двигателей. -М.: Военное издательс тво Министерства обороны СССР, 1967, с.264-266, ОЕ 2549790 АЛ, 18.05.1977. ЕР 0444913 АЛ, 04.09.1991. УР 63248931 А, 17.10.1988. УР 05195809 А, 03.08.1993. 9$ 25398497 А, 21.03.1995. ВЕ 525244 А, 25.01.1954. СН 248309 А, 30.04.1947. СН 250738 А, 15.09.1947. (85) Дата перевода заявки РСТ на национальную фазу: 15.12.1998 (86) Заявка РСТ: 0$ 97/08757 (02.05.1997) (87) Публикация РСТ: М/О 97/43530 (20.11.1997) (71) Заявитель: ДЗЕ ДАУ КЕМИКАЛ КОМПАНИ (0$) (72) Изобретатель: ЗАЧАРИ Ричард Е. (ЦЗ), ХАДСОН Роджер Д. (4$), ГЕНРИ Джеймс Е. (4$), ЛАЙВЛИ Вильям Е. (4$) (73) Патентообладатель: ДЗЕ ДАУ КЕМИКАЛ КОМПАНИ (15) (74) Патентный поверенный: Томская Елена Владимировна (54) СПОСОБ И УСТРОЙСТВО ДЛЯ УВЕЛИЧЕНИЯ МОЩНОСТИ В ГАЗОВЫХ ТУРБИНАХ ПОСРЕДСТВОМ МОКРОГО СЖАТИЯ (57) Способ увеличения ...

2-axis type gas turbine having steam injecting apparatus

가스 터빈의 연소기에 수증기를 분사해서 터빈의 출력을 증가시킬 때, 증기 분사 시의 압축기의 서지 마진 확대를 가능하게 한 증기 분사 기구를 갖는 2축 가스 터빈을 제공한다. 입구 안내익(12)을 설치한 압축기(10)와, 연소기(20)와, 터빈(30, 40)과, 배열 회수 보일러(60)와, 연소기에 공급하는 증기를 조절하는 증기 밸브(72)와, 연소기에 공급하는 연료를 조절하는 연료 밸브(71)를 구비한 증기 분사 기구를 갖는 2축식 가스 터빈에 있어서, 압축기의 회전수 계측기와, 배열 회수 보일러로부터 연소기에 공급하는 증기를 계측하는 유량 계측기와, 압축기에 설치한 입구 안내익 개방도 계측기와, 증기 밸브 개방도 계측기를 갖고, 상기 회전수 계측기, 입구 안내익 개방도 계측기 또는 증기 밸브 개방도 계측기로 계측한 각 계측 신호와 가스 터빈에 대한 증가 출력 지령값에 기초하여 상기 연료 밸브, 증기 밸브 및 입구 안내익의 개방도를 조작하는 지령 신호를 연산해서 출력하는 제어 장치(100)를 구비하였다.

Humidificated gas turbine and pure oxygen combustion system having the same

본 발명은, 연료가 공급되며 순산소와 반응하여 연소반응이 일어나고, 증기상태의 물이 투입되는 연소부와, 상기 연소부에서 연소반응에 의해 발생 된 연소가스 및 투입된 증기에 의해 구동되는 터빈부를 포함하는 가습가스터빈을 제공한다. 이와 같은 본 발명의 일 실시예에 따른 가습가스터빈에 의하면, 기체상태의 증기를 연소부에 투입함으로서 발전시스템의 효율이 향상되는 효과를 제공한다.

Thermal power facility recovering moisture from exhaust gas and method for processing the recovered water of the same

본 발명은, 연소 배기 가스와 기액 직접 접촉하는 회수수 계통의 순환수와 보일러 급수에 이용하는 급수 계통의 급수 pH를 조정하여 설비 전체에서 사용하는 pH 조정제의 양을 저감하고, 배기 가스로부터 습분을 회수하는 화력 발전 설비의 경제성을 향상시킨 화력 발전 설비를 제공하는 것을 과제로 한다. 배기 가스로부터 습분을 회수하는 화력 발전 설비에 가스 터빈으로부터 배출된 연소 배기 가스를 열원으로서 공급하여 증기를 발생하는 배열 회수 보일러와, 그 하류측에 설치되어 배열 회수 보일러로부터 흘러내린 연소 배기 가스와 물과 기액 직접 접촉하여 연소 배기 가스 중의 습분을 응축하여 회수하는 물 회수 장치와, 회수수의 일부를 물 회수 장치로 순환시키는 회수수 계통과, 회수수의 다른 일부를 급수로서 배열 회수 보일러에 공급하는 급수 계통과, 회수수 계통을 흐르는 순환수를 제1 pH의 값으로 조정하는 제1 pH 조정 장치와, 급수 계통을 흐르는 급수를 제2 pH의 값으로 조정하는 제2 pH 조정 장치와, pH 조정 장치를 제어하는 제어 장치를 구비하여 구성하였다. The present invention reduces the amount of the pH adjuster used in the entire facility by regulating the circulating water in the recovered water system in direct contact with the combustion exhaust gas and the feed water pH in the water system used in the boiler feedwater, The present invention provides a thermal power generation facility that improves the economical efficiency of a thermal power generation facility. An exhaust gas recirculation system comprising: an arrangement recovery boiler for generating steam by supplying combustion exhaust gas discharged from a gas turbine as a heat source to a thermal power generation facility for recovering moisture from exhaust gas; combustion exhaust gas flowing downstream from the arrangement recovery boiler, A water recovery system for circulating a part of the recovered water to the water recovery device, and a part of the recovered water to be supplied to the batch recovery boiler as feed water A first pH adjusting device for adjusting the circulating water flowing through the water supply system and the recovered water system to a value of the first pH, a second pH adjusting device for adjusting the water supplied to the water supply system to a second pH value, And a control device for controlling the apparatus.

GAS TURBINE SYSTEM

1. Газотурбинная система, содержащая:камеру сгорания, имеющую топливную форсунку для впрыска газообразного топлива и впрыскиваемой воды;бак для накапливания впрыскиваемой воды, подаваемой в камеру сгорания;устройство повышения давления топлива для повышения давления газообразного топлива, подаваемого в камеру сгорания;канал подачи топлива для подачи газообразного топлива с повышенным давлением в камеру сгорания; инагнетательный канал, сообщающийся с баком и каналом подачи топлива, для повышения давления впрыскиваемой воды при помощи газообразного топлива с повышенным давлением.2. Газотурбинная система по п. 1, в которой камера сгорания представляет собой камеру с предварительным смешиванием, в которой происходит предварительное смешивание газообразного топлива и впрыскиваемой воды.3. Газотурбинная система по п. 2, в которой газообразное топливо содержит газообразный водород.4. Газотурбинная система по любому из пп. 1-3, дополнительно содержащая устройство для получения чистой воды, чтобы производить впрыскиваемую воду в виде чистой воды.5. Газотурбинная система по любому из пп. 1-3, в которой устройство повышения давления топлива содержит компрессорное устройство для газа.6. Газотурбинная система по любому из пп. 1-3, в которой устройство повышения давления топлива содержит компрессорное устройство для жидкого топлива, чтобы повышать давление жидкого топлива, и испаритель для получения газообразного топлива из жидкого топлива с повышенным давлением. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (51) МПК F02C 3/30 (11) (13) 2014 119 542 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2014119542/06, 29.10.2012 (71) Заявитель(и): КАВАСАКИ ЮКОГЁ КАБУСИКИ КАЙСЯ (JP) Приоритет(ы): (30) Конвенционный приоритет: 02.11.2011 JP 2011-240818 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 02.06.2014 R U (43) Дата публикации заявки: 10.12.2015 Бюл. № 34 (72) Автор(ы): ХОРИКАВА Ацуси (JP), КАДЗАРИ Масахиде (JP), КАШИХАРА ...

Ring type injection apparatus for wet compression

본 발명은 분사된 액적이 응축수로 배수되지 않고 최대한 증발되도록 하여 압축기의 압축일을 감소시킬 수 있는 습식 압축용 환형 분사 장치를 제공하는 것이 그 기술적 과제이다. 이를 위해, 본 발명의 습식 압축용 환형 분사 장치는, 같은 중심을 가지며 반경 방향으로 간격을 두어 배치되는 복수의 환형 파이프; 및 상기 각각의 환형 파이프에 배치되되 원주 방향으로 간격을 두어 배치되는 복수의 노즐을 포함한다. It is a technical object of the present invention to provide a wet type compression type annular injection device capable of reducing the compression work of a compressor by causing evaporated droplets to evaporate as much as possible without draining them into condensed water. To this end, the wet compression annular sprayer of the present invention comprises: a plurality of annular pipes having the same center and spaced apart in the radial direction; And a plurality of nozzles disposed in the respective annular pipes and spaced apart in the circumferential direction.

Power augmentation system for gas turbine

本发明涉及用于燃气涡轮的功率增大系统。具体而言，用于电联接到电力网的燃气涡轮的功率增大系统以连续流动顺序包括：压缩空气供应、压缩空气储存罐和布置在压缩空气储存罐下游的膨胀涡轮。膨胀涡轮的排气出口与燃气涡轮的压缩机或入口区段中的至少一者流体连通。

System and method for augmenting turbine power output

본 발명의 방법 및 시스템은 다양한 모드의 작동에 사용될 수 있는 가스 터빈 엔진의 축 출력을 증강시킨다. 시스템은 가스 터빈 엔진 내로 분무수를 분사하여, 그것에 의해 적어도 하나의 압축기 블레이드로부터 부착물의 제거를 달성할 수 있는 세척 유닛과, 공기 흐름의 질량 유동을 증가시키기 위해 전산 유체 모델의 제어 하에 가스 터빈 또는 가스 터빈 입구의 덕트의 공기 흐름 내에 분무수를 분사할 수 있는 적어도 하나의 물 분사 유닛을 포함함으로써, 가스 터빈의 출력을 증강시킬 수 있다.

Turboprop direct-injection hybrid multistage-power underwater high-speed propeller and control method

本发明公开了涡桨直喷混合式多级动力水下高速推进器及控制方法，包括低速段发动机、加速段发动机以及高速段发动机，针对不同作战方针，将水冲压高金属含量推进剂发动机与高金属含量固体火箭发动机相结合，并辅以涡轮动力输出装置，通过合理设计装药方式，调整装药量和冲压入水量满足不同航行速度下系统对推进动力的需求，突破了传统水下航行器单一航速的限制，可在同一航程中实现常规低速巡航和七倍于常规速度的高速打击两种典型运动状态。

Hydrogen gas tubine engine

Hydrogen gas and a water supply are not mixed in advance but are directly introduced into the combustion chamber via separate nozzles. Hydrogen gas and the water spray are jetted into the combustion chamber simultaneously or at slightly staggered timings. As the compressed hydrogen gas is ignited by the ignition plug in the combustion chamber, the thermal energy by the combustion of hydrogen gas is directly converted into mechanical dynamic energy. At the same time, a portion of the thermal energy causes the water spray in the combustion chamber to instantly vaporise into stream. Explosive thermal energy of hydrogen gas and steam will become combined and converted into mechanical dynamic energy.

POWER FORCING DEVICE WITH DYNAMIC DYNAMIC PROCESSES

1. Устройство форсирования мощности с демпфированием динамических процессов, предназначенное для газотурбинного двигателя и содержащеепереходный элемент камеры сгорания,паровой коллектор, расположенный вокруг переходного элемента,причем через переходный элемент проходят каналы переходного элемента, ачерез паровой коллектор проходят каналы коллектора,при этом каналы коллектора совмещены с каналами переходного элемента.2. Устройство форсирования мощности по п.1, в котором каналы переходного элемента имеют проходящие через них отверстия.3. Устройство форсирования мощности по п.2, в котором указанные отверстия содержат отверстия, расположенные под углом.4. Устройство форсирования мощности по п.1, в котором паровой коллектор имеет расположенную в нем полость.5. Устройство форсирования мощности по п.1, в котором каналы коллектора содержат трубки.6. Устройство форсирования мощности по п.5, в котором указанные трубки содержат трубки, расположенные под углом.7. Устройство форсирования мощности по п.1, в котором паровой коллектор имеет продувочные каналы.8. Устройство форсирования мощности по п.1, в котором переходный элемент содержит раму, а паровой коллектор содержит паропровод, расположенный на указанной раме.9. Устройство форсирования мощности по п.1, в котором каналы коллектора имеют заданный размер, выбранный на основании частоты колебаний, возникающих в камере сгорания.10. Устройство форсирования мощности с демпфированием динамических процессов, предназначенное для газотурбинного двигателя и содержащеепереходный элемент камеры сгорания,паровой коллектор, расположенный вокруг переходного элемента,причем � РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F01D 9/02 (13) 2013 143 396 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2013143396/06, 31.03.2011 (71) Заявитель(и): Дженерал Электрик Компани (US) Приоритет(ы): (22) Дата подачи заявки: 31.03.2011 (43) Дата публикации заявки: 10.05.2015 Бюл. № 13 R U (85) Дата ...

Combustion engine

本实用新型公开了一种燃烧式发动机。燃烧式发动机可包括燃烧单元以及至少一个喷水器，所述喷水器构造为向燃烧单元内或上游喷水。燃烧式发动机可进一步包括流动地连接至燃烧单元的上游的第一冷却器，以及第一集水器，所述第一集水器流动地相互连接在第一冷却器和至少一个喷水器之间。第一集水器（18）可被构造为收集冷凝水且将收集的水供给至少一个喷水器。因此，第一集水器可用作用于喷水的富足水源。本实用新型可以提供用于供给喷水器的富足水源，向喷水器提供蒸馏水，以及提供一多余系统，即包括两个供水系统，用于提供用以喷水的水，其可提供故障保险系统，即使一个供水系统临时不能向喷水器提供所需水量，也能够供水。

Gas turbine power generation equipment and air humidifying apparatus

本发明涉及一种空气加湿器，用于向燃气轮机的工作介质添加水分进行加湿，以及涉及一种燃气轮机发电设备，用于利用具有高湿度的工作介质驱动燃气轮机发电。本发明的目的是降低燃气轮机中的燃烧过的废气的压力损失，提高发电机的输出和效率。该设备包含：加湿器(3)、燃烧器(5)、涡轮机(6)、发电机(7)和水回收装置(10)，还包含废气再加热器(11)，用于利用由加湿器排出的盈余水对由水回收装置排出的燃烧过的废气进行加热。

System and method for power generation in steel mill

제철소에서의 동력 발전용 시스템은, 제철소로부터의 폐수 및 석탄을 수용하여, 석탄-물 슬러리(coal-water slurry)를 제공하는 석탄-물 슬러리 제조 유닛(unit)과, 석탄-물 슬러리를 가스화하여, 일산화탄소 및 수소를 포함하는 합성 가스를 생산하는 가스화 유닛과, 합성 가스를 처리하여, 처리된 합성 가스를 생산하는 처리 유닛과, 처리된 합성 가스의 적어도 일부분을 사용하여 제철소에 전기를 공급하는 동력 발전 유닛을 포함한다. 관련 방법이 또한 서술된다.

Unit for supply of fluid medium and for increase of power and procedure for injection of fluid medium

FIELD: machine building. SUBSTANCE: unit for supply of fluid medium made for system increasing power consists of: one or more stages in active or non-active state. Each stage has at least the first and second valves; each first and second valve can be in open and closed positions. The system for increase of power consists of: a unit for fluid medium supply containing one or more stages in active and non-active state. Each stage has at least the first and second valves. Each first and second valve can be in open and closed position. Further, the system consists of a pump connected to the unit of fluid medium supply feeding each stage, of a control unit connected to the pump, of a regulating pump connected to the unit of fluid medium supply to control the first and second valves, and of a source of fluid medium supplying fluid medium to one or more stages. The procedure for injection of fluid medium from the unit of fluid medium supply into the injection unit consists in: activation of at least one stage of the unit for fluid medium supply with one ore more stages in active or non-active state; also, each stage has at least the first and the second valves. Each first and second valve can be in open or closed positions. Activation proceeds like follow: a stage is filled with fluid medium from the fluid medium source at the first valve in an open position and the second valve in a closed position; fluid medium is compressed with the pump to the first specified level; compressed fluid medium is released at the first valve in a closed position and the second valve in an open position. EFFECT: raised power of gas turbines and reduced cost of system for increase of power. 32 cl, 5 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 425 994 (13) C2 (51) МПК F02C 1/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2009123447/06, 19.06.2009 (24) Дата начала отсчета срока действия патента: 19. ...

Method for operating a premix burner

In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Method for operating a premix burner

In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

A kind of simple cycle gas turbine engine based on rotation detonation combustion

本发明提供了一种基于旋转爆轰燃烧的简单循环燃气轮机，它包括压气机、旋转爆轰燃烧室、热射流起爆管、引射器、掺混器、涡轮、负载、冷源。将旋转爆轰燃烧室应用于简单循环燃气轮机，并在燃烧室尾部增加掺混器保证涡轮进口处工质未超温。本发明利用旋转爆轰燃烧室的增压特性，增加了燃烧室出口工质的做功能力，在涡轮进口处温度、部件效率、压气机压比相同的条件下，使燃气轮机循环热效率提高了5％‑10％。

Gas turbine operating method and gas turbine for carrying out the method

Device and method for temporary power increase

Изобретение относится к области турбинных двигателей, а более конкретно к устройству (13) и способу временного увеличения мощности по меньшей мере первого турбинного двигателя (5A). Устройство (13) содержит бак (14) охлаждающей жидкости, первый контур (16A) впрыска, соединенный с упомянутым баком (14) и ведущий к по меньшей мере одной форсунке(22), выполненной с возможностью установки выше по потоку от по меньшей мере одной ступени (8) компрессора первого турбинного двигателя (5A). Этот первый контур (16A) впрыска содержит первый проходной клапан (23), выполненный с возможностью открываться, когда давление превышает предварительно определенное пороговое значение по сравнению с давлением ниже по потоку от по меньшей мере одной ступени (8) компрессора второго турбинного двигателя (5B) с тем, чтобы давать возможность охлаждающей жидкости протекать по направлению к упомянутой форсунке(22) первого контура (16A) впрыска. Достигается автоматическое и быстрое временное увеличение мощности двигателя для компенсации отказа другого двигателя, минимизация дополнительного веса. 4 н. и 3 з.п. ф-лы, 5 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 644 317 C2 (51) МПК F02C 3/30 (2006.01) F02C 7/143 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F02C 3/305 (2017.08); F02C 7/1435 (2017.08) (21)(22) Заявка: 2015129556, 18.12.2013 (24) Дата начала отсчета срока действия патента: Дата регистрации: 08.02.2018 20.12.2012 FR 1262433 (43) Дата публикации заявки: 25.01.2017 Бюл. № 3 (56) Список документов, цитированных в отчете о поиске: US 2004255596 A1, 23.12.2004. US 3518023 A, 30.06.1970. GB 2079707 A, 27.01.1982. US 3234740 A, 15.02.1966. RU 2386832 C1, 20.04.2010. (45) Опубликовано: 08.02.2018 Бюл. № 4 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 20.07.2015 2 6 4 4 3 1 7 (73) Патентообладатель(и): ТУРБОМЕКА (FR) Приоритет(ы): (30) Конвенционный приоритет: R U 18.12.2013 (72) Автор(ы): МУАН Бертран (FR), ЮМБЕР ...

Solar energy chemical recuperation cycle system

本发明涉及能源技术领域，公开了一种太阳能化学回热燃气轮机系统，包括：尾气重整器、太阳能重整器以及设有燃烧室和燃气透平的燃气轮机。其中，尾气重整器的反应侧出口与太阳能重整器入口相连接，烟气侧入口和燃气透平的排气侧相连接，且尾气重整器设置有燃料入口；太阳能重整器的出口侧与燃烧室入口侧相连接；燃料在燃烧室燃烧后，在燃气透平内做功，所生成的尾气进入尾气重整器；燃料与水蒸汽混合后从燃料入口进入尾气重整器的反应侧，在尾气的加热作用下发生重整反应并生成合成气，合成气进入太阳能重整器后通过吸收聚焦太阳能，发生进一步重整反应，并供应给燃烧室。该太阳能化学回热燃气轮机系统能够提高能量利用效率。

Method and system for gas turbine power augmentation using steam injection

Operation method of gas turbine assembly

POWER PLANT OF THE COMBINED CYCLE AND METHOD OF OPERATION OF SUCH POWER PLANT OF THE COMBINED CYCLE

1. Электростанция (10а-d) комбинированного цикла, содержащая газовую турбину (11а,b), выход выхлопных газов которой присоединен к теплоутилизационному парогенератору (19), который составляет часть водно-парового цикла (35), причем для получения большого резерва мощности и в то же время высокой проектной производительности при работе с базовой нагрузкой газовая турбина (11а, b) спроектирована с возможностью (26, 27) закачки пара для повышения мощности, причем газовая турбина (11а) содержит по меньшей мере одну камеру (15, 16) сгорания и компрессор (12) для подачи охлаждающего воздуха для указанной газовой турбины (11а, b), который выводится из компрессора (12) и охлаждается по меньшей мере в одном охладителе (17, 18) охлаждающего воздуха, и пар для закачки пара генерируется в указанном охладителе (17, 18) охлаждающего воздуха, причем указанный пар закачивается в выход или вход со стороны атмосферы указанного охладителя (17, 18) охлаждающего воздуха и/или непосредственно в указанную по меньшей мере одну камеру (15, 16) сгорания, и теплоутилизационный парогенератор (19) оснащен дожиганием (22, 22'), отличающаяся тем, что дожигание представляет собой по меньшей мере одноступенчатое дожигание (22) для увеличения производства пара высокого давления и обеспечения повышения мощности в качестве резерва мощности для энергетической системы, когда это потребуется.2. Электростанция комбинированного цикла по п. 1, отличающаяся тем, что по меньшей мере один охладитель (17, 18) охлаждающего воздуха представляет собой прямоточный охладитель (OTC).3. Электростанция комбинированного цикла по п. 1, отличающаяся тем, что пар для закачки пара отбирается из указанного теплоутилизационного парогенератора (19).4. Электростанция комбинированного ц РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F01K 23/06 (13) 2014 143 268 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2014143268, 22.03.2013 (71) Заявитель(и): АЛЬСТОМ ТЕКНОЛОДЖИ ...

DEVICE AND METHOD FOR TEMPORARY INCREASING POWER

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2015 129 556 A (51) МПК F02C 3/30 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2015129556, 18.12.2013 (71) Заявитель(и): ТУРБОМЕКА (FR) Приоритет(ы): (30) Конвенционный приоритет: 20.12.2012 FR 1262433 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 20.07.2015 R U (43) Дата публикации заявки: 25.01.2017 Бюл. № 03 (72) Автор(ы): МУАН Бертран (FR), ЮМБЕР Софи (FR), ЛАБОРД Патрис (FR), МИНЕЛЬ Лоран (FR), ПРЕНСИВАЛЛЬ Реми (FR) (86) Заявка PCT: (87) Публикация заявки PCT: WO 2014/096694 (26.06.2014) R U (54) УСТРОЙСТВО И СПОСОБ ДЛЯ ВРЕМЕННОГО УВЕЛИЧЕНИЯ МОЩНОСТИ (57) Формула изобретения 1. Устройство (13) для временного увеличения мощности по меньшей мере первого турбинного двигателя (5A), содержащее: бак (14) охлаждающей жидкости, первый контур (16A) впрыска, соединенный с упомянутым баком (14) и ведущий к по меньшей мере одной форсунке (22), выполненной с возможностью установки выше по потоку от по меньшей мере одной ступени (8) компрессора первого турбинного двигателя (5A), при этом первый контур (16A) впрыска включает в себя, по меньшей мере, первый проходной клапан (23), выполненный с возможностью открываться, когда давление выше по потоку от упомянутого первого проходного клапана (23) превышает давление ниже по потоку, по меньшей мере, от одной ступени (8) компрессора второго турбинного двигателя (5B) на величину, большую, чем предварительно определенное пороговое значение, с тем, чтобы давать возможность охлаждающей жидкости протекать по направлению к упомянутой форсунке (22) первого контура (16A) впрыска, и тем, что оно дополнительно включает в себя по меньшей мере один контур (15A) наддува, выполненный с возможностью соединения с по меньшей мере одной ступенью (8) компрессора первого турбинного двигателя (5A) для наддува упомянутого бака (14) и содержащий обратный клапан (21) для избегания сброса давления в баке (14). 2. Устройство (13) по п. 1, ...

Combined cycle power generation plant utilzing solar heat

太阳热利用联合循环发电站具备：对燃烧用空气进行加压的压缩机（1）；将上述燃烧用空气（60）和燃气涡轮机燃料（61）混合燃烧，产生高温的燃烧气体的燃烧器（2）；使用上述燃烧气体来驱动上述压缩机（1）的燃气涡轮机（3）；从上述燃气涡轮机（3）的废气的热能得到蒸汽的排热回收锅炉（4）；使用通过上述排热回收锅炉（4）得到的蒸汽进行驱动的蒸汽涡轮机（5），还具备：通过太阳光的热能使给水成为温水的集热器（10）；贮存从上述集热器（10）和上述排热回收锅炉（4）得到的高温高压水的蓄热器（9）；将贮存在上述蓄热器（9）中的高温高压水作为喷雾水向上述压缩机（1）的吸气空气喷雾的喷雾装置（4）。

Method and system for using low btu fuel gas in a gas turbine

하나의 실시양태에서, 연소 시스템은, 약 100 Btu/scf(British thermal units per standard cubic foot) 이하의 발열량을 갖는 연료를 포함하는 연료 공급기, 상기 연료 공급기와 유체 연통하는 불활성 가스 격리 유닛(32), 및 상기 불활성 가스 격리 유닛(32) 및 산화제(78) 공급기의 하류에 위치하여 그들과 유체 연통하는 연소 시스템을 포함한다. 불활성 가스 격리 유닛(32)은 CO로부터 N 2 를 분리하며 약 110 Btu/scf 이상의 발열량을 갖는 잔류물(retentate) 스트림을 형성하도록 구성된 멤브레인을 포함한다. 하나의 실시양태에서, 발전기(8)를 작동하는 방법은, 연료 스트림(76)을 불활성 가스 격리 유닛(32)을 통해 통과시켜 상기 연료 스트림(76)으로부터 N 2 를 제거하고 잔류물 스트림을 형성시키는 단계, 및 상기 잔류물 스트림 및 산화제(78) 스트림을 연소시켜 연소 스트림을 형성하는 단계를 포함한다. In one embodiment, a combustion system includes a fuel supply comprising a fuel having a calorific value of about 100 Btu / scf (British thermal units per standard cubic foot) or less, an inert gas isolation unit 32 in fluid communication with the fuel supply. And a combustion system located downstream of the inert gas isolation unit 32 and oxidant 78 feeder and in fluid communication therewith. Inert gas isolation unit 32 includes a membrane that separates N 2 from CO and is configured to form a retentate stream having a calorific value of at least about 110 Btu / scf. In one embodiment, the method of operating the generator 8 passes the fuel stream 76 through an inert gas isolation unit 32 to remove N 2 from the fuel stream 76 and form a residue stream. And combusting the residue stream and oxidant 78 stream to form a combustion stream.

High-efficiency thermal engine

FIELD: engines and pumps. SUBSTANCE: proposed thermal engine comprises two independent rotors (3, 4), preferable coaxial ones (XX), each being arranged in one of two cases (5, 6). Note here that first rotor (3) makes a part of LP stage (1), while second rotor (4) is incorporates with HP stage (2). Every stage (1, 2) furnished with its rotor (3, 4) comprises gas compressor (15, 16) and gas expanding turbine (17, 18). Thermal engine comprises at least one combustion chamber (19, 20). Note that at least one combustion chamber is arranged in, in fact, central cylindrical space axially limited by two rotors (3, 4) and their cases (5, 6), and, radially limited, in inward to outward direction, by inner (22), intermediate (23) and outer (24) walls, in fact, cylindrical and coaxial relative to axis (XX). Intermediate (23) and inner (22) walls form, between themselves, inner circular channel (26) communicating outlet of HP-stage compressor (16) with inlet of first combustion chamber (19). Outer (24) and intermediate (23) walls form outer circular channel (25) communicating outlet of compressor (15) of LP stage (1) with inlet of compressor (16) of HP stage (2). Outlet of first combustion chamber (19) feed combustion gases to turbine (18) of HP stage (2), said gases being directed from outlet of turbine (18) of HP stage (2) to inlet of turbine (17) of LP stage (1). Outlet of LP stage (1) communicates with outer space of engine case (24, 27, 31) via at least one exhaust gas channel (41). EFFECT: higher efficiency of micro engine. 26 cl, 4 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 380 557 (13) C2 (51) МПК F02C F02C 3/05 6/00 (2006.01) (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21), (22) Заявка: 2006139622/06, 08.11.2006 (24) Дата начала отсчета срока действия патента: 08.11.2006 (43) Дата публикации заявки: 20.05.2008 2 3 8 0 5 5 7 R U Адрес для переписки: 103735, Москва, ул. Ильинка, 5/2, ООО " ...

NATURAL GAS LIQUEFACTION SYSTEM PROVIDED ON SURFACE OF A WATER EXTEND, AND ASSOCIATED COOLING METHOD

L'installation (10) comporte : - au moins un échangeur thermique refroidi à l'air (22), l'échangeur thermique refroidi à l'air (22) comportant un faisceau de tubes propre à recevoir un flux à refroidir (24) et un ventilateur, propre à faire circuler un flux d'air à travers le faisceau de tubes ; - un ensemble de projection (26) d'eau. L'ensemble de dessalement (20) comporte une prise de prélèvement d'eau salée (100) dans l'étendue d'eau (12), l'ensemble de dessalement (20) étant raccordé en aval à l'ensemble de projection (26) d'eau. L'ensemble de projection (26) d'eau comporte au moins une buse de projection débouchant dans le faisceau de tubes, la ou chaque buse de projection étant dirigée vers les tubes du faisceau de tubes pour projeter de l'eau déminéralisée liquide provenant de l'ensemble de dessalement (20) au contact des tubes du faisceau de tubes. The installation (10) comprises: - at least one air-cooled heat exchanger (22), the air-cooled heat exchanger (22) comprising a bundle of tubes capable of receiving a stream to be cooled (24) and a fan adapted to circulate a flow of air through the bundle of tubes; - A projection assembly (26) of water. The desalination unit (20) has a salt water sampling plug (100) in the water body (12), the desalination unit (20) being connected downstream to the projection assembly ( 26) of water. The water projection assembly (26) comprises at least one projection nozzle opening into the bundle of tubes, the or each projection nozzle being directed towards the tubes of the tube bundle to project liquid demineralized water from the desalination unit (20) in contact with the tubes of the bundle of tubes.

MULTI-ENGINE ENGINE INSTALLATION PROVIDED WITH A FLUID INJECTION AND AIRCRAFT EMERGENCY SYSTEM

La présente invention concerne une installation motrice (10) munie d'un premier turbomoteur (11) et d'un deuxième turbomoteur (16) et d'un système (20) de secours d'injection de fluide dans lesdits turbomoteurs (11, 16). Une première et une deuxième conduites de pressurisation (26, 28) relient un réservoir (21) à chaque générateur de gaz des turbomoteurs. De plus, le système (20) comporte un dispositif d'injection (35, 40) par turbomoteur comportant une conduite d'injection (36, 41) reliant ledit réservoir (21) à au moins une buse d'injection (31). Un distributeur (51, 52) est disposé le long de chaque conduite d'injection (36, 41), chaque distributeur (51) alimentant un turbomoteur étant relié au générateur de gaz de l'autre turbomoteur. The present invention relates to a power plant (10) provided with a first turbine engine (11) and a second turbine engine (16) and a backup system (20) for injecting fluid into said turbine engines (11, 16). ). A first and a second pressurization line (26, 28) connect a reservoir (21) to each gas generator of the turbine engines. In addition, the system (20) comprises an injection device (35, 40) by a turbine engine comprising an injection line (36, 41) connecting said reservoir (21) to at least one injection nozzle (31). A distributor (51, 52) is arranged along each injection line (36, 41), each distributor (51) supplying one turbine engine being connected to the gas generator of the other turbine engine.

METHOD FOR INCREASING THE SAFETY OF A MOTOR INSTALLATION, AND MOTOR INSTALLATION SUITABLE FOR CARRYING OUT SAID METHOD

LIQUID FUEL SUPPLY SYSTEMS FOR A COMBUSTION SYSTEM, IN PARTICULAR A GAS TURBINE, COMPRISING A DEVICE FOR GENERATING AN EMULSION AND FOR DISTRIBUTING THE FLOW OF EMULSION

Système d'alimentation en combustible liquide (12) pour un système à combustion (14), notamment d'une turbine à gaz, comprenant au moins un réservoir de stockage (16) de combustible liquide apte à alimenter au moins un injecteur (34) relié à une chambre de combustion (32) du système à combustion (14), ledit système d'alimentation (12) comprenant une première section de tuyauterie (18) disposée en aval du réservoir (16) et une deuxième section de tuyauterie (20) disposée en aval de la première section de tuyauterie (18) et en amont dudit injecteur (34), ladite première section de tuyauterie (18) comprenant au moins un moyen de mise sous pression (22), et au moins un point d'injection ou entrée (24) d'un produit hydrosoluble, et la deuxième section de tuyauterie (20) comprenant un dispositif (26) de mélange et de répartition de débit configuré pour créer une émulsion et répartir le débit d'émulsion vers au moins un conduit (28) relié audit injecteur (34). La deuxième section de tuyauterie comprend un dispositif de mélange et de répartition de débit et le régime en amont dudit dispositif est configuré pour créer une émulsion et répartir le débit d'émulsion vers au moins un conduit relié audit injecteur. Liquid fuel supply system (12) for a combustion system (14), in particular a gas turbine, comprising at least one liquid fuel storage tank (16) able to supply at least one injector (34) connected to a combustion chamber (32) of the combustion system (14), said supply system (12) comprising a first section of pipe (18) disposed downstream of the tank (16) and a second section of pipe (20 ) disposed downstream of the first pipe section (18) and upstream of said injector (34), said first pipe section (18) comprising at least one pressurizing means (22), and at least one point of injection or inlet (24) of a water-soluble product, and the second section of piping (20) comprising a mixing and flow distribution device (26) configured to create an ...

NATURAL GAS LIQUEFACTION SYSTEM PROVIDED ON SURFACE OF A WATER EXTEND, AND ASSOCIATED COOLING METHOD

L'installation (10) comporte : - au moins un échangeur thermique refroidi à l'air (22), l'échangeur thermique refroidi à l'air (22) comportant un faisceau de tubes propre à recevoir un flux à refroidir (24) et un ventilateur, propre à faire circuler un flux d'air à travers le faisceau de tubes ; - un ensemble de projection (26) d'eau. L'ensemble de dessalement (20) comporte une prise de prélèvement d'eau salée (100) dans l'étendue d'eau (12), l'ensemble de dessalement (20) étant raccordé en aval à l'ensemble de projection (26) d'eau. L'ensemble de projection (26) d'eau comporte au moins une buse de projection débouchant dans le faisceau de tubes, la ou chaque buse de projection étant dirigée vers les tubes du faisceau de tubes pour projeter de l'eau déminéralisée liquide provenant de l'ensemble de dessalement (20) au contact des tubes du faisceau de tubes. The installation (10) comprises: - at least one air-cooled heat exchanger (22), the air-cooled heat exchanger (22) comprising a bundle of tubes capable of receiving a stream to be cooled (24) and a fan, adapted to circulate a flow of air through the bundle of tubes; - A projection assembly (26) of water. The desalination unit (20) has a salt water sampling plug (100) in the water body (12), the desalination unit (20) being connected downstream to the projection assembly ( 26) of water. The water projection assembly (26) comprises at least one projection nozzle opening into the bundle of tubes, the or each projection nozzle being directed towards the tubes of the tube bundle to project liquid demineralized water from the desalination unit (20) in contact with the tubes of the bundle of tubes.

Method and device for overloading turbo-reactors with combined water injection and post-combustion

Turbomachine control method comprising a device for temporary power increase

Procédé de régulation de turbomachine (10) comprenant un dispositif d’augmentation temporaire de puissance (26), ledit procédé de régulation comprenant une étape (E3) dans laquelle on ajuste le débit de fluide réfrigérant injecté en fonction de la pression atmosphérique (P0) et/ou de la température ambiante (T0) et/ou d’au moins un paramètre tel que la vitesse de rotation d’un générateur de gaz (N1), la vitesse de rotation d’une turbine basse pression ou d’une turbine libre (N2), la pression des gaz en sortie d’un étage de compresseur (P3), la température en entrée de la turbine basse pression ou de la turbine libre (T45), le couple moteur (TQ), et/ou le pas collectif d’un rotor d’hélicoptère (XPC) ou le pas d’une hélice d’un turbopropulseur. Figure pour l’abrégé : Fig. 3. Turbomachine regulation method (10) comprising a temporary power increase device (26), said regulation method comprising a step (E3) in which the flow of refrigerant injected is adjusted as a function of atmospheric pressure (P0) and / or the ambient temperature (T0) and / or at least one parameter such as the speed of rotation of a gas generator (N1), the speed of rotation of a low pressure turbine or a turbine free (N2), the gas pressure at the outlet of a compressor stage (P3), the inlet temperature of the low pressure turbine or of the free turbine (T45), the engine torque (TQ), and / or the The collective pitch of a helicopter rotor (XPC) or the pitch of a propeller of a turboprop. Figure for the abstract: Fig. 3.

Internal combustion engine operating by hydrogen gas

MULTI-ENGINE ENGINE INSTALLATION PROVIDED WITH A FLUID INJECTION AND AIRCRAFT EMERGENCY SYSTEM

La présente invention concerne une installation motrice (10) munie d'un premier turbomoteur (11) et d'un deuxième turbomoteur (16) et d'un système (20) de secours d'injection de fluide dans lesdits turbomoteurs (11, 16). Une première et une deuxième conduites de pressurisation (26, 28) relient un réservoir (21) à chaque générateur de gaz des turbomoteurs. De plus, le système (20) comporte un dispositif d'injection (35, 40) par turbomoteur comportant une conduite d'injection (36, 41) reliant ledit réservoir (21) à au moins une buse d'injection (31). Un distributeur (51, 52) est disposé le long de chaque conduite d'injection (36, 41), chaque distributeur (51) alimentant un turbomoteur étant relié au générateur de gaz de l'autre turbomoteur. The present invention relates to a power plant (10) provided with a first turbine engine (11) and a second turbine engine (16) and a system (20) for fluid injection backup in said turbine engines (11, 16 ). First and second pressurizing lines (26, 28) connect a reservoir (21) to each gas generator of the turbine engines. In addition, the system (20) comprises a turbine engine injection device (35, 40) comprising an injection pipe (36, 41) connecting said reservoir (21) to at least one injection nozzle (31). A distributor (51, 52) is arranged along each injection line (36, 41), each distributor (51) supplying a turbine engine being connected to the gas generator of the other turbine engine.

DEVICE AND METHOD FOR TEMPORARY POWER INCREASE

L'invention concerne le domaine des turbomachines, et plus spécifiquement un dispositif (13) et un procédé d'augmentation temporaire de puissance d'au moins une première turbomachine (5A). Ce dispositif (13) comprend un réservoir (14) de liquide réfrigérant et un premier circuit d'injection (16A), connecté audit réservoir (14) et débouchant sur au moins une tuyère d'injection (22) apte à être installée en amont d'au moins un étage de compresseur (8) de la première turbomachine (5A). Ce premier circuit d'injection (16A) comporte au moins une première vanne de passage (23) configurée pour s'ouvrir quand une surpression excède un seuil prédéterminé par rapport à une pression en aval d'au moins un étage de compresseur (8) d'une deuxième turbomachine (5B), de manière à permettre l'écoulement du liquide réfrigérant vers ladite tuyère d'injection (22) du premier circuit d'injection (16A).