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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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14-06-2012 дата публикации

Gas turbine engine and cooling system

Номер: US20120144843A1

Автор: Eric Sean Donovan, Steven Wesley Tomlinson, William Daniel Feltz

Принадлежит: Rolls Royce North American Technologies Inc

One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique cooling system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooling one or more objects of cooling. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

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Номер записи: 1

28-06-2012 дата публикации

System and method for using gas turbine intercooler heat in a bottoming steam cycle

Номер: US20120159923A1

Автор: Kenneth Charles Bodek, Pierre Sebastien Huck, Richard Bodek, Sebastian Walter Freund, Thomas Johannes Frey

Принадлежит: General Electric Co

A steam cycle power plant includes a gas turbine, a gas turbine intercooler, a steam turbine, and a heat recovery steam generator (HRSG). The gas turbine intercooler recovers unused heat generated via the gas turbine and transfers substantially all of the recovered heat for generating extra steam for driving the steam turbine.

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Номер записи: 2

05-07-2012 дата публикации

Method to maximize lng plant capacity in all seasons

Номер: US20120167619A1

Автор: Robert C. HAVLIK, Stanley H. HUANG

Принадлежит: Chevron USA Inc

As described herein, a method and system for operating a liquefied natural gas (LNG) plant are provided. The method and system also provide for domestic natural gas production. In the present methods and systems, substantially all of the natural gas produced from a well or formation is processed to form LNG; a portion of the LNG produced is regasified; and the regasification is utilized to cool the inlet air to the gas turbines in the LNG plant, either directly or indirectly.

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Номер записи: 3

19-07-2012 дата публикации

Cooled gas turbine engine member

Номер: US20120183386A1

Автор: Mark Owen Caswell

Принадлежит: Rolls Royce North American Technologies Inc

A gas turbine engine is disclosed having a vane disposed in a flow path of a gas turbine engine component, for example a gas turbine engine compressor. The vane is in thermal contact with a heat tube that extends through a wall of the engine component and into a space in which a thermal fluid passes. The thermal fluid can be at a different temperature than the vane such that heat is transferred between the two. In one embodiment the vane forms part of an intercooler for a compressor of the gas turbine engine. The vane can have a fin disposed at the end of the heat tube to facilitate a heat transfer.

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Номер записи: 4

27-12-2012 дата публикации

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

Номер: US20120324904A1

Автор: Chris Pin Harry, Gabriel Taraboulsi, Walter Kasimierz Omielan

Принадлежит: Rolls Royce Power Engineering PLC

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.

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Номер записи: 5

31-01-2013 дата публикации

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

Номер: US20130028707A1

Автор: Erik Boldt, Luis Puerta, Marco Micheli, Wolfgang Kappis

Принадлежит: Alstom Technology AG

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.

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Номер записи: 6

28-02-2013 дата публикации

Variable temperature chiller coils

Номер: US20130048265A1

Автор: Bhalchandra Arun DESAI, Eric Milton LAFONTAINE, Huong Van Vu, Mark Andrew Cournoyer, Michael Adelbert Sullivan

Принадлежит: General Electric Co

A chiller coil system for an asymmetric gas turbine filter house includes a plurality of chiller coil modules arranged in a substantially vertical array, each chiller coil module provided with a cooled fluid inlet pipe and a fluid outlet pipe. Each outlet pipe is connected to a common return pipe and at least some of the inlet pipes are connected to the common return pipe. A mixing control valve is provided for controlling an amount of cooling fluid in the common return pipe to be added to at least some of the inlet pipes.

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Номер записи: 7

28-03-2013 дата публикации

Method of operating a gas turbine and gas turbine

Номер: US20130074511A1

Автор: Edwin Snoeks, Irina Tanaeva

Принадлежит: Individual

A gas turbine system comprises a gas turbine having a low pressure compression stage and a high pressure compression stage, a combustion chamber, and an expansion stage connected to the combustion chamber. The low pressure compression stage and the high pressure compression stage are connected with each other via an intercooling stage, wherein the low pressure compressed air stream from the low pressure compression stage is chilled to an intercooling temperature that is lower than the ambient temperature of the air source from which the air stream was supplied to the low pressure compression stage of the gas turbine.

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Номер записи: 8

09-05-2013 дата публикации

GAS TURBINE ENGINE COMPONENT AXIS CONFIGURATIONS

Номер: US20130111923A1

Автор: Dewis David William, Donnelly Frank Wegner, Swartz Douglas W., Watson John D.

Принадлежит: ICR Turbine Engine Corporation

A method is disclosed to enable the efficient physical packaging of gas turbine engine components to optimize power density, more readily integrate with other equipment and facilitate maintenance. The method illustrates dense packaging of turbomachinery by close-coupling of components, and rotation of various engine components with respect to engines and/or other engine components, and reversal of spool shaft rotational direction to suit the application. Engines can be dense-packed because of a number of features of the basic engine including the use of compact centrifugal compressors and radial inlet turbine assemblies, the close coupling of turbomachinery, the ability to rotate key components to facilitate ducting and preferred placement of other components, the ability to control spool shaft rotational direction and full power operation at high overall pressure ratios. 1. A gas turbine engine , comprising:at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a corresponding radial inlet turbine, wherein a spool axis of rotation for the centrifugal compressor and radial inlet turbine comprise a common shaft;an intercooler positioned in a fluid path between the first and second centrifugal compressors of the first and second turbo-compressor spools;a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the centrifugal compressor of the at least first and second turbo-compressor spools, thereby providing a further heated gas; anda combustor operable to combust a fuel in the presence of the further heated gas, wherein at least one of the following is true:(i) the engine has full power operation at an overall engine compression ratio of about 10:1 to about 20:1;(ii) the combustor is substantially contained within a volume occupied by the recuperator;(iii) in at least one of the ...

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Номер записи: 9

11-07-2013 дата публикации

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

Номер: US20130174549A1

Автор: Fumio Takahashi, Kazuhito Koyama, Kazuo Takahashi, Naoyuki Nagafuchi, Shigeo Hatamiya, Takaaki Sediai

Принадлежит: HITACHI LTD

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.

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Номер записи: 10

12-09-2013 дата публикации

Advanced adiabatic compressed air energy storage system

Номер: US20130232974A1

Автор: Michael Nakhamkin

Принадлежит: Synchrony Inc

A compressed air energy storage (CAES) system is disclosed for the generation of power. The system may include a compressor configured to receive inlet air and output compressed air to an air storage during an off-peak period. During a peak load period, compressed air from the air storage may be released to generate power. A heat exchanger fluidly coupled to the air storage may receive the released compressed air and transfer heat to the compressed air. An air expander may receive the heated compressed air from the heat exchanger, expand the heated compressed air to generate a first power output, and output an exhaust. The system may further include a bypass line configured to circumvent compressed air around the air expander. A second power output may be generated through a turbine configured to receive the compressed air from the air storage and the exhaust from the air expander.

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Номер записи: 11

02-01-2014 дата публикации

Low Emission Turbine Systems Incorporating Inlet Compressor Oxidant Control Apparatus And Methods Related Thereto

Номер: US20140000273A1

Автор: Franklin F. Mittricker, Loren K. Starcher, Omar Angus Sites, Richard A. Huntington, Sulabh K. Dhanuka

Принадлежит: Individual

Systems, methods, and apparatus are provided for controlling the oxidant feed in low emission turbine systems to maintain stoichiometric or substantially stoichiometric combustion conditions. In one or more embodiments, such control is achieved through methods or systems that ensure delivery of a consistent mass flow rate of oxidant to the combustion chamber.

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Номер записи: 12

06-02-2014 дата публикации

Controller for Gas Turbine Power Plant

Номер: US20140033720A1

Автор: Eunkyeong Kim, Kazuhito Koyama, Kazuo Takahashi, Naohiro Kusumi, Shigeo Hatamiya, Takuya Yoshida, Yukinori Katagiri

Принадлежит: HITACHI LTD

A controller for use in a gas turbine power plant includes a compressor that compresses combustion air; a water-atomization cooling apparatus that sprays water drops of atomized water supplied via a water-atomization flow-rate regulating valve over a flow of air drawn in the compressor; a combustor that mixes the compressed combustion air with fuel to thereby burn a fuel-air mixture and generate combustion gas at high temperature and performs combustion switching during operation; a turbine that uses the combustion gas to drive the compressor and a generator; the water-atomization flow-rate regulating valve that controls a flow rate of the atomized water; and a compressor inlet inner blade that controls a flow rate of air drawn in the compressor. The controller includes control means that calculates a fuel-air ratio correction command signal for compensating for reduction in a fuel-air ratio in the combustor occurring during the combustion switching.

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Номер записи: 13

06-02-2014 дата публикации

Atomizer

Номер: US20140034752A1

Автор: AGATA Go, Hatamiya Shigeo, Koyama Kazuhito, KUSUMI Naohiro, MYOREN Chihiro, Sekiai Takaaki, Takahashi Fumio

Принадлежит: Hitachi, Ltd.

In an atomizer constructed to cool inlet air for a gas turbine by spraying fine droplets of water into the inlet air, a spray nozzle is disposed to spray the finely atomized droplets of water from an outer edge of an atomized airstream into a high-speed zone thereof, towards a central region of the airstream. The atomized airstream meets an airstream of a low-speed zone formed at a downstream side, and after the two kinds of airstreams have been mixed and unified, this mixture is supplied to an axisymmetric compressor. Devices such as a feed water pipe and spray nozzle are placed in the low-speed zone so as not to obstruct the airstream. 1. An atomizer constructed to cool inlet air for a gas turbine by spraying fine droplets of water into the inlet air ,wherein a spray nozzle is disposed to spray the finely atomized droplets of water from an outer edge of an atomized airstream into a high-speed zone thereof, towards a central region of the airstream.2. The atomizer according to claim 1 , wherein:the spray nozzle is placed in a low-speed zone formed at rear of a silencer sound absorber; andwhen width of a flow channel across the silencer sound absorber is taken as W and a distance from an outlet of the silencer sound absorber to an atomizing hole of the spray nozzle is taken as L, a relationship of L<2W is established.3. The atomizer according to claim 2 , wherein:the spray nozzle includes a first spray nozzle adapted to spray water into the central region of the high-speed zone of the airstream, and a second spray nozzle adapted to spray water into a peripheral region of the high-speed zone of the airstream.4. The atomizer according to claim 2 , wherein:the spray nozzle is disposed in plurality to spray droplets from a low-speed zone formed at rear of a silencer sound absorber, into adjacent high-speed zones, an independent feed water pipe being connected to each of the spray nozzles.5. The atomizer according to claim 4 , configured so that the amount of water to be ...

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Номер записи: 14

06-03-2014 дата публикации

GAS TURBINE SYSTEM HAVING AN EVAPORATIVE COOLER

Номер: US20140060058A1

Автор: Birkner Jens, David Walter, Gensler Rudolf, Graßmann Arne, Halberstadt Knut, Heimberg Beate, Kocdemir Bora, Nies Rainer, Schürhoff Jörg, Stamm Werner

Принадлежит:

A gas turbine system includes a compressor; a combustion chamber; a gas turbine; and an evaporative cooler. The evaporative cooler includes a plurality of cooling elements, a flow channel, and a feed device. The plurality of cooling elements are arranged in the flow channel. The feed device supplies a liquid to the plurality of cooling elements. The liquid is evaporated or vaporized. Each of the plurality of cooling elements is a flat cooling sheet, a surface of the cooling sheet having hydrophilic properties at least in a subregion which is specified for forming a liquid film. The evaporative cooler is connected ahead of the compressor on an intake side. 1. A gas turbine system , comprising:a compressor;a combustion chamber;a gas turbine; and a plurality of cooling elements,', 'a flow channel, and', 'a feed device;, 'an evaporative cooler, comprisingwherein the plurality of cooling elements are arranged in the flow channel,wherein the feed device supplies a liquid to the plurality of cooling elements,wherein the liquid is evaporated or vaporized, andwherein each of the plurality of cooling elements is a flat cooling sheet, a surface of the cooling sheet having hydrophilic properties at least in a subregion which is specified for forming a liquid film,wherein the evaporative cooler is connected ahead of the compressor on an intake side.2. The gas turbine system as claimed in claim 1 , wherein the plurality of cooling sheets stand vertically and are arranged in a form of a cascade.3. The gas turbine system as claimed in claim 1 , wherein at least one of the plurality of cooling elements comprises a main body including a hydrophilic surface coating.4. The gas turbine system as claimed in claim 1 , wherein a contact angle of the hydrophilic surface is less than 20° relative to the liquid.5. The gas turbine system as claimed in claim 4 , wherein the contact angle of the hydrophilic surface is less than 10°.6. The gas turbine system as claimed in claim 1 , wherein the ...

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Номер записи: 15

01-01-2015 дата публикации

POWER PLANT COMPRISING A CONDENSED WATER RECOVERY DEVICE

Номер: US20150000302A1

Автор: Biagi Fernando Roberto, Marchetti Giorgio, Santini Marco

Принадлежит: NUOVO PIGNONE S.P.A.

A power plant including a thermal machine, an inlet duct for delivering a combustive first fluid in said thermal machine, a ventilation circuit for delivering a cooling second fluid to said thermal machine, the first and/or the second fluid including water therein, and a water recovery device connected with the inlet duct and/or the ventilation circuit for condensing and collecting said water from the first and/or the second fluid, the water recovery device being associated with at least one heat exchanger thermally connected with the inlet duct and/or the ventilation circuit for cooling said first and/or said second fluid beyond the dew point thereof, the water recovery device further including connecting means for delivering the water condensed from the first and/or the second fluid to a water using device. 1. A power plant , comprising:a thermal machine;an inlet duct for delivering a combustive first fluid in the thermal machine;a ventilation circuit for delivering a cooling second fluid to the thermal machine, wherein the first and/or the second fluid comprises water therein; and 'at least one heat exchanger thermally connected with the inlet duct and/or the ventilation circuit for cooling the first and/or the second fluid beyond the dew point; and', 'a water recovery device connected with the inlet duct and/or the ventilation circuit, configured to condense and to collect the water from the first and/or the second fluid, and comprisesa connector for delivering the water condensed from the first and/or the second fluid to a water using device.2. The power plant according to claim 1 , wherein the water recovery device is thermally connected with the ventilation circuit for separating and collecting the water from the second fluid.3. The power plant according to claim 1 , wherein the water using device is of an open-cycle type.4. The power plant according to claim 2 , wherein the water using device comprises:at least one heating element for producing steam from ...

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Номер записи: 16

04-01-2018 дата публикации

Variable geometry thruster

Номер: US20180003128A1

Автор: Andrei Evulet

Принадлежит: Jetoptera Inc

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

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Номер записи: 17

07-01-2021 дата публикации

Systems and Methods for Controlling Liquid Flow to a Turbine Fogging Array

Номер: US20210003077A1

Автор: Ammons Mark, Scoggins Brian, Shepherd Donald W.

Принадлежит:

Methods and apparatus for controlling liquid flow to a turbine fogging array. Some implementations are generally directed toward adjusting the output of a variable output pump that supplies water to the turbine fogging array. In some of those implementations, the output is adjusted based on a determined target pump output value that is indicative of a pump output required to change the moisture content of intake air of a combustion turbine to meet a target humidity value. Some implementations are generally directed toward actuating at least one control valve of a plurality of control valves that control liquid throughput to one or more fogging nozzles of a fogging array. 1. A system for controlling output of a fogging array positioned upstream of a combustion turbine , the system comprising:one or more weather sensors measuring one or more conditions of intake air of the combustion turbine and providing weather sensor data responsive to the measurements, the weather sensor data enabling determination of relative humidity of the intake air;a variable output pump supplying liquid to a fogging array positioned upstream of the combustion turbine, the variable output pump operable at a plurality of speeds;memory storing instructions;a controller receiving the weather sensor data and coupled to a drive for the pump, the controller operable to execute the instructions stored in the memory; identify a target humidity value for the intake air;', 'determine, based on the weather sensor data and the target humidity value, a target pump output value indicative of a pump output required to change the moisture content of the intake air to meet the target humidity value; and', 'adjust the speed for the variable output pump based on the target pump output value., 'wherein the instructions comprise instructions to2. The system of claim 1 , further comprising:a temperature sensor measuring temperature of the liquid and generating temperature sensor data, the temperature sensor ...

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Номер записи: 18

03-01-2019 дата публикации

THERMAL SHIELD FOR GAS TURBINE ENGINE DIFFUSER CASE

Номер: US20190003392A1

Автор: Roberge Gary D.

Принадлежит:

A gas turbine engine comprises a fan delivering air into a bypass duct as bypass air and into a core engine. The core engine includes a high pressure compressor, a combustor, and a turbine section including a fan drive turbine driving a fan rotor through a gear reduction. The high pressure compressor having a downstream most location and air in a chamber radially outward of the combustor being air downstream of the downstream most location in the high pressure compressor. A tap taps compressed air and moves compressed air through a heat exchanger, then returns the compressed air back into a core engine housing and passes the returned air through a conduit radially outwardly of the combustor. The air is passed ng from the conduit radially inwardly to cool the turbine section. 1. A gas turbine engine comprising:a fan delivering air into a bypass duct as bypass air and into a core engine;said core engine including a high pressure compressor, a combustor, and a turbine section including a fan drive turbine driving a fan rotor through a gear reduction;said high pressure compressor having a downstream most location and air in a chamber radially outward of said combustor being air downstream of said downstream most location in said high pressure compressor; anda tap for tapping compressed air and moving compressed air through a heat exchanger, then returning said compressed air back into a core engine housing and passing the returned air through a conduit radially outwardly of said combustor, and said air passing from said conduit radially inwardly to cool said turbine section.2. The gas turbine engine as set forth in claim 1 , wherein said tap is from a location downstream of said downstream most location in said high pressure compressor.3. The gas turbine engine as set forth in claim 2 , wherein said heat exchanger is placed in the bypass duct with the bypass air cooling the tapped air in said heat exchanger.4. The gas turbine engine as set forth in claim 3 , wherein ...

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Номер записи: 19

03-01-2019 дата публикации

GAS TURBINE ENGINE WITH THERMOELECTRIC INTERCOOLER

Номер: US20190003393A1

Автор: DIERKSMEIER DOUGLAS D., Karam Michael A., Vetters Daniel K.

Принадлежит:

A gas turbine engine includes a compressor, a cooling source, and a thermoelectric intercooler adapted for selective operation in response to operational states of the gas turbine engine. 1. A gas turbine engine for generating drive from combustion of fuel , comprisinga compressor including a plurality of rotating stages each adapted to compress air,a cooling source adapted to provide coolant to the compressor of the gas turbine engine, anda thermoelectric intercooler located axially between rotating stages of the compressor along a central engine axis, the thermoelectric intercooler including a compressed air passageway fluidly coupled to the compressor to pass compressed air of the compressor therethrough, a coolant passageway fluidly coupled to the cooling source to pass coolant of the cooling source therethrough, and a thermoelectric section configured in thermal communication with each of the compressed air passageway and the coolant passageway,wherein the thermoelectric section is disposed between the compressed air passageway and the coolant passageway.2. The gas turbine engine of claim 1 , further comprising a controller configured to determine an operational state of the gas turbine engine and to selectively apply voltage across the thermoelectric section based on the operational state of the gas turbine engine.3. The gas turbine engine of claim 2 , wherein the cooling source is one of a fuel system of the gas turbine engine and a cooling air stream.4. The gas turbine engine of claim 2 , wherein the gas turbine engine is configured to provide propulsion for an aircraft and the operational state of the gas turbine engine includes one of ground idle claim 2 , takeoff claim 2 , climb claim 2 , cruise claim 2 , and flight idle.5. The gas turbine engine of claim 4 , wherein the controller is configured to apply voltage across the thermoelectric section to direct current through the thermoelectric section in a first direction in response to determination that the ...

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Номер записи: 20

14-01-2016 дата публикации

METHOD AND SYSTEM FOR POWER PRODUCTION WTIH IMPROVED EFFICIENCY

Номер: US20160010551A1

Автор: Allam Rodney John, Fetvedt Jeremy Eron, Forrest Brock Alan

Принадлежит:

The present disclosure relates to systems and methods that provide power generation using predominantly COas a working fluid. In particular, the present disclosure provides for the use of a portion of the heat of compression from a COcompressor as the additive heating necessary to increase the overall efficiency of a power production system and method. 1. A method for heating a recirculating gas stream comprising:{'sub': 1', '1', '2', '1, 'passing a gas stream G at a pressure Pand a temperature Tthrough a recuperative heat exchanger such that the gas stream is cooled to a temperature Tthat is less than T;'}{'sub': 1', '2, 'separating the gas stream G into a first fraction Gand a second fraction G;'}{'sub': 1', '2', '1, 'compressing the gas stream fraction Gto a pressure Pthat is greater than P;'}{'sub': 2', '3', '1', '2', '3', '2, 'compressing the gas stream fraction Gto a pressure Pthat is greater than Pso as to heat the gas stream fraction Gto a temperature Tthat is greater than T;'}{'sub': '2', 'withdrawing the heat from the compressed gas stream fraction G;'}{'sub': 1', '2', 'C, 'combining the gas stream fraction Gand the gas stream fraction Gto form a combined recirculating gas stream G;'}{'sub': C', '4', '2', '3, 'pumping the recirculating gas stream Gto a pressure Pthat is greater than Pand greater than P; and'}{'sub': C', 'C, 'passing the recirculating gas stream Gto the recuperative heat exchanger such that the gas stream Gis heated by the cooling gas stream G;'}{'sub': 2', 'C', '4, 'wherein the heat withdrawn from the compressed gas stream fraction Gis added to the recirculating gas stream Gafter pumping to pressure P.'}2. The method according to claim 1 , wherein the temperature Tis about 100° C. to about 400° C.3. The method according to claim 1 , wherein the pressure Pof gas stream fraction Gand the pressure Pof gas stream fraction Gare each separately about 40 bar (4 MPa) to about 100 bar (10 MPa).4. The method according to claim 1 , wherein the ...

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Номер записи: 21

14-01-2021 дата публикации

SCROLL AND GAS TURBINE FACILITY

Номер: US20210010422A1

Автор: Itoh Masao, Iwai Yasunori, KASUYA Hiroki, MORISAWA Yuichi

Принадлежит: TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION

An entire scroll is effectively cooled. A scroll of an embodiment leads combustion gas to a turbine stage as a working medium for driving a turbine rotor in a gas turbine facility, and includes a scroll inner cylinder and a scroll outer cylinder. The working medium flows into the scroll inner cylinder. The scroll outer cylinder is provided to cover the scroll inner cylinder with a scroll cooling flow path therebetween where a cooling medium with a temperature lower than the working medium is supplied. The scroll cooling flow path includes an inner ring side flow path part located inside than the scroll inner cylinder in a radial direction of the turbine rotor and an outer ring side flow path part located outside than the scroll inner cylinder in the radial direction of the turbine rotor. Here, a dividing part dividing the outer ring side flow path part in an axial direction along a rotation axis of the turbine rotor is provided at the scroll inner cylinder. 1. A scroll which leads combustion gas to a turbine stage as a working medium for driving a turbine rotor in a gas turbine facility , the scroll comprising:a scroll inner cylinder into which the working medium flows; anda scroll outer cylinder which is provided to cover the scroll inner cylinder with a scroll cooling flow path where a cooling medium with a temperature lower than the working medium is supplied between the scroll inner cylinder and the scroll outer cylinder, whereinthe scroll cooling flow path includes:an inner ring side flow path part located on an inner side than the scroll inner cylinder in a radial direction of the turbine rotor; andan outer ring side flow path part located on an outer side than the scroll inner cylinder in the radial direction of the turbine rotor, and whereina dividing part which divides the outer ring side flow path part in an axial direction along a rotation axis of the turbine rotor is provided at the scroll inner cylinder.2. The scroll according to claim 1 , whereinthe ...

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Номер записи: 22

17-01-2019 дата публикации

GAS TURBINE COMPRISING A WET COMPRESSION DEVICE FOR INTRODUCING A SURFACTANT LIQUID MIXTURE

Номер: US20190017411A1

Автор: Hülsemann Gerhard, Savilius Nicolas

Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A gas turbine having a wet compression device which allows droplets of an aqueous liquid mixture to be introduced into a compressor of the gas turbine during operation of the gas turbine, the aqueous liquid mixture containing at least one surfactant. The aqueous liquid mixture additionally contains at least a defoaming agent, and the gas turbine has a second metering device, which is designed to feed a predetermined quantity of defoaming agent into water which is provided for use in the wet compression device. 17.-. (canceled)8. A gas turbine comprising:a wet compression device, by means of which an aqueous liquid mixture in droplet form containing at least one surfactant is introduced into a compressor of the gas turbine during the operation of the gas turbine, wherein the aqueous liquid mixture additionally contains at least a defoaming agent, anda second metering device, which is designed to feed a predetermined quantity of defoaming agent into water which is provided for use in the wet compression device.9. The gas turbine as claimed in claim 8 , further comprising:a first metering device, which is designed to feed a predetermined quantity of surfactant into water which is provided for use in the wet compression device.10. The gas turbine as claimed in claim 8 ,wherein the at least one surfactant is selected from the following group of surfactants: polyalkylene glycol ether, polysorbate20, alkyl polyglycosides.11. The gas turbine as claimed in claim 8 ,wherein the at least one defoaming agent is selected from the following group of defoaming agents: tri-n-butyl phosphate, monoglycerides, diglycerides.12. A method for operating a gas turbine as claimed in claim 8 , comprising:feeding the aqueous liquid mixture to the wet compression device. This application is the US National Stage of International Application No. PCT/EP2016/077126 filed Nov. 9, 2016, and claims the benefit thereof. The International Application claims the benefit of German Application No. DE ...

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Номер записи: 23

23-01-2020 дата публикации

DIVERSION OF FAN AIR TO PROVIDE COOLING AIR FOR GAS TURBINE ENGINE

Номер: US20200025080A1

Автор: Bifulco Anthony R., Kupratis Daniel Bernard

Принадлежит:

A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages. 1. A gas turbine engine section comprising:a plurality of spaced rotor stages, with a static guide vane intermediate said spaced rotor stages, said static guide vane providing swirl into air passing toward a downstream one of said spaced rotor stages, and an outer housing surrounding said spaced rotor stages, a diverter diverting a portion of air radially outwardly through said outer housing, and across at least one heat exchanger, with the diverted air passing back into a duct radially inwardly through said outer housing, and being exhausted toward said downstream one of said spaced rotor stages.2. The gas turbine engine as set forth in claim 1 , wherein said exhausted air passing through an injector claim 1 , and said injector imparting swirl into the air exhausting toward the downstream one of the two spaced turbine rotors.3. The gas turbine engine as set forth in claim 2 , wherein a swirl angle imparted by said injector is greater than a swirl angle imparted by said static guide vane.4. The gas turbine engine as set forth in claim 3 , wherein a swirl angle imparted by said static guide vane is greater than 40 degrees.5. The gas turbine engine as set forth in claim 4 , wherein said swirl angle is greater than 55 degrees.6. The gas turbine engine as set forth in claim 1 , wherein said at least one heat exchanger cooling an electronic component.7. The gas turbine engine as set forth in claim 1 , ...

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Номер записи: 24

23-01-2020 дата публикации

MICROCHANNEL HEAT EXCHANGERS FOR GAS TURBINE INTERCOOLING AND CONDENSING

Номер: US20200025084A1

Автор: Dejulio Emil R., LOEBIG James C.

Принадлежит:

A microchannel heat exchanger (MCHX) includes an air-passage layer including a plurality of air-passage microchannels, a working fluid layer including a plurality of working fluid microchannels, and a sealing layer coupled to the working fluid layer to provide a working/sealing layer set. The working/sealing layer set includes an arrangement of raised pedestals. The raised pedestals may extend from the working fluid layer to the sealing layer and contact the sealing layer. 1. A microchannel heat exchanger , comprising:an air-passage layer including a plurality of air-passage microchannels structured and arranged to convey an air stream in a first direction;a working fluid layer including a plurality of working fluid microchannels structured and arranged to convey a working fluid in a second direction opposite to the first direction, an internal intake manifold disposed at an inlet of the plurality of working fluid microchannels, and an internal outtake manifold disposed at an outlet of the plurality of working fluid microchannels;a sealing layer coupled to the working fluid layer to provide a working/sealing layer set; andwherein the working/sealing layer set includes an arrangement of raised pedestals disposed in the internal intake manifold and the internal outtake manifold, and wherein the arrangement of raised pedestals comprises raised pedestals that extend from the working fluid layer to the sealing layer and contact the sealing layer.2. The microchannel heat exchanger of claim 1 , wherein the plurality of air-passage microchannels are disposed on a first side of the air-passage layer and on a second side of each air-passage layer of the plurality of air-passage layers claim 1 , and wherein the first side is opposite the second side.3. The microchannel heat exchanger of claim 1 , wherein the plurality of air-passage microchannels converge at an end of the air-passage layer.4. The microchannel heat exchanger of claim 1 , wherein the plurality of air-passage ...

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Номер записи: 25

23-01-2020 дата публикации

Intercooled cooling air with auxiliary compressor control

Номер: US20200025105A1

Автор: Brian D. Merry, Gabriel L. Suciu, Michael G. Mccaffrey

Принадлежит: United Technologies Corp

A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

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Номер записи: 26

05-02-2015 дата публикации

SYSTEM AND METHOD FOR A WATER INJECTION SYSTEM

Номер: US20150033751A1

Автор: Andrew Philip Lynn

Принадлежит:

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 ...

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Номер записи: 27

30-01-2020 дата публикации

Combustion device and gas turbine engine system

Номер: US20200032712A1

Автор: MASAHIRO Uchida, Shintaro Ito, Shogo Onishi, Soichiro Kato, Taku Mizutani, Toshiro Fujimori, Tsukasa Saitou

Принадлежит: IHI Corp

The combustion device includes: a compressor that compresses combustion air; a combustor that combusts the compressed combustion air and fuel ammonia; and an ammonia injector that injects the fuel ammonia into the combustion air during or before compression of the combustion air by the compressor and cools the combustion air.

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Номер записи: 28

04-02-2021 дата публикации

Plant control apparatus, plant control method and power plant

Номер: US20210033025A1

Автор: Ibrahim ABDURRAHMAN, Masayuki Tobo, Toyohiro Akebi, Yusuke FUKAMACHI

Принадлежит: Toshiba Corp, Toshiba Energy Systems and Solutions Corp

In one embodiment, a plant control apparatus controls a power plant. The apparatus includes a gas turbine, an exhaust heat recovery boiler to generate main steam, a first steam turbine driven by first steam, and a first valve to supply the first steam to the first steam turbine. The plant further includes a reheater to generate reheat steam, a second steam turbine driven by second steam, and second and third valves to supply the second steam to the second steam turbine. The apparatus includes an acquisition module to acquire a setting value of total output of the first and second steam turbines, and a control module to adjust the total output to the setting value by controlling opening degrees of the first, second and third valves. The control module controls the second and third valves to different opening degrees when adjusting the total output to the setting value.

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Номер записи: 29

08-02-2018 дата публикации

SYSTEMS AND METHODS FOR SELECTIVELY AUGMENTING POWER OUTPUT OF A GAS TURBINE ENGINE

Номер: US20180038281A1

Автор: Eifert Andrew J.

Принадлежит: Rolls -Royce North American Technologies, Inc.

Systems and methods for augmenting power output when operating a load having relatively brief periods of high energy demand and high heat generation. A system comprises a gas turbine engine including a coolant injection assembly, an electrical generator coupled to the gas turbine engine, a high-energy operating load coupled to the electrical generator, and a cooling system adapted to provide cooling to the high-energy operating load. The cooling system is coupled and adapted to provide coolant to the coolant injection assembly of the gas turbine engine. A method comprises coupling the cooling system to the coolant injection assembly at the inlet of the gas turbine engine, selectively diverting at least a portion of the coolant of the cooling system to the coolant injection assembly, and spraying the diverted coolant into air entering the gas turbine engine. 1. A system for augmenting power output when operating a load having relatively brief periods of high energy demand and high heat generation , the system comprising:a gas turbine engine including a coolant injection assembly, a compressor, a combustor, and a turbine;an electrical generator coupled to the gas turbine engine;at least one high-energy operating load coupled to the electrical generator;a cooling system adapted to provide cooling to the at least one high-energy operating load;wherein the cooling system is coupled and adapted to provide coolant to the coolant injection assembly of the gas turbine engine.2. The system of claim 1 , wherein said cooling system is adapted to selectively provide coolant during periods of high energy demand and high heat generation of the operating load.3. The system of wherein the coolant injection assembly comprises a plurality of nozzles in fluid communication with the cooling system claim 2 , the plurality of nozzles disposed circumferentially about and upstream of an inlet of the gas turbine engine.4. The system of further comprising a coolant mixer disposed between the ...

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Номер записи: 30

07-02-2019 дата публикации

FULL TURBOMACHINERY MODULE FOR LNG PLANTS OR THE LIKE

Номер: US20190041127A1

Автор: CECARINI Michele, GIANCOTTI Marco, GUIDOTTI Luciano, RIGHESCHI Andrea

Принадлежит:

A modular gas turbine system is disclosed. The system includes a base plate and a gas turbine engine mounted on the base plate. The gas turbine engine is drivingly coupled to a rotating load mounted on the base plate. A supporting frame extends above the base plate. A first bridge crane and a second bridge crane are movably supported on the supporting frame. 1. A transportable modular gas turbine system , comprising:a base plate;a gas turbine engine having a rotation axis, mounted on the base plate;at least one rotating load, mechanically coupled to the gas turbine engine and mounted on the base plate;a supporting frame extending above the base plate;a first bridge crane movably supported on the supporting frame;a second bridge crane movably supported on the supporting frame.2. The modular gas turbine system of claim 1 , wherein the first bridge crane and the second bridge crane are movable on common rails mounted on the supporting frame.3. The modular gas turbine system of claim 1 , wherein at least one of the first bridge crane and second bridge crane is movable on rails extending substantially parallel to a rotation axis of the gas turbine engine.4. The modular gas turbine system of claim 1 , wherein the first bridge crane is movable along first rails extending substantially parallel to the rotation axis of the gas turbine engine and the second bridge crane is movable along second rails extending substantially orthogonal to the rotation axis of the gas turbine engine.5. The modular gas turbine system of claim 1 , wherein at least one of said first bridge crane and second bridge crane is movable on first rails extending substantially parallel to the rotation axis of the gas turbine engine and projecting horizontally beyond the footprint of the base plate claim 1 , up to a lay down area arranged on a side of the base plate.6. The modular gas turbine system of claim 1 , wherein the first bridge crane has a lifting capacity higher than the second bridge crane.7. The ...

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Номер записи: 31

06-02-2020 дата публикации

SYSTEMS AND METHODS FOR POWER GENERATION WITH FLAMELESS COMBUSTION

Номер: US20200040817A1

Автор: Fetvedt Jeremy Eron, Forrest Brock Alan

Принадлежит:

The present disclosure provides systems and methods wherein power production can be achieved with combustion of a fuel utilizing flameless combustion. A fuel may be combusted in a combustor/turbine in a substantially flameless operation to produce a combustion product stream that can be expanded for power generation. After expansion, the output stream can be treated to generate a recycle COstream into which an oxidant can be input. The recycle COstream including the oxidant can be injected into the combustor/turbine to effect combustion in a substantially flameless state. Various control schemes can be implemented to automatically control the concentration of oxygen present in the recycle COstream that is injected into the combustor/turbine in order to achieve and/or maintain substantially flameless combustion. 1. A method for power generation , the method comprising:{'sub': '2', 'providing a recycle stream comprising CO;'}{'sub': 2', '2', '2, 'adding an oxidant to the recycle stream comprising COsuch that the recycle stream comprising COfurther includes the oxidant in an amount of about 2% to about 15% by mass based on the total mass of the recycle stream comprising CO;'}{'sub': '2', 'injecting the recycle stream comprising COand including the oxidant into a combustion turbine with a fuel to cause combustion of the fuel and formation of a combustion product stream; and'}generating power by expanding the combustion product stream in the combustion turbine.2. The method of claim 1 , wherein the combustion of the fuel is substantially flameless.3. The method of claim 1 , further comprising heating the recycle stream comprising COand including the oxidant to a temperature in the range of about 400° C. to about 2000° C. prior to injecting into the combustion turbine.4. The method of claim 3 , wherein heating the recycle stream comprising COand including the oxidant comprises passing the recycle stream comprising COand including the oxidant through a recuperative heat ...

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Номер записи: 32

19-02-2015 дата публикации

COMPOSITE HEAT EXCHANGER

Номер: US20150047367A1

Автор: Benignos Jorge Carretero

Принадлежит: GENERAL ELECTRIC COMPANY

A heat exchanger assembly in one embodiment includes an inlet, an outlet, and a core. The inlet is configured to accept a fluid to be cooled and the outlet is configured to provide an exit for a flow of the fluid that has been cooled. The core includes at least one passageway formed therein configured for passage of the fluid to be cooled from the inlet to the outlet. The core also includes a receiving surface configured to receive a cooling flow therethrough. The core is configured to direct the cooling flow to pass by at least a portion of the at least one passageway to cool the fluid. The core is comprised of a high temperature geopolymer composite material. The composite material may be configured for use at temperatures above about 300 degrees Celsius, and may have a thermal conductivity below about 20 Watts/(meter*degree Kelvin). 1. A heat exchanger assembly comprising:an inlet configured to accept a fluid to be cooled;an outlet configured to provide an exit for a flow of the fluid that has been cooled; and at least one passageway formed therein configured for passage of the fluid to be cooled from the inlet to the outlet; and', 'a cooling surface configured to receive a cooling flow therethrough, the core configured to direct the cooling flow to pass by at least a portion of the at least one passageway to cool the fluid,', 'wherein the core is comprised of a high temperature geopolymer composite material, the high temperature geopolymer composite material configured for use at temperatures above about 300 degrees Celsius, the high temperature geopolymer composite material having a thermal conductivity below about 20 Watts/(meter*degree Kelvin)., 'a core, the core comprising2. The assembly of claim 1 , wherein the inlet is configured to accept a flow of air to be cooled and wherein the cooling surface is configured for passage therethrough of a cooling air flow claim 1 , wherein the assembly is configured for an air-to-air heat exchange.3. The assembly of ...

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Номер записи: 33

15-02-2018 дата публикации

INTAKE AIR COOLING METHOD, INTAKE AIR COOLING DEVICE EXECUTING SAID METHOD, AND WASTE HEAT RECOVERY FACILITY AND GAS TURBINE PLANT EACH COMPRISING SAID INTAKE AIR COOLING DEVICE

Номер: US20180045080A1

Автор: HISADA Naoki, Ito Eisaku, SUGISHITA Hideaki, Uechi Hideyuki

Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

An intake air cooling device includes a water supply line and a heat pump device. The water supply line sends water to a waste heat recovery boiler which generates steam using heat of an exhaust gas from a gas turbine. The heat pump device transfers heat of air suctioned by the gas turbine to water flowing through the water supply line and thereby cools the air while heating the water. 122-. (canceled)23. An intake air cooling device comprising:a water supply line which sends water to a waste heat recovery boiler which converts the water into steam using heat of an exhaust gas exhausted from a gas turbine;a heat pump device which transfers heat of air suctioned by the gas turbine to water flowing through the water supply line and thereby cools the air while heating the water; anda supply water temperature adjusting device, which lowers temperature of preheated water which is water flowing through a preheated water supply line on the waste heat recovery boiler side with respect to the heat pump device, in the water supply line.24. The intake air cooling device according to claim 23 , wherein the supply water temperature adjusting device includes:a supply water temperature adjuster which takes heat away from the preheated water; anda water supply temperature adjusting line which guides the preheated water to the supply water temperature adjuster and returns the preheated water from which heat has been taken away by the supply water temperature adjuster to any place in the water supply line.25. The intake air cooling device according to claim 24 , wherein the supply water temperature adjusting device includes:a thermometer which determines a temperature of the water flowing through the preheated water supply line; anda temperature adjusting valve which flows water from the preheated water supply line to the water supply temperature adjusting line when the temperature of the water determined by the thermometer is equal to or higher than a predetermined temperature.26. ...

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Номер записи: 34

08-05-2014 дата публикации

GAS TURBOMACHINE SYSTEM INCLUDING AN INLET CHILLER CONDENSATE RECOVERY SYSTEM

Номер: US20140123623A1

Автор: John Joseph, Mazumder Indrajit, Pemmi Bhaskar

Принадлежит: GENERAL ELECTRIC COMPANY

A gas turbomachine system includes a compressor portion including an inlet portion, a turbine portion fluidically connected to, and mechanically linked with, the compressor portion, and a combustor assembly including at least one combustor fluidically connected to the turbine portion. An inlet system is fluidically connected to the inlet portion of the compressor portion. The inlet system includes an inlet chiller. An inlet chiller condensate recovery system is fluidically connected to the inlet system. The inlet chiller condensate recovery system includes an inlet fluidically connected to the inlet chiller and an outlet fluidically connected to one of the compressor portion and the combustor assembly. 1. A gas turbomachine system comprising:a compressor portion including an inlet portion;a turbine portion fluidically connected to, and mechanically linked with, the compressor portion;a combustor assembly including at least one combustor fluidically connected to the turbine portion;an inlet system fluidically connected to the inlet portion of the compressor portion, the inlet system including an inlet chiller; andan inlet chiller condensate recovery system fluidically connected to the inlet system, the inlet chiller condensate recovery system fluidically connected to the inlet chiller and one of the compressor portion and the combustor assembly.2. The gas turbomachine according to claim 1 , wherein the inlet chiller condensate recovery system includes a storage tank including an inlet fluidically connected to the inlet chiller and an outlet fluidically connected to the one of the compressor portion and the combustor assembly.3. The gas turbomachine system according to claim 2 , wherein the storage tank includes a de-ionizer.4. The gas turbomachine system according to claim 2 , further comprising:a pump including an inlet portion fluidically connected to the storage tank and an outlet portion configured and disposed to guide inlet chiller condensate from the storage ...

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Номер записи: 35

14-02-2019 дата публикации

WASTE HEAT RECOVERY CASCADE CYCLE AND METHOD

Номер: US20190048747A1

Автор: AMIDEI Simone, AUCIELLO Jury, CAPODANNO Stefano, DEL TURCO Paolo

Принадлежит:

A power conversion system including a first working fluid circuit and a second working fluid circuit. Heat, e.g. waste heat from a top, high-temperature thermodynamic cycle, is transferred to working fluid circulating in the first working fluid circuit and expanded in a first expander to generate useful mechanical power. A heat transfer arrangement is provided, between the first working fluid circuit and second working fluid circuit, configured for transferring low-temperature heat from the first working fluid circuit to the second working fluid circuit. In the second working fluid circuit working fluid is processed, which is expanded in at least one expander to generate useful mechanical power which is used to power a pump or compressor of the first working fluid circuit. The heat of the expanded gas is further used in a second recuperator to pre-heat the first working fluid. 1. A power conversion system comprising:a first working fluid circuit having a high pressure side and a low pressure side and configured to flow a first working fluid therethrough;a heater configured to circulate the first working fluid in heat exchange relationship with a heat source to vaporize the first working fluid;a first expander arranged between the high pressure side and the low pressure side of the first working fluid circuit, configured to expand the first working fluid therein and generate mechanical power therewith;a first pump or compressor arranged between the low pressure side and the high pressure side of the first working fluid circuit;a second working fluid circuit having a high pressure side and a low pressure side and configured to flow a second working fluid therethrough;a heat transfer arrangement-, configured for transferring heat from the low pressure side of the first working fluid circuit to the high pressure side of the second working fluid circuit and vaporize the second working fluid;an expander arrangement arranged between the high pressure side and the low ...

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Номер записи: 36

22-02-2018 дата публикации

Low Rotor Boost Compressor for Engine Cooling Circuit

Номер: US20180051628A1

Автор: Roberge Gary D.

Принадлежит:

A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor. The high pressure compressor has a downstream most location. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor and a heat exchanger, which passes the air back to a location to be cooled. The boost compressor is driven by a shaft which drives the lower pressure compressor. 1. A gas turbine engine comprising:a compressor section having a low pressure compressor and a high pressure compressor, and said high pressure compressor having a downstream most location;a cooling air system including a tap from a location upstream of said downstream most location, said tap passing air to a boost compressor and a heat exchanger; andsaid boost compressor passing the air back to a location to be cooled, and said boost compressor being driven by a shaft which drives said lower pressure compressor.2. The gas turbine engine as set forth in claim 1 , wherein said boost compressor is located in a tail cone of said engine.3. The gas turbine engine as set forth in claim 2 , wherein an output of said boost compressor delivers cooling air to a chamber outside of a combustor.4. The gas turbine engine as set forth in claim 2 , wherein said heat exchanger includes a first heat exchanger positioned between said tap and said boost compressor and a second heat exchanger is positioned between said boost compressor and said output.5. The gas turbine engine as set forth in claim 4 , wherein said boost compressor is driven directly by said shaft.6. The gas turbine engine as set forth in claim 4 , wherein a speed increasing gearbox is positioned between said shaft and said boost compressor.7. The gas turbine engine as set forth in claim 6 , wherein a clutch selectively disconnects said boost compressor from said shaft.8. The gas turbine engine as set forth in claim 7 , wherein said clutch is located between ...

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Номер записи: 37

22-02-2018 дата публикации

System and Method to Integrate Condensed Water with Improved Cooler Performance

Номер: US20180051929A1

Автор: Michael T. MATHEIDAS, Paul W. Sibal, Richard A. Huntington

Принадлежит: Individual

A method and system for cooling a process fluid is disclosed. An inlet air stream of a turbine is cooled with an inlet air cooling system. Moisture contained in the cooled inlet air stream is condensed and separated from the cooled inlet air stream to produce a water stream in an open-loop circuit. The water stream is sprayed into an air cooler air stream. The combined air cooler air stream and sprayed water stream is directed through an air cooler. Heat is exchanged between the process fluid and the combined air cooler air stream and sprayed water stream to thereby condense, chill, or sub-cool the process fluid.

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Номер записи: 38

10-03-2022 дата публикации

Thermal Storage in Pressurized Fluid for Compressed Air Energy Storage Systems

Номер: US20220074547A1

Автор: Lewis Cameron, McGillis Andrew, Stradiotto Daniel, Young Davin

Принадлежит:

A thermal storage subsystem may include at least a first storage reservoir configured to contain a thermal storage liquid at a storage pressure that is greater than atmospheric pressure. A liquid passage may have an inlet connectable to a thermal storage liquid source and configured to convey the thermal storage liquid to the liquid reservoir. A first heat exchanger may be provided in the liquid inlet passage and may be in fluid communication between the first compression stage and the accumulator, whereby thermal energy can be transferred from a compressed gas stream exiting a gas compressor/expander subsystem to the thermal storage liquid. 2. The compressed gas energy storage system of claim 1 , wherein the thermal storage liquid is heated to a storage temperature prior to entering the first storage reservoir claim 1 , wherein the storage temperature is below a boiling temperature of the thermal storage liquid when at the storage pressure and is the above boiling temperature of the thermal storage liquid when at atmospheric pressure.3. The compressed gas energy storage system of claim 2 , wherein the storage temperature is between about 150 degrees Celsius and about 350 degrees Celsius.4. The compressed gas energy storage system of claim 1 , wherein the compressed gas within the accumulator is at an accumulator pressure claim 1 , and wherein the storage pressure is equal to or greater than the accumulator pressure and wherein the storage pressure is between about 100% and about 200% of the accumulator pressure and is between about 20 bar and about 60 bar.5. The compressed gas energy storage system of claim 1 , wherein the first storage reservoir comprises a pressurized layer of cover gas above the thermal storage liquid.6. The compressed gas energy storage system of claim 5 , wherein the layer of cover gas is formed by the boiling of a portion of the thermal storage liquid within the first storage reservoir whereby the layer of cover gas is pressurized to the ...

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Номер записи: 39

21-02-2019 дата публикации

MODULAR GAS TURBINE SYSTEM

Номер: US20190055887A1

Автор: CECARINI Michele, GIANCOTTI Marco, GUIDOTTI Luciano, RIGHESCHI Andrea

Принадлежит:

A modular gas turbine system is disclosed. The system includes a base plate and a gas turbine engine mounted on the base plate. The gas turbine engine has a rotation axis, a first air compressor section and a second air compressor section. A rotating load is mechanically coupled to the gas turbine engine and mounted on the base plate. A supporting frame extends above the base plate and supports a plurality of secondary coolers, which are fluid exchange relationship with an intercooler of the gas turbine engine. 1. A modular gas turbine system , comprising:a base plate;mounted on the base plate, a gas turbine engine having a rotation axis, a first air compressor section and a second air compressor section;at least one rotating load, mechanically coupled to the gas turbine engine and mounted on the base plate;a supporting frame extending above the base plate;an air intercooler, fluidly coupled to the first air compressor section and second air compressor section; the air intercooler configured and arranged for cooling partly compressed air from the first air compressor section in heat exchange relationship with a heat removal fluid;wherein a plurality of secondary coolers are arranged on the supporting frame at a height above the base plate, preferably on the supporting frame at a level above at least one of the gas turbine engine and the load, and are in fluid exchange relationship with the intercooler, the heat removal fluid being in heat exchange relationship with a cooling medium in the secondary coolers.2. The modular gas turbine system of claim 1 , wherein the secondary coolers are air coolers claim 1 , and wherein the heat removal fluid is in heat exchange relationship with cooled ambient air in said secondary coolers.3. The modular gas turbine system of claim 1 , further comprising at least one lube oil cooler arranged on the supporting frame.4. The modular gas turbine system of claim 3 , wherein the lube oil cooler is arranged at the same level as the ...

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Номер записи: 40

01-03-2018 дата публикации

SYSTEM FOR PRODUCING ENERGY OR TORQUE

Номер: US20180058461A1

Автор: Potteau Sêbastien

Принадлежит: VALEO SYSTEMES DE CONTROLE MOTEUR

The invention relates to a system () for producing energy or torque, comprising: a generator designed so as to generate energy or torque from a gas introduced at an admission of the generator; at least two compressors () for compressing the gas at the admission of the generator; and a pipeline system () in which the pipes (Ce, Cs) are designed such that they can be opened or closed in order to selectively place said compressors () in series or in parallel. 1. A system for producing energy or torque , comprising:a generator configured to generate energy or torque from a gas fed into an intake of the generator;at least two compressors for the gas at the intake of the generator; anda ducting system in which ducts are opened or closed to selectively arrange said compressors in series or in parallel.2. The system as claimed in claim 1 , wherein:the gas inlet of each compressor is linked to a respective first duct for bringing gas into said compressor, the first ducts being linked to a shared gas intake duct, at least one gas guiding device being configured to control the flow rate between the shared gas intake duct and at least one of the first ducts,the gas outlet of each compressor is linked to a respective second duct for taking gas out of said compressor, the second ducts being linked to a shared gas outlet duct, at least one gas guiding device being designed configured to control the flow rate between at least one of the second ducts and the shared gas outlet duct.3. The system as claimed in claim 1 , wherein a third duct links the gas outlet of one of the compressors to the gas inlet of the other compressor claim 1 , a gas guiding device being arranged in said duct to prevent or enable the flow of gas in the third duct such as to selectively arrange the two compressors in series or otherwise.4. The system as claimed in claim 3 , wherein the third duct includes a heat exchanger designed configured to cool the incoming gas in the compressor located downstream.5. The ...

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Номер записи: 41

12-03-2015 дата публикации

Method of cooling a gas turbine engine

Номер: US20150068213A1

Автор: Ariel Harter Lomas, Bradley Steven Carey, George Jason Kaliope, Kevin Michael Elward, Richard Francis Gutta

Принадлежит: General Electric Co

A method of cooling a gas turbine engine is provided. The method includes removing a load from the gas turbine engine. The method also includes operating the gas turbine engine at a rated speed of the gas turbine engine. The method further includes modulating an angle of at least one stage of inlet guide vanes disposed proximate an inlet of a compressor section of the gas turbine engine, wherein modulating the angle modifies a flow rate of an inlet flow for reducing a cooling time of the gas turbine engine.

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Номер записи: 42

10-03-2016 дата публикации

Gas turbine engine with turbine cooling and combustor air preheating

Номер: US20160069264A1

Автор: Brostmeyer Joseph D., Cejka Justin T., Downs James P.

Принадлежит:

A gas turbine engine, especially an industrial gas turbine engine for electrical power production, where a second compressor is used to supply a second compressed air at a higher pressure to a stage of stator vanes in the turbine section of the engine for cooling of the stage of stator vanes, and where the heated compressed air used to cool the stator vanes is then discharged into the combustor to be burned with a fuel and produce a hot gas stream that is passed through the turbine. an intercooler can be used with the second compressor to lower the temperature of the second compressed air used for cooling the stator vanes. 1. An industrial gas turbine engine comprising:a first compressor to produce a first compressed air with a first pressure;a combustor to receive the first compressed air from the first compressor to burn with a fuel to produce a hot gas stream;a turbine rotatably connected to the first compressor to receive the hot gas stream from the combustor;the turbine having a stator vane with a cooling circuit;a second compressor to produce a second compressed air with a second pressure;a first passage to pass the second compressed air from the second compressor to the cooling circuit of the stator vane;a second passage to pass the second compressed air from the turbine stator vane to the combustor; and,the second pressure is greater than the first pressure.2. The industrial gas turbine engine of claim 1 , and further comprising:the second compressor includes an intercooler to lower a temperature of the second compressed air.3. The industrial gas turbine engine of claim 1 , and further comprising:an inlet to the second compressor is connected to a lower stage of the first compressor; and,an intercooler is located between the first compressor and the second compressor to lower a temperature of the second compressed air.4. The industrial gas turbine engine of claim 1 , and further comprising:a heat recovery steam generator to receive exhaust from the turbine ...

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Номер записи: 43

08-03-2018 дата публикации

INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER

Номер: US20180066587A1

Автор: Chandler Jesse M., Lord Wesley K., Merry Brian D., Staubach Joseph Brent, Suciu Gabriel L.

Принадлежит:

A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed. 120.-. (canceled)21. An intercooling system for a gas turbine engine comprising:a heat exchanger for cooling air drawn from a portion of a main compressor section at a first temperature and pressure for cooling the air to a second temperature cooler than the first temperature;a cooling compressor compressing air communicated from the heat exchanger to a second pressure greater than the first pressure and communicating the cooling air to a portion of at least a turbine section; andsaid heat exchanger having at least two passes, with a first of said passes passing air in a direction having at least a radially outward component, and a second of said passes returning the air in a direction having at least a radially inward component to the compressor.22. The intercooling system as set forth in claim 21 , wherein said first pass is positioned downstream of said second pass in said bypass duct.23. The intercooling system as set forth in claim 22 , wherein said cooling compressor includes a centrifugal compressor impeller.24. The intercooling system as set forth in claim 22 , wherein a main fan delivers bypass air into a bypass duct and into said main compressor section and said heat exchanger positioned within said bypass duct to be cooled by bypass air.25. The intercooling ...

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Номер записи: 44

27-02-2020 дата публикации

COMPRESSED AIR STORAGE POWER GENERATION DEVICE

Номер: US20200063658A1

Автор: KUBO Yohei, MATSUKUMA Masaki, SAKAMOTO Kanami, SARUTA Hiroki, Toshima Masatake

Принадлежит: Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.)

The compressed air energy storage power generation device includes a third heat exchanger and fourth heat exchangers. The third heat exchanger performs heat exchange between the air exhausted from the expander and the second heating medium to cool the second heating medium. The fourth heat exchanger performs heat exchange between the second heating medium cooled by the third heat exchanger and at least one of the lubricating oil to be supplied to the compressor or the first heating medium to be supplied to the first heat exchanger to cool the lubricating oil or the first heating medium. 1. A compressed air energy storage power generation device comprising:an electric motor to be driven by electric power generated by renewable energy;a compressor configured to be driven by the electric motor and to compress air;a pressure accumulator configured to store compressed air compressed by the compressor;an expander to be driven by the compressed air to be supplied from the pressure accumulator;a generator mechanically connected to the expander;a first heat exchanger configured to perform heat exchange between the compressed air to be supplied from the compressor to the pressure accumulator and a first heating medium to cool the compressed air and to heat the first heating medium;a first heat storage configured to store the first heating medium heated by the first heat exchanger;a second heat exchanger configured to perform heat exchange between the compressed air to be supplied from the pressure accumulator to the expander and the first heating medium to be supplied from the first heat storage to heat the compressed air and to cool the first heating medium;a third heat exchanger configured to perform heat exchange between air exhausted from the expander and a second heating medium to heat the air and to cool the second heating medium; anda fourth heat exchanger configured to perform heat exchange between the second heating medium cooled by the third heat exchanger and at ...

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Номер записи: 45

19-03-2015 дата публикации

GAS TURBINE ENGINE SYSTEM THAT USES ORGANIC MEDIUM

Номер: US20150075133A1

Автор: Bohn Dieter, Braun Rene, Kusterer Karsten, MORISHITA Hiroshi, Sugimoto Takao, Tanaka Ryozo, TANIMURA Kazuhiko

Принадлежит: KAWASAKI JUKOGYO KABUSHIKI KAISHA

A gas turbine engine system is provided which achieves high efficiency while using sunlight as a heat source. In a gas turbine engine system including: a compressor configured to compress a first working medium; a heater configured to heat the compressed first working medium by an external heat source; a turbine configured to output power from the first working medium; and an intermediate cooler provided at the compressor and configured to cool the first working medium compressed by a low-pressure compression part of the compressor and supply the first working medium to a high-pressure compression part of the compressor, an organic Rankine cycle engine using, as a second working medium, an organic substance which is a cooling medium of the intermediate cooler is provided. 1. A gas turbine engine system comprising:a compressor configured to compress a first working medium;a heater configured to heat the compressed first working medium utilizing an external heat source;a turbine configured to output power from the first working medium;an intermediate cooler provided at the compressor and configured to cool the first working medium compressed by a low-pressure compression part of the compressor and supply the first working medium to a high-pressure compression part of the compressor; andan organic Rankine cycle engine using, as a second working medium, an organic substance which serves as a cooling medium of the intermediate cooler.2. The gas turbine engine system as claimed in claim 1 , further comprising:a heat exchanger provided on a discharge path for discharging the first working medium discharged from the turbine, the heat exchanger using, as a heating medium, the first working medium discharged from the turbine; andan organic Rankine cycle engine using, as a third working medium, an organic substance which serves as a heat receiving medium of the heat exchanger.3. The gas turbine engine system as claimed in comprising claim 1 , as the heater claim 1 , a solar ...

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Номер записи: 46

17-03-2016 дата публикации

System and method for providing a film treatment to a surface using cooling devices

Номер: US20160076458A1

Автор: Alston Ilford Scipio, Eduardo Mendoza, Ryan Hooley, Sanji Ekanayake

Принадлежит: General Electric Co

Disclosed herein are systems and methods for treating a surface, such as a gas turbine surface, with a filming agent using an inlet air cooling device. A filming control system includes a storage tank configured to contain a filming agent; an inlet air cooling device; and a supply conduit coupled to the storage tank on a first end and the inlet air cooling device on a second end; wherein the filming control system is configured to deliver the filming agent from the storage tank and to discharge the filming agent through the air inlet cooling device and the filming agent includes siloxane, fluorosilane, mercapto silane, amino silane, tetraethyl orthosilicate, succinic anhydride silane, or a combination including at least one of the foregoing.

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Номер записи: 47

15-03-2018 дата публикации

METHOD AND SYSTEM FOR POWER PRODUCTION WITH IMPROVED EFFICIENCY

Номер: US20180073434A1

Автор: Allam Rodney John, Fetvedt Jeremy Eron, Forrest Brock Alan

Принадлежит:

The present disclosure relates to systems and methods that provide power generation using predominantly COas a working fluid. In particular, the present disclosure provides for the use of a portion of the heat of compression from a COcompressor as the additive heating necessary to increase the overall efficiency of a power production system and method. 1. A method for heating a recirculating gas stream comprising:passing a heated exhaust gas stream through a recuperative heat exchanger to withdraw heat therefrom and form a cooled gas stream;separating the cooled gas stream into at least a first fraction and a second fraction;compressing the first fraction of the cooled gas stream to for a compressed first fraction gas stream;compressing the second fraction of the gas stream so as to add heat to the second fraction of the gas stream and form a compressed second fraction gas stream;combining the compressed first fraction gas stream and the compressed second fraction gas stream to form a combined recirculating gas stream; andpumping the combined recirculating gas stream to a pressure that is greater than a pressure of the compressed first fraction gas stream and greater than a pressure of the compressed second fraction gas stream;wherein the combined recirculating gas stream is heated using the heat withdrawn from the heated exhaust gas stream and the heat added to the second fraction of the gas stream.2. The method according to claim 1 , wherein heat is added to the second fraction of the gas stream so that the compressed second fraction gas stream is at a temperature of about 100° C. to about 400° C.3. (canceled)4. The method according to claim 1 , wherein the combined recirculating gas stream is pumped to a pressure of about 100 bar (10 MPa) to about 500 bar (50 MPa).56-. (canceled)7. The method according to claim 1 , wherein compressing the second fraction of the gas stream comprises multi-stage compression with no intercooling.8. The method according to claim 1 , ...

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Номер записи: 48

07-03-2019 дата публикации

COMPRESSED AIR ENERGY STORAGE POWER GENERATION APPARATUS

Номер: US20190072032A1

Автор: KUBO Yohei, MATSUKUMA Masaki, SAKAMOTO Kanami, SARUTA Hiroki, Toshima Masatake

Принадлежит: Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.)

A compressed air energy storage (CAES) power generation apparatus includes a motor driven by renewable energy, a compressor driven by the motor, a pressure accumulating tank storing compressed air compressed by the compressor, an expander driven by the compressed air from the pressure accumulating tank, and a generator connected to the expander. The apparatus includes a first heat exchanger that performs heat exchange between the compressed air from the compressor to the pressure accumulating tank and a heat medium, cools the compressed air, and heats the heat medium, a heat accumulating tank that stores the heat medium heated by the first heat exchanger, a second heat exchanger that performs heat exchange between the compressed air from the pressure accumulating tank to the expander, heats the compressed air, and cools the heat medium, and third heat exchangers that perform heat exchange between the exhaust heat outside a system and a fluid in the system. The power generation efficiency of the apparatus is improved using the exhaust heat outside the system while the exhaust heat outside the system is cooled using the cold heat generated in the system of the apparatus. 1. A compressed air energy storage power generation apparatus comprising:an electric motor driven by power generated by renewable energy;a compressor driven by the electric motor to compress air;a pressure accumulator that stores the compressed air compressed by the compressor;an expander driven by the compressed air supplied from the accumulator;a generator mechanically connected to the expander;a first heat exchanger that performs heat exchange between the compressed air supplied from the compressor to the pressure accumulator and a heat medium, cools the compressed air, and heats the heat medium;a heat accumulator that stores the heat medium heated by the first heat exchanger;a second heat exchanger that performs heat exchange between the compressed air supplied from the pressure accumulator to the ...

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Номер записи: 49

07-03-2019 дата публикации

INLET AIR COOLING SYSTEM AND INLET AIR COOLING METHOD FOR GAS TURBINE

Номер: US20190072036A1

Автор: KAMETA Masanori, Kikkawa Yoshitsugi, Momose Toshiya, Okano Takashi, YASUDA Satoshi

Принадлежит:

An inlet air cooling system used in a gas turbine for supplying power to a refrigerant compressor for compressing refrigerant in a natural gas liquefaction plant includes: an inlet air cooler for cooling inlet air of the gas turbine; chiller motors used for a chiller for cooling coolant supplied to the inlet air cooler; a first variable speed driver for supplying electric power to each of the one or more chiller motors; and an electric generator driven by the gas turbine, wherein the electric generator is electrically connected to the first variable speed driver, and electric power generated by the electric generator can be supplied to each of the chiller motors from the first variable speed driver without using a main power line of an electric power system, which enables efficient electric power supply to the motors via the variable speed driver. 1. An inlet air cooling system used in a gas turbine for supplying power to a refrigerant compressor for compressing refrigerant in a natural gas liquefaction plant , comprising:an inlet air cooler for cooling inlet air of the gas turbine;one or more chiller motors used for a chiller for cooling coolant supplied to the inlet air cooler;a first variable speed driver for supplying electric power to each of the one or more chiller motors; andan electric generator driven by the gas turbine,wherein the electric generator is electrically connected to the first variable speed driver, and electric power generated by the electric generator is allowed to be supplied to each of the one or more chiller motors from the first variable speed driver without using a main power line of an electric power system.2. The gas turbine inlet air cooling system according to claim 1 , wherein the electric generator functions as a starter motor for starting the gas turbine claim 1 , andwherein the gas turbine inlet air cooling system further comprises a second variable speed driver for supplying electric power from the main power line to the electric ...

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Номер записи: 50

16-03-2017 дата публикации

Waste heat recovery device, gas turbine plant provided with same, and waste heat recovery method

Номер: US20170074164A1

Автор: Hideaki Sugishita, Hideyuki Uechi, Yuichi Oka, Yukimasa Nakamoto

Принадлежит: Mitsubishi Hitachi Power Systems Ltd

A waste heat recovery device includes: a low-boiling-point medium Rankine cycle in which a low-boiling-point medium circulates while the low-boiling-point medium is repeatedly condensed and evaporated; a heated water line that guides liquid water, which is heated here, to the low-boiling-point medium Rankine cycle from a waste heat recovery boiler; and a water recovery line that returns the water, which has passed through the low-boiling-point medium Rankine cycle, to the waste heat recovery boiler. The low-boiling-point medium Rankine cycle includes a heater that heats the low-boiling-point medium by exchanging heat between the low-boiling-point medium, which is a liquid, and liquid water, which has passed through the heated water line.

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Номер записи: 51

18-03-2021 дата публикации

MOBILE GAS TURBINE INLET AIR CONDITIONING SYSTEM AND ASSOCIATED METHODS

Номер: US20210079841A1

Автор: Rodriguez-Ramon Ricardo, Yeung Tony

Принадлежит: BJ Energy Solutions, LLC

A system, as well as associated methods, for increasing the efficiency of a gas turbine including an inlet assembly and a compressor may include a housing configured to channel airstream towards the inlet assembly, an air treatment module positioned at a proximal end the housing, and at least one air conditioning module mounted downstream of the air treatment module for adjusting the temperature of the airstream entering the compressor. The air treatment module may include a plurality of inlet air filters and at least one blower configured to pressurize the air entering the air treatment module. 1. An air treatment system to increase the efficiency of a gas turbine comprising an inlet assembly and a compressor , the inlet assembly located upstream of the compressor and forming an input side of the gas turbine , the air treatment system comprising:a housing positioned to channel an airstream towards the inlet assembly, the housing positioned upstream of the input side, which channels the airstream to the compressor; and a plurality of inlet air filters to provide fluid flow to a first internal chamber, and', 'one or more blowers mounted in the first internal chamber and providing fluid flow to an interior of the housing via at least one outlet of the first internal chamber, the one or more blowers configured to pressurize the air entering the air treatment module, and', 'one or more air conditioning modules mounted downstream of the air treatment module for adjusting the temperature of the airstream entering the compressor, such that the airstream enters the one or more air conditioning modules at a first temperature and exits the one or more air conditioning modules at a second temperature., 'an air treatment module positioned at a proximal end of the housing, the air treatment module comprising2. The air treatment system of claim 1 , wherein the one or more air conditioning modules comprise at least one chiller module.3. The air treatment system of claim 2 , ...

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Номер записи: 52

31-03-2022 дата публикации

COMPLEX CYCLES

Номер: US20220099028A1

Автор: PALMER Chloe J, WHURR John R

Принадлежит: ROLLS-ROYCE PLC

A complex cycle gas turbine engine () for an aircraft with hydrogen fuel supply. The gas turbine engine comprises, in fluid flow series, a core gas turbine () and a recuperator () for heating hydrogen fuel prior to combustion by turbine exhaust products. 1. A complex cycle gas turbine engine for an aircraft with hydrogen fuel supply , comprising , in fluid flow series , a core gas turbine and a recuperator for heating hydrogen fuel prior to combustion by turbine exhaust products.2. The gas turbine engine of claim 1 , in which the core gas turbine engine comprises:a low-pressure spool having a low-pressure compressor driven by a low-pressure turbine;a high-pressure spool having a high-pressure compressor driven by a low high-pressure turbine.3. The gas turbine engine of claim 2 , further comprising a fan driven by the low-pressure spool claim 2 , optionally via a reduction gearbox.4. The gas turbine engine of claim 2 , in which the core gas turbine comprises a combustor between the high-pressure compressor and the high-pressure turbine claim 2 , the combustor having a liner cooled in a regenerative configuration by the hydrogen fuel.5. The gas turbine engine claim 1 , further comprising a fuel turbine for receiving heated hydrogen fuel from the recuperator to drive a load.6. The gas turbine engine of claim 5 , in which the load is:an electrical generator;a fuel pump for pumping the hydrogen fuel;a low-pressure spool or a high-pressure spool in the core gas turbine.7. The gas turbine engine claim 2 , further comprising an intercooler between the low-pressure compressor and the high-pressure compressor for cooling low-pressure compressor discharge air by the hydrogen fuel.8. The gas turbine engine of claim 7 , further comprising a second recuperator for further heating hydrogen fuel received from the intercooler.9. The gas turbine engine of claim 8 , in which the second recuperator is stationed downstream of the recuperator.10. The gas turbine engine of claim 1 , ...

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Номер записи: 53

02-04-2015 дата публикации

GAS TURBINE WITH COOLING AIR COOLING SYSTEM AND METHOD FOR OPERATION OF A GAS TURBINE AT LOW PART LOAD

Номер: US20150089955A1

Автор: DOEBBELING Klaus, Knapp Klaus

Принадлежит:

A gas turbine and method for operating a gas turbine, includes a compressor, a combustor, a turbine and a cooling air cooling system having at least a first cooling air line going from a first bleed of the compressor to the turbine, and at least one second cooling air line at a downstream position of the compressor relative to the first cooling air line. A heat exchanger is arranged in the second cooling air line for cooling the extracted air of higher pressure. The heat exchanger is connected with an air inlet side of the compressor such that heat is transferred in order to heat up the inlet air of the compressor. 1. A gas turbine comprising a compressor , a combustor , a turbine and a cooling air cooling system having at least a first cooling air line going from a first bleed of the compressor to the turbine , and at least one second cooling air line at a downstream position of the compressor relative to the first cooling air line , a heat exchanger arranged in the second cooling air line for cooling the extracted air of higher pressure , and in that the heat exchanger is connected with an air inlet side of the compressor such that heat is transferred in order to heat up the inlet air of the compressor.2. The gas turbine according to claim 1 , wherein the heat exchanger is connected to a preheater system for transferring the heat from the second cooling air line.3. The gas turbine according to claim 1 , wherein the preheater system comprises an electrical heater or is run by an external heat source.4. The gas turbine according to claim 1 , having an air intake and an air distribution device downstream of the air intake claim 1 , further comprising an air extraction line between the air intake and the distribution device which is provided with heat exchange means for transferring heat from the heat exchanger to the inlet air of the compressor.5. The gas turbine according to claim 4 , further comprising a blower is arranged in the air extraction line.6. The gas ...

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Номер записи: 54

19-03-2020 дата публикации

COMPRESSED AIR ENERGY STORAGE POWER GENERATION DEVICE

Номер: US20200088095A1

Автор: KUBO Yohei, MATSUKUMA Masaki, Matsuo Yuji, NAKAMICHI Ryo, Sato Takashi

Принадлежит: Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.)

A compressor, a first heat exchanger, a first heat storage unit, a pressure accumulation unit, a second heat exchanger, and a second heat storage unit are provided. The first heat storage unit and the second heat storage unit are connected by a first flow passage and a second flow passage. The first and second flow passages are connected by a third flow passage. A first on-off means is provided in a first region of the first flow passage and a second on-off means is provided in a second region. A third on-off means is provided in a third region of the second flow passage, and a fourth on-off means is provided in a fourth region. A driving means and a heating means are provided in the third flow passage. 1. A compressed air energy storage power generation device comprising:a compressor that compresses air;a pressure accumulation unit that stores compressed air compressed by the compressor;an expander driven by compressed air supplied from the pressure accumulation unit;a generator mechanically connected to the expander;a first heat exchanger that conducts heat exchange between a heating medium and the compressed air supplied from the compressor to the pressure accumulation unit so as to cool compressed air and heat a heating medium;a first heat storage unit that stores the heating medium heated by the first heat exchanger;a second heat exchanger that conducts heat exchange between the compressed air supplied from the pressure accumulation unit to the expander and the heating medium supplied from the first heat storage unit so as to heat compressed air and cool a heating medium;a second heat storage unit that stores the heating medium cooled by the second heat exchanger to supply the heating medium to the first heat exchanger;a first heating medium flow passage and a second heating medium flow passage that connects the first heat storage unit and the second heat storage unit;a third heating medium flow passage that connects an intermediate portion of the first heating ...

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Номер записи: 55

19-03-2020 дата публикации

HYBRID EXPANDER CYCLE WITH PRE-COMPRESSION COOLING AND TURBO-GENERATOR

Номер: US20200088098A1

Автор: Roberge Gary D.

Принадлежит:

A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes an air inlet, compressor, combustor, turbine, and heat exchange system. The heat exchange system is configured to transfer thermal energy from an inlet air flow or exhaust air flow to a fuel to produce a gaseous fuel that is used to drive a fuel turbine and fuel pump and used for combustion in the gas turbine engine. The fuel turbine is in fluid communication with the heat exchange system and the combustor and configured to extract energy from expansion of the gaseous fuel. The fuel pump is configured to be driven by the fuel turbine and is in fluid communication with the heat exchanger system. 1. A gas turbine engine system comprising: an air inlet configured to receive an inlet air flow;', 'a compressor configured to compress the inlet air flow to produce a compressed air flow;', 'a combustor configured to combust a mixture of the compressed air flow and a gaseous fuel at a first pressure to produce a combustion gas flow;', 'a turbine configured to extract energy from expansion of the combustion gas flow to produce an exhaust gas flow; and', 'a heat exchange system configured to transfer thermal energy from an air flow to a fuel to produce the gaseous fuel at a second pressure greater than the first pressure, wherein the air flow is selected from the group consisting of the inlet air flow and the exhaust gas flow; and, 'a gas turbine engine comprising a fuel turbine in fluid communication with the heat exchange system and the combustor, wherein the fuel turbine is configured to extract energy from expansion of the gaseous fuel at the second pressure to produce the gaseous fuel at the first pressure; and', 'a fuel pump configured to be driven by the fuel turbine, wherein the fuel pump is in fluid communication with the heat exchanger system., 'a fuel turbine system comprising2. The gas turbine engine system of claim 1 , wherein the heat exchange ...

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Номер записи: 56

19-03-2020 дата публикации

HYBRID EXPANDER CYCLE WITH TURBO-GENERATOR AND COOLED POWER ELECTRONICS

Номер: US20200088099A1

Автор: Roberge Gary D.

Принадлежит:

A gas turbine engine system includes a gas turbine engine and a turbo-generator. The gas turbine engine includes a heat exchange system configured to transfer thermal energy from an air flow (i.e., inlet air flow or exhaust gas flow) to a fuel to produce a gaseous fuel. The turbo-generator includes a fuel turbine fluidly coupled to the heat exchange system and a combustor of the gas turbine engine, a fuel pump configured to be driven by the fuel turbine and fluidly coupled to the heat exchange system, and a motor/generator configured to be driven by the fuel turbine. The fuel turbine is configured to extract energy from expansion of the gaseous fuel to produce a gaseous fuel for combustion in the combustor. The motor/generator includes a cooling jacket, which is fluidly coupled to the fuel pump. 1. A gas turbine engine system comprising: an air inlet configured to receive an inlet air flow;', 'a compressor configured to compress the inlet air flow to produce a compressed air flow;', 'a combustor fluidly coupled to the compressor and configured to combust a mixture of the compressed air flow and a gaseous fuel at a first pressure to produce a combustion gas flow;', 'a turbine fluidly coupled to the combustor and configured to extract energy from expansion of the combustion gas flow to produce an exhaust gas flow; and', 'a heat exchange system configured to transfer thermal energy from an air flow to a fuel to produce the gaseous fuel at a second pressure greater than the first pressure, wherein the air flow is selected from the group consisting of the inlet air flow and the exhaust gas flow; and, 'a gas turbine engine comprising a fuel turbine fluidly coupled to the heat exchange system and the combustor, wherein the fuel turbine is configured to extract energy from expansion of the gaseous fuel at the second pressure to produce the gaseous fuel at the first pressure;', 'a fuel pump configured to be driven by the fuel turbine, wherein the fuel pump is fluidly coupled ...

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Номер записи: 57

19-03-2020 дата публикации

HYBRID EXPANDER CYCLE WITH INTERCOOLING AND TURBO-GENERATOR

Номер: US20200088102A1

Автор: Roberge Gary D.

Принадлежит:

A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes a heat exchange system configured to transfer thermal energy from a first compressed air flow and an exhaust gas flow to a fuel to produce a gaseous fuel. The fuel turbine system includes a fuel turbine fluidly coupled to the heat exchange system and a combustor of the gas turbine engine, and a fuel pump fluidly coupled to the heat exchange system and configured to be driven by the fuel turbine. The fuel turbine is configured to extract energy from expansion of the gaseous fuel to produce the gaseous fuel at a lower pressure for delivery to the combustor. 1. A gas turbine engine system comprising: 'a compressor section comprising:', 'a gas turbine engine comprising 'a high pressure compressor fluidly coupled to the low pressure compressor and configured to compress the first compressed air flow to produce a second compressed air flow;', 'a low pressure compressor configured to compress an inlet air flow to produce a first compressed air flow;'}a combustor fluidly connected to an outlet of the high pressure compressor and configured to combust a mixture of the second compressed air flow and a gaseous fuel at a first pressure to produce a combustion gas flow;a turbine fluidly coupled to the combustor and configured to extract energy from expansion of the combustion gas flow to produce an exhaust gas flow; anda heat exchange system configured to transfer thermal energy from the first compressed air flow and the exhaust gas flow to a fuel to produce the gaseous fuel at a second pressure greater than the first pressure; and a fuel turbine fluidly coupled to the heat exchange system and the combustor, wherein the fuel turbine is configured to extract energy from expansion of the gaseous fuel at the second pressure to produce the gaseous fuel at the first pressure; and', 'a fuel pump fluidly coupled to the heat exchange system and configured to be driven by ...

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Номер записи: 58

16-04-2015 дата публикации

ENGINE

Номер: US20150101342A1

Автор: Bond Alan, Varvill Richard

Принадлежит:

The present disclosure relates to an engine having two modes of operation—air breathing and rocket—that may be used in aerospace applications such as in an aircraft, flying machine, or aerospace vehicle. The engine's efficiency can be maximized by using a precooler arrangement to cool intake air in air breathing mode using cold fuel delivery systems used for the rocket mode. By introducing the precooler and certain other engine cycle components, and arranging and operating them as described, problems such as those associated with higher fuel and weight requirements and frost formation can be alleviated. 1. An engine comprising:a rocket combustion chamber for the combustion of fuel and oxidant;an air-breathing combustion chamber for the combustion of fuel and oxidant;a compressor for pressurizing air for supply to said air-breathing combustion chamber;a first fuel delivery system for delivering fuel to said rocket combustion chamber;a second fuel delivery system for delivering fuel to said air-breathing combustion chamber;an oxidant delivery system for delivering oxidant to said rocket combustion chamber;wherein the air-breathing combustion chamber and the rocket combustion chamber are configured to be operated independently.2. An engine according to claim 1 , wherein the engine further comprises:a first heat exchanger arrangement having an inlet and an outlet arranged for cooling air to be supplied to said compressor using a heat transfer medium before compression by said compressor;a heat transfer medium loop for said heat transfer medium;a second heat exchanger arrangement configured for cooling of said heat transfer medium by fuel delivered by the first or second fuel delivery system.3. An engine according to claim 2 , wherein the engine further comprises a turbine for driving said compressor claim 2 , the turbine being configured to be driven using a portion of heat transfer medium from the outlet of the first heat exchanger arrangement.4. An engine according to ...

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Номер записи: 59

12-05-2022 дата публикации

COMBUSTION ENGINE INCLUDING TURBOMACHINE

Номер: US20220145796A1

Автор: Hallisey Kevin P., Sautron Dominique Patrick

Принадлежит:

A combustion engine including at least one combustion chamber, a first bleed air supply fluidly coupled to a portion of the combustion engine upstream the combustion chamber, a second bleed air supply fluidly coupled to a portion of the combustion engine downstream the combustion chamber, and a turbomachine comprising a first compressor, a second compressor, and a first turbine mounted to a common shaft, with the first and second compressors in serial flow arrangement. The turbomachine, further comprising an intercooler serially fluidly coupling a portion of the first compressor to a portion of the second compressor. 1. A combustion engine comprising: a first bleed air supply fluidly coupled to a portion of the combustion engine upstream of the combustion chamber;', 'a second bleed air supply fluidly coupled to a portion of the combustion engine downstream of the combustion chamber; and', a first compressor, a second compressor, and a first turbine mounted to a common shaft with the first and second compressors in serial flow arrangement, with the first compressor fluidly coupled to the first bleed air supply, and', 'an intercooler serially fluidly coupling a portion of the first compressor to a portion of the second compressor., 'a turbomachine comprising], 'at least one combustion chamber;'}2. The combustion engine of claim 1 , the turbomachine further comprises a second turbine mounted to the common shaft and in serial flow arrangement with the first turbine claim 1 , with the first turbine being fluidly coupled to at least one of the first or second bleed air supplies.3. The combustion engine of claim 2 , further comprising a turbo-ejector fluidly coupling the second compressor and the second turbine.4. The combustion engine of claim 3 , the turbo-ejector comprises a venturi defining a throat claim 3 , with the venturi fluidly coupled to the second turbine claim 3 , and a tap at the throat claim 3 , and the second compressor is fluidly coupled to the tap.5. The ...

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Номер записи: 60

28-03-2019 дата публикации

MULTISTAGE AXIAL COMPRESSOR AND GAS TURBINE

Номер: US20190093554A1

Автор: MORITA Daisuke

Принадлежит: MITSUBISHI HEAVY INDUSTRIES ,LTD.

A multistage axial compressor includes: a rotational shaft to which a plurality of rotor blades are mounted; a casing surrounding the rotational shaft, the casing forming a flow passage of a working fluid between the rotational shaft and the casing; a wall portion having an annular shape and extending in a circumferential direction of the rotational shaft so as to surround the casing, the wall portion forming an bleed chamber having an annular shape and being in communication with the flow passage; a plurality of port portions connected to an outer peripheral surface of the wall portion, the port portions forming respective outlet flow passages which are in communication with the bleed chamber; and a plurality of bleed pipes connected to the respective port portions. 1. A multistage axial compressor , comprising:a rotational shaft to which a plurality of rotor blades are mounted;a casing surrounding the rotational shaft, the casing forming a flow passage of a working fluid between the rotational shaft and the casing;a wall portion having an annular shape and extending in a circumferential direction of the rotational shaft so as to surround the casing, the wall portion forming an bleed chamber having an annular shape and being in communication with the flow passage;a plurality of port portions connected to an outer peripheral surface of the wall portion, the port portions forming respective outlet flow passages which are in communication with the bleed chamber; anda plurality of bleed pipes connected to the respective port portions,{'b': '1', 'wherein, in a cross-sectional view orthogonal to the rotational shaft, of two corner regions where an inner surface of each of the port portions and an inner surface of the wall portion intersect with each other, at the corner region positioned on a back side in a rotational direction of the working fluid in the bleed chamber, when θ is defined as an angle formed between the inner surface of the port portion and the inner ...

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Номер записи: 61

06-04-2017 дата публикации

GAS TURBINE ASSEMBLY

Номер: US20170096936A1

Автор: Nilsson Ulf

Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A gas turbine assembly having a first shaft, a first compressor and a first turbine mounted on the first shaft, a combustor between the first compressor and the first turbine and a second shaft and a second turbine mounted on the second shaft, the second turbine having an inlet connected to an outlet of said first turbine. The gas turbine assembly further includes a third shaft on which an upstream compressor is mounted, the upstream compressor having an outlet which is connectable to an inlet of the first compressor. 1. A gas turbine assembly comprising:a first shaft,a first compressor and a first turbine mounted on the first shaft,a combustor between the first compressor and the first turbine, anda second turbine having an inlet connected to an outlet of the first turbine,a third shaft on which a controllable motor and an upstream compressor are mounted, the upstream compressor having an outlet which is connected to an inlet of the first compressor,wherein the controllable motor varies the speed of the third shaft and upstream compressor independently from an air flow passing through the upstream compressor,wherein the air flow is ducted through the upstream compressor and the first compressor in series.2. The gas turbine assembly of claim 1 , further comprising:a second drive shaft connected to the second turbine providing a torque to drive a mechanical load or a generator.3. The gas turbine assembly of claim 1 ,wherein the controllable motor is an electrical motor.4. The gas turbine assembly of claim 1 ,wherein the upstream compressor has a pressure ratio of 1/3 or lower of the pressure ratio for the first compressor, andthe pressure ratio for the first compressor is the pressure ratio at full load.5. The gas turbine assembly of claim 1 ,wherein the upstream compressor has a pressure ratio of 1/5 or lower of the pressure ratio of the first compressor.6. The gas turbine assembly of claim 1 ,wherein the upstream compressor has a pressure ratio of 1/10 or lower of ...

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Номер записи: 62

03-07-2014 дата публикации

Aircraft engine systems and methods for operating same

Номер: US20140182264A1

Автор: Christopher Thompson, Craig Gonyou, Kurt David Murrow, Michael Jay Epstein, Nicholas Dinsmore, Randy M. Vondrell, Robert Harold Weisgerber, Samuel Jacob Martin

Принадлежит: General Electric Co

A gas turbine propulsion system includes a system which utilizes a cryogenic liquid fuel for a non-combustion function.

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Номер записи: 63

23-04-2015 дата публикации

GAS TURBINE WITH FLEXIBLE AIR COOLING SYSTEM AND METHOD FOR OPERATING A GAS TURBINE

Номер: US20150107258A1

Автор: Knoepfel Hanspeter, MARMILIC Robert, Rofa Stefan

Принадлежит:

A gas turbine for a gas and steam turbine plant and method for operating a gas turbine is provided. The gas turbine includes a cooling system for cooling inlet air taken from compressor extractions or compressor discharge and introduced to the turbine(s) and/or combustor(s) of the gas turbine which is adapted for flexible operation in a combined cycle application as well as a simple cycle application. The cooling system includes at least a water/steam cooled cooling air cooler for use in a normal combined cycle application. The gas turbine is provided with at least one second cooling air system arranged in a bypass which is operable instead of or parallel to the water/steam cooled cooling air cooler for use in particular in a simple cycle application operation of the gas turbine. 1. A gas turbine for a gas and steam turbine plant comprising a cooling system for cooling inlet air taken from compressor extractions or compressor discharge and introduced to the turbine(s) and/or combustor(s) of the gas turbine which is adapted for flexible operation in a combined cycle application as well as a simple cycle application , wherein the cooling system includes at least a water/steam cooled cooling air cooler for use in a normal combined cycle application , wherein the gas turbine is provided with at least one second cooling air system arranged in a bypass which is operable instead of or parallel to the water/steam cooled cooling air cooler for use in particular in a simple cycle application operation of the gas turbine.2. The gas turbine according to claim 1 , further comprising means are provided for completely shutting off the water/steam cooled cooling air cooler of the cooling system when said second cooling air system is operated.3. The gas turbine according to claim 1 , wherein the gas turbine is adapted to being operable without a water/steam cycle being built up.4. The gas turbine according to claim 1 , further comprising a control device for automatically switching ...

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Номер записи: 64

08-04-2021 дата публикации

Device for temporarily increasing turbomachine power

Номер: US20210102491A1

Автор: Bertrand Moine, Frederic Pousse, Laurent Minel, Lionel Napias

Принадлежит: Safran Helicopter Engines SAS

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.

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Номер записи: 65

04-04-2019 дата публикации

GAS TURBINE SYSTEM

Номер: US20190099764A1

Автор: Enis Ben M., LIEBERMAN PAUL

Принадлежит:

The present invention is a centrifuge to be used for removing ice particles from the air fed to a gas turbine system. In an embodiment, the centrifuge is comprised of three ducts defining an air-path which comprises of two bends greater than 90 degrees. In an embodiment, the first two ducts extend past the bends to provide a dead air zone to trap ice particles which have been introduced by cooling air containing moisture. The dead air zones are further provided with revolving doors which remove the ice particles from the system. In an embodiment, the centrifuge receives cold air from the compander and removes ice particles before exhausting the cold air to a gas turbine electric generator, such that the blades of the gas turbine generator are not damaged by the ice particles. 2. The centrifuge of claim 1 , wherein the bend from the first duct to the second duct is approximately 135-degrees and the bend from the second duct to the third duct is approximately 135-degrees.3. The centrifuge of claim 1 , wherein the first revolving door and the second revolving door move due to the pressure difference between air inside the duct and air outside of the duct.4. The centrifuge of claim 1 , wherein the first revolving door and the second revolving door each rotate with assistance from an electric motor.5. The centrifuge of claim 1 , wherein ice particles collect and are removed from the centrifuge by the first revolving door and the second revolving door.6. The centrifuge of claim 5 , wherein the ice particles which have been removed from the centrifuge are placed into a heat exchange system.7. The centrifuge of claim 5 , wherein the ice particles which have been removed from the centrifuge are collected in a cold water supply.8. A method of supplying super cold air to a gas turbine generator comprising the steps of:a. compressing air with a compressor;b. sending the compressed air to a compander;c. releasing cold air from the compander; [ 1. a first end to receive air from ...

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Номер записи: 66

29-04-2021 дата публикации

EXTENDED GAS TURBINE PROCESS HAVING AN EXPANDER

Номер: US20210123377A1

Автор: Graeber Carsten, Juretzek Uwe

Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A power plant including a compressor, a combustion chamber and a turbine, and a compressor air line, which connects the compressor to the combustion chamber, a first heat exchanger connected into the compressor air line and into an exhaust line branching off the turbine. A first expander is arranged between the first heat exchanger and the combustion chamber in the compressor air line, and the first expander and the compressor are arranged on a common shaft. 117.-. (canceled)18. A power plant comprising:a compressor, a combustion chamber and a turbine,a compressor air line which connects the compressor to the combustion chamber,a first heat exchanger which is connected into the compressor air line, anda first expander which is arranged in the compressor air line between the first heat exchanger and the combustion chamber,wherein the first heat exchanger is further connected into an exhaust line which branches from the turbine, andwherein the first expander and the compressor are arranged on a common shaft.19. The power plant as claimed in claim 18 ,wherein the compressor is a multi-stage intercooled compressor, in which second heat exchangers are arranged as compressor intercooling between the compressor stages.20. The power plant as claimed in claim 18 ,wherein the first heat exchanger comprises two heat exchanger modules, which are both arranged one behind the other in each case in the compressor air line and the exhaust line,wherein a water injection is arranged in the compressor air line between the heat exchanger modules.21. The power plant as claimed in claim 19 ,wherein the second heat exchangers are connected into a district heating circuit.22. The power plant as claimed in claim 20 ,wherein a third heat exchanger is arranged in the exhaust line between the heat exchanger modules, for preheating fuel.23. The power plant as claimed in claim 18 ,wherein a fourth heat exchanger is arranged in an air supply line to the compressor and is connected into a cooling ...

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Номер записи: 67

29-04-2021 дата публикации

HEAT DISSIPATION SYSTEMS WITH HYGROSCOPIC WORKING FLUID

Номер: US20210123616A1

Автор: Martin Christopher Lee

Принадлежит:

In various embodiments, the present invention relates to heat dissipation systems including a hygroscopic working fluid and methods of using the same. In various embodiments, the present invention provides a method for heat dissipation using a hygroscopic working fluid. The method can include transferring thermal energy from a heated process fluid to the hygroscopic working fluid in a process heat exchanger, to form a cooled process fluid. The method can include condensing liquid from a feed gas on a heat transfer surface of a feed gas heat exchanger in contact with the cooled process fluid, to form a cooled feed gas, the heated process fluid, and a condensate. The method can include dissipating thermal energy from the hygroscopic working fluid to a cooling gas composition with a fluid-air contactor. The method can include transferring moisture between the hygroscopic working fluid and the cooling gas composition with the fluid-air contactor. The method can include adding at least part of the condensate to the hygroscopic working fluid. 1. A method for heat dissipation using a hygroscopic working fluid , the method comprising:transferring thermal energy from a heated process fluid to the hygroscopic working fluid in a process heat exchanger, to form a cooled process fluid;condensing liquid from a feed gas on a heat transfer surface of a feed gas heat exchanger in contact with the cooled process fluid, to form a cooled feed gas, the heated process fluid, and a condensate;dissipating thermal energy from the hygroscopic working fluid to a cooling gas composition with a fluid-air contactor;transferring moisture between the hygroscopic working fluid and the cooling gas composition with the fluid-air contactor; andadding at least part of the condensate to the hygroscopic working fluid.2. The method of claim 1 , wherein the condensing of the liquid from the feed gas comprises transferring thermal energy from the feed gas to the cooled process fluid.3. The method of claim 1 ...

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Номер записи: 68

09-06-2022 дата публикации

Fuel delivery

Номер: US20220178307A1

Автор: Chloe J. PALMER, Guy D. Snowsill, Jonathan E. Holt

Принадлежит: Rolls Royce PLC

A fuel delivery system (201) is shown for delivering the hydrogen fuel from a cryogenic storage system to a fuel injection system in a gas turbine engine. The fuel delivery system includes a pump (301), a metering device (302), and a fuel heating system (303,304) for heating the hydrogen fuel to an injection temperature for the fuel injection system.

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Номер записи: 69

27-04-2017 дата публикации

SYSTEM AND METHOD OF INTERFACING INTERCOOLED GAS TURBINE ENGINE WITH DISTILLATION PROCESS

Номер: US20170114672A1

Автор: Watkins Richard Michael

Принадлежит:

A system includes a gas turbine system having a heat recovery steam generator (HRSG), a compressor, an intercooler, and a steam turbine. The HRSG is configured to receive an exhaust gas, heat a first working fluid with the exhaust gas, and route the first working fluid to the steam turbine, where the steam turbine is configured to extract energy from the first working fluid, and where the intercooler is configured to receive a compressed air from the compressor of the gas turbine engine and to cool the compressed air to a first controllable temperature determined by engine controls with a second working fluid having a second controllable temperature suitable for cooling the compressed air to the first controllable temperature determined by the engine controls. The system also includes a first feed heater of a distillation system, where the first feed heater is configured to receive the mixture and the second working fluid such that the second working fluid sinks heat to the mixture. The system also includes a first-effect vessel of the distillation system. The first-effect vessel is configured to receive the mixture from the first feed heater and to receive the first working fluid from the steam turbine, such that the first working fluid sinks heat to the mixture. 1. A system , comprising:a gas turbine system comprising a heat recovery steam generator (HRSG), a steam turbine, a compressor, and an intercooler, wherein the HRSG is configured to receive an exhaust gas, heat a first working fluid with the exhaust gas, and route the first working fluid to the steam turbine, wherein the steam turbine is configured to extract energy from the first working fluid, and wherein the intercooler is configured to receive a compressed air from the compressor and to cool the compressed air to a first controllable temperature determined by engine controls with a second working fluid having a second controllable temperature suitable for cooling the compressed air to the first ...

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Номер записи: 70

27-04-2017 дата публикации

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

Номер: US20170114718A1

Автор: Masaki Iijima

Принадлежит: Mitsubishi Heavy Industries Ltd

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.

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Номер записи: 71

07-05-2015 дата публикации

GAS TURBINE INLET SYSTEM AND RELATED METHOD FOR COOLING GAS TURBINE INLET AIR

Номер: US20150121881A1

Автор: KIPPEL Brad Aaron, Zhang Jianmin

Принадлежит: GENERAL ELECTRIC COMPANY

An inlet air conditioning system for a gas turbine includes an inlet duct for the with an air flow path to provide inlet air to the gas turbine; evaporative cooling media disposed in the air flow path; a water chiller; and a circulation pump that circulates water through the water chiller and the evaporative media in series. The chiller is configured to chill the water to below ambient wet-bulb temperature before the water is circulated to the evaporative cooling media. A power plant includes a gas turbine including a compressor, a combustion system, and a turbine section; a load; and the inlet air conditioning system. 1. An inlet air conditioning system for a gas turbine , the system comprising:an inlet duct for the gas turbine, the inlet duct comprising an air flow path to provide inlet air to the gas turbine;evaporative cooling media disposed in the air flow path;a water chiller; anda circulation pump that circulates water through the water chiller and the evaporative cooling media in series,wherein the chiller is configured to chill the water to below ambient wet-bulb temperature before the water is circulated to the evaporative cooling media.2. The inlet system according to claim 1 , wherein the evaporative cooling media comprises a plurality of vertically distinct sections each with water inlets at the tops of each of the plurality of vertically distinct sections claim 1 , and wherein the water is supplied from the chiller and separately to the tops of the plurality of vertically distinct sections.3. The inlet system according to claim 2 , wherein the plurality of vertically distinct sections is stacked on top of one another.4. The inlet system according to claim 3 , wherein the water inlets are functionally parallel to one another.5. The inlet system according to claim 1 , wherein the height of the evaporative cooling media and the water circulated through the chiller are optimized to concurrently provide a combination of evaporative and sensitive cooling in ...

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Номер записи: 72

24-07-2014 дата публикации

Zoned Evaporative Cooling Media for Air Intake House of Gas Turbine

Номер: US20140202186A1

Автор: Laquinnia Lawson, Jr., Sanjay Mahapatra

Принадлежит: Braden Manufacturing LLC

An evaporative cooling system for combustion gas turbine system has an array of cooling media including first and second cooling media types. The first cooling media type has a first maximum air velocity rating, and the second cooling media type has a second maximum air velocity rating that greater than the first maximum air velocity rating.

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Номер записи: 73

04-05-2017 дата публикации

Intercooled gas turbine optimization

Номер: US20170122208A1

Автор: Christopher Hung Vu, Daniel Aaron Kessler, Veronica Elizabeth Vela

Принадлежит: General Electric Co

A control system for a gas turbine includes a controller. The controller includes a processor configured to access an operational parameter associated with the gas turbine. The processor is configured to calculate a bias based on the operational parameter, wherein the bias indicates an amount of change in a temperature of an oxidant entering a compressor of the turbine to reach a reference temperature. The processor is further configured to control the temperature of the oxidant based on the bias to improve power output of the gas turbine.

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Номер записи: 74

25-08-2022 дата публикации

Turbine inlet air cooling systems with condensate water recovery

Номер: US20220268204A1

Автор: Thomas Brady

Принадлежит: Stellar Energy Americas Inc

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.

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Номер записи: 75

12-05-2016 дата публикации

POWER PLANT HAVING A TWO-STAGE COOLER DEVICE FOR COOLING THE ADMISSION AIR FOR A TURBOSHAFT ENGINE

Номер: US20160131032A1

Автор: Pomme Vincent

Принадлежит:

A power plant having at least one compressor, at least one fuel-burning engine, and a cooler device for cooling admission air for the engine, the engine being provided with a combustion chamber. The cooler device is constituted by a heat engine having three heat sources arranged between two compression stages of the compressor and including a refrigerant fluid and two evaporators. The admission air flows in succession through the two evaporators between the two compression stages firstly to cool the admission air between the two compression stages prior to being injected into the combustion chamber, and secondly to vaporize the refrigerant fluid. 1. A power plant comprising at least one compressor , at least one fuel-burning engine , and a cooler device for cooling the admission air for each engine , each engine being provided with a combustion chamber , each compressor having at least two compression stages in order to compress the admission air prior to injecting it into the combustion chamber of each engine , the cooler device including a refrigerant fluid , first pipes and second pipes and also two evaporators , a pump , an expander , and a condenser , the first pipes connecting a first compression stage to a first evaporator , the first evaporator to a second evaporator , and the second evaporator to a second compression stage , the second pipes connecting the condenser to the pump , the pump to the first evaporator , the condenser to the expander , and the expander to the second evaporator , the refrigerant fluid circulating in the second pipes and the components of the cooler device , while the admission air flows through the first pipes and successively through the two evaporators in order firstly to vaporize the refrigerant fluid and secondly to cool the admission air between the two compression stages , wherein the cooler device is a heat engine having three heat sources including compression and drive means , the refrigerant fluid circulating through the ...

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Номер записи: 76

10-05-2018 дата публикации

INTERCOOLED COOLED COOLING INTEGRATED AIR CYCLE MACHINE

Номер: US20180128176A1

Автор: Snape Nathan, Staubach Joseph B.

Принадлежит:

An intercooled cooling system for a gas turbine engine is provided. The intercooled cooling system includes cooling stages in fluid communication with an air stream utilized for cooling. A first cooling stage is fluidly coupled to a bleed port of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system includes a pump fluidly coupled to the first cooling stage to receive and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. The intercooled cooling system includes an air cycle machine in fluid communication to outputs of the cooling stages to selectively receive the cool bleed air or the intercooled cooling air. 1. An intercooled cooling system for a gas turbine engine , the intercooled cooling system comprising:a plurality of cooling stages in fluid communication with an air stream utilized by the plurality of cooling stages for cooling,wherein a first cooling stage of the plurality of cooling stages is fluidly coupled to a bleed port of a compressor of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air;a pump fluidly coupled to the first cooling stage to receive and increase a pressure of the cool bleed air to produce a pressurized cool bleed air,wherein a second cooling stage of the plurality of cooling stages is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air; andan air cycle machine in fluid communication to outputs of the first and second cooling stages to selectively receive at least a portion of the cool bleed air or at least a portion of the intercooled cooling air.2. The intercooled cooled cooling air system of claim 1 , wherein the air cycle machine comprises a turbine configured to receive ...

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Номер записи: 77

03-06-2021 дата публикации

ENERGY STORAGE APPARATUS AND METHOD

Номер: US20210164395A1

Автор: Howitt Mark Aidan

Принадлежит:

An energy storage apparatus comprising: at least one inlet for incoming process gas; at least one outlet for expanded process gas; and a plurality of energy storage sub-systems configured to be arranged in series with each other and with a compressed gas store. A first one of the plurality of energy storage sub-systems comprises: at least a first compressor; at least a first expander; at least a first thermal store; and at least a first heat transfer device associated with the first thermal store. A second one of the plurality of energy storage sub-systems comprises: at least a second compressor; at least a second expander; at least a second thermal store; and at least a second heat transfer device associated with the second thermal store. The first heat transfer device is configured to transfer heat generated by compression of the process gas in either the first or the second compressor to the first thermal store for storing the heat in the first thermal store, and wherein the first heat transfer device is configured to transfer heat from the first thermal store to process gas received at the first or the second expander. The second heat transfer device is configured to transfer heat generated by compression of the process gas in the first or the second compressor to the second thermal store for storing the heat in the second thermal store, and wherein the second heat transfer device is configured to transfer heat from the second thermal store to process gas received at the first or the second expander. The first compressor is configured to provide a first compression to incoming process gas received from the at least one inlet and to supply a first compressed process gas to the second compressor. The second compressor is configured to provide a second compression to the first compressed process gas received from the first compressor and to supply a second compressed process gas to the compressed gas store. The second expander is configured to provide a first ...

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Номер записи: 78

17-05-2018 дата публикации

COOLING SYSTEM FOR A TURBINE ENGINE

Номер: US20180135518A1

Автор: Moniz Thomas Ory, Sage Patrick Sean, Yanosik Ann Marie

Принадлежит:

A gas turbine engine includes a compressor section having a high pressure compressor and a core casing surrounding the compressor section and defining an inlet. The gas turbine engine also includes a cooling system for cooling air in or to the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and a fluid line assembly in fluid communication with the fluid tank. The fluid line assembly includes an outlet positioned upstream of the high pressure compressor and downstream of the inlet defined by the core casing for injecting cooling fluid into an airflow upstream of the high pressure compressor. 1. A gas turbine engine defining an axial direction and a radial direction , the gas turbine engine comprising:a compressor section for progressively compressing air, the compressor section including a high pressure compressor;a core casing surrounding the compressor section and defining an inlet; anda cooling system for cooling air in or to the compressor section, the cooling system comprising a fluid line assembly, the fluid line assembly including an outlet positioned upstream of the high pressure compressor and downstream of the inlet defined by the core casing for injecting cooling fluid into an airflow upstream of the high pressure compressor.2. The gas turbine engine of claim 1 , wherein the compressor section further includes a low pressure compressor claim 1 , and wherein the outlet of the fluid line assembly is positioned downstream of the low pressure compressor.3. The gas turbine engine of claim 2 , further comprising:an inner flowpath liner extending between the low pressure compressor and the high pressure compressor; andan outer flowpath liner also extending between the low pressure compressor and the high pressure compressor at a location outward from the inner flowpath liner along the radial direction, wherein the outlet of the fluid line assembly is positioned at the inner flowpath liner.4. The gas turbine ...

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Номер записи: 79

30-04-2020 дата публикации

INLET AIR HEATING SYSTEMS FOR COMBINED CYCLE POWER PLANTS

Номер: US20200131990A1

Автор: Beadie Douglas Frank, Erickson Dean Matthew, KIPPEL Bradly Aaron

Принадлежит:

Inlet air heating systems for combined cycle power plants and combined cycle power plants including inlet air heating systems are disclosed. The inlet air heating systems may include a plurality of heating coil assemblies partially positioned within an inlet housing of a gas turbine system, and a vent valve in fluid communication with each of the heating coils. The inlet air heating system may also include a supply line in fluid communication with the heating coils to provide water to the heating coils, and a hot water line in fluid communication with the supply line and a component positioned downstream of a condenser of the combined cycle power plant. The hot water line may provide hot water from the combined cycle power plant to the supply line. Additionally, the inlet air heating system may include a drain line in fluid communication with the heating coils and the condenser. 1. An inlet air heating system for a gas turbine system of a combined cycle power plant , the inlet air heating system comprising:a plurality of heating coil assemblies at least partially positioned within an inlet housing of the gas turbine system;a vent valve in fluid communication with each of the plurality of heating coil assemblies, the vent valve allowing air to flow into and out of the plurality of heating coil assemblies when in an open position;a supply line in fluid communication with the plurality of heating coil assemblies, the supply line providing water to the plurality of heating coil assemblies;a hot water line in fluid communication with the supply line and a component of the combined cycle power plant positioned downstream of a condenser of the combined cycle power plant, the hot water line providing hot water from the combined cycle power plant to the supply line; anda drain line in fluid communication with the plurality of heating coil assemblies and the condenser of the combined cycle power plant, the drain line providing the water from the plurality of heating coil ...

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Номер записи: 80

10-06-2021 дата публикации

METHOD FOR STORING AND PRODUCTION ENERGY BY MEANS OF COMPRESSED AIR WITH ADDITIONAL ENERGY RECOVERY

Номер: US20210172372A1

Автор: BRIOT Patrick, TEIXEIRA David

Принадлежит:

The invention relates to a compressed-air energy storage and production method comprising the following steps: 1. A compressed-air energy storage and production method comprising the following steps:{'b': 101', '102', '103', '104', '101', '102', '103', '104, 'a) compression of the air by staged compressors (K-, K-, K-, K-), during which cooling of the air is performed after at least one compression stage through exchange with a heat transfer fluid (C-, C-, C-, C-),'}b) storage of the compressed air and of the hot heat transfer fluid after exchange during compression,{'b': 201', '202', '203', '204', '101', '102', '103', '104, 'c) staged expansions of the air by power generation turbines (EX-, EX-, EX-, EX-), during which heating of the air is performed after at least one expansion stage by the hot heat transfer fluid from the storage (C-, C-, C-, C-),'}{'b': 501', '501', '501, 'characterized in that, after heating the expanded air and prior to being recycled to the compression step, the transfer fluid is cooled by an additional energy recovery loop comprising a pump (P-), an exchanger (E-) and a turbine (EX-), as well as an additional heat transfer fluid.'}2. A method as claimed in claim 1 , wherein the fluid used for heat transfer with the air is selected from among water claim 1 , mineral oils claim 1 , ammonia solutions.3. A method as claimed in claim 1 , wherein the additional transfer fluid is selected from among hydrocarbons claim 1 , such as butane and propane claim 1 , and ammonia solutions.4101102103104. A method as claimed in claim 1 , wherein heat exchange equipments (C- claim 1 , C- claim 1 , C- claim 1 , C-) are common to the compression and compressed air expansion steps.5101102103104. A method as claimed in claim 1 , wherein at least one heat exchange equipment (C- claim 1 , C- claim 1 , C- claim 1 , C-) uses the technology of heat exchange without direct contact between the fluids.6101102103104. A method as claimed in claim 1 , wherein at least one ...

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Номер записи: 81

04-06-2015 дата публикации

High pressure ratio compressors with multiple intercooling and related methods

Номер: US20150152884A1

Автор: Andrea GABBRIELLI, Denis Guillaume GUENARD, Fabio BOZZONE, Giorgio Greco, Nicola Banchi, Remo Tacconelli

Принадлежит: Nuovo Pignone Srl

Turbo-compressor/generator trains including high pressure ratio compressors with multiple intercooling and related methods are provided. A high pressure ratio compressor with multiple intercooling includes a casing with plural chambers, one or more shafts penetrating inside the chambers, and impellers mounted on the one or more shafts inside the chambers, respectively. Each chamber has a gas inlet and a gas outlet to allow gas flow to be input into and to be output from the respective chamber. A gas flow is successively compressed in each of the chambers, and is cooled outside the compressor when transferring from one chamber to a next chamber among the plural chambers.

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Номер записи: 82

07-05-2020 дата публикации

REVERSE FLOW ENGINE ARCHITECTURE

Номер: US20200141416A1

Автор: Plante Ghislain, VALOIS Patrick

Принадлежит:

A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft. 1. A reverse flow gas turbine engine comprising: a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction , the LP spool comprising an LP compressor drivingly connected to an LP turbine via an LP compressor gear train; the HP spool comprising an HP compressor in flow communication with the LP compressor , and an HP turbine disposed forward of the HP compressor and aft of the LP turbine , the HP turbine being drivingly connected to the HP compressor via an HP shaft.2. The reverse flow gas turbine engine defined in claim 1 , wherein the LP spool further comprises an LP compressor shaft drivingly connected to the LP compressor gear train claim 1 , and wherein the LP compressor shaft is disposed entirely forward of the HP shaft.3. The reverse flow gas turbine engine defined in claim 2 , wherein the LP spool further comprises an LP turbine shaft drivingly connected to a reduction gearbox (RGB) having an output shaft adapted to be connected to a rotatable load.4. The reverse flow gas turbine engine defined in claim 3 , wherein the LP compressor shaft is parallel to the LP turbine shaft claim 3 , and wherein both shafts extend forward of the LP turbine.5. The reverse flow gas turbine engine defined in claim 3 , wherein the LP compressor shaft branches off at an angle from the LP turbine shaft.6. The reverse flow gas turbine engine defined in claim 5 , wherein the LP compressor is non-coaxially disposed with respect to the LP turbine.7. The reverse flow gas turbine ...

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Номер записи: 83

07-06-2018 дата публикации

EROSION SUPPRESSION SYSTEM AND METHOD IN AN EXHAUST GAS RECIRCULATION GAS TURBINE SYSTEM

Номер: US20180156136A1

Автор: DELLA-FERA Gabriel, Denman Todd F., Ellis Scott E.

Принадлежит:

In an embodiment, a method includes flowing an exhaust gas from a turbine of a gas turbine system to an exhaust gas compressor of the gas turbine system via an exhaust recirculation path; evaluating moist flow parameters of the exhaust gas within an inlet section of the exhaust gas compressor using a controller comprising non-transitory media programmed with instructions and one or more processors configured to execute the instructions; and modulating cooling of the exhaust gas within the exhaust recirculation path, heating of the exhaust gas within the inlet section of the exhaust gas compressor, or both, based on the evaluation. 1. A method , comprising:flowing an exhaust gas from a turbine of a gas turbine system to an exhaust gas compressor of the gas turbine system via an exhaust recirculation path;evaluating moist flow parameters of the exhaust gas within an inlet section of the exhaust gas compressor using a controller comprising non-transitory media programmed with instructions and one or more processors configured to execute the instructions; andmodulating cooling of the exhaust gas within the exhaust recirculation path, heating of the exhaust gas within the inlet section of the exhaust gas compressor, or both, based on the evaluation.2. The method of claim 1 , wherein evaluating moist flow parameters of the exhaust gas within the inlet section of the exhaust gas compressor comprises estimating a projected droplet size and flux of the exhaust gas at a portion of the exhaust gas compressor based at least in part on the evaluation of the moist flow parameters of the exhaust gas claim 1 , wherein the cooling modulation of the exhaust gas and/or the heating modulation of the exhaust gas is made based at least partially on the projected droplet size and flux.3. The method of claim 2 , wherein evaluating moist flow parameters of the exhaust gas within the inlet section of the exhaust gas compressor comprises:monitoring relative humidity within the inlet section ...

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Номер записи: 84

22-09-2022 дата публикации

METHOD AND SYSTEM FOR POWER PRODUCTION WITH IMPROVED EFFICIENCY

Номер: US20220298969A1

Автор: Allam Rodney John, Fetvedt Jeremy Eron, Forrest Brock Alan

Принадлежит:

The present disclosure relates to systems and methods that provide power generation using predominantly COas a working fluid. In particular, the present disclosure provides for the use of a portion of the heat of compression from a COcompressor as the additive heating necessary to increase the overall efficiency of a power production system and method. 1. A method for heating a recirculating gas stream comprising:{'sub': 1', '1', '2', '1, 'passing a gas stream G at a pressure Pand a temperature Tthrough a recuperative heat exchanger such that the gas stream is cooled to a temperature Tthat is less than T;'}{'sub': 1', '2, 'separating the gas stream G into a first fraction Gand a second fraction G;'}{'sub': 1', '2', '1, 'compressing the gas stream fraction Gto a pressure Pthat is greater than P;'}{'sub': 2', '3', '1', '2', '3', '2, 'compressing the gas stream fraction Gto a pressure Pthat is greater than Pso as to heat the gas stream fraction Gto a temperature Tthat is greater than T;'}{'sub': '2', 'withdrawing the heat from the compressed gas stream fraction G;'}{'sub': 1', '2', 'C, 'combining the gas stream fraction Gand the gas stream fraction Gto form a combined recirculating gas stream G;'}{'sub': C', '4', '2', '3, 'pumping the recirculating gas stream Gto a pressure Pthat is greater than Pand greater than P; and'}{'sub': C', 'C, 'passing the recirculating gas stream Gto the recuperative heat exchanger such that the gas stream Gis heated by the cooling gas stream G;'}{'sub': 2', 'C', '4, 'wherein the heat withdrawn from the compressed gas stream fraction Gis added to the recirculating gas stream Gafter pumping to pressure P.'}2. The method according to claim 1 , wherein the temperature Tis about 100° C. to about 400° C.3. The method according to claim 1 , wherein the pressure Pof gas stream fraction Gand the pressure Pof gas stream fraction Gare each separately about 40 bar (4 MPa) to about 100 bar (10 MPa).4. The method according to claim 1 , wherein the ...

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Номер записи: 85

23-05-2019 дата публикации

GAS TURBINE BLOWER/PUMP

Номер: US20190153938A1

Автор: HAMMOUD OMAR

Принадлежит:

A low emission, high efficiency Gas Turbine engine operating on a combination of Natural Gas and Bio Gas as fuel, driving either a high efficiency turbo-blower or a high efficiency Turbo Pump system combined with heat recovery systems and in other embodiments is provided a generator of electricity or providing evaporate cooling from using the remaining waste heat in the exhaust gas. 1. A unit having:(a) a first inlet and first outlet;(b) a second inlet and second outlet;(c) an impeller disposed between said first inlet and said first outlet;(d) a compressor for elevating the pressure of air;(e) a recuperator for increasing the temperature of said air at said elevated pressure;(f) a gas turbine disposed between said second inlet and said second outlet;(g) a combustor for receiving a combustion mixture comprising said air at said elevated temperature and said elevated pressure, and fuel introduced into said second inlet to drive said gas turbine and exhaust through said second outlet;(h) the impeller disposed between said first inlet and said first outlet; and(i) said gas turbine and said impeller directly connected to a shaft so as to drive said impeller and move a fluid from said first inlet to said first outlet.2. A unit as claimed in wherein said fluid is air and said impeller is an air blower.3. A unit as claimed in wherein said fluid is water and said impeller is a pump.4. A unit as claimed in wherein said combustion mixture includes air and a gas selected from the group of natural gas and biogas.5. A unit as claimed in wherein said gas turbine comprises a high pressure turbine and a free powered turbine and wherein said free powered turbine and said impeller are connected to a common shaft.6. A unit as claimed in wherein said gas turbine comprises a high pressure turbine claim 1 , a low pressure turbine claim 1 , and free powered turbine and wherein said free powered turbine and said impeller are connected to a common shaft.7. A unit as claimed in including an ...

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Номер записи: 86

23-05-2019 дата публикации

MICRO-TURBINE GAS GENERATOR AND PROPULSIVE SYSTEM

Номер: US20190153948A1

Автор: Evulet Andrei

Принадлежит:

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor. 1. A combustor , comprising:a first toroidal casing circumscribing an axis and having an inlet configured to receive fluid, the first casing defining a first internal chamber in fluid communication with the inlet;a second toroidal casing disposed within the first internal chamber and circumscribing the axis, the second casing having an outer wall defining a second internal chamber, the outer wall having a plurality of orifices formed therethrough, the orifices providing fluid communication between the first and second chambers;a plurality of fuel injectors positioned to inject fuel into the second chamber through the orifices; andoutlet structure defining at least one channel in fluid communication with the second chamber, the at least one channel being oriented parallel to the axis.2. The combustor of claim 1 , wherein the orifices are oriented at an oblique angle with respect to the outer wall.3. The combustor of claim 1 , further comprising an ignition source positioned within the second chamber.4. The combustor of claim 1 , wherein the outlet structure comprises an inner wall converging toward the outer wall and is configured to urge high-temperature fluid flowing about the axis within the second chamber through the at least one channel.5. The combustor of claim 1 , further comprising a ...

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Номер записи: 87

23-05-2019 дата публикации

COMPRESSOR INJECTOR APPARATUS AND SYSTEM

Номер: US20190153949A1

Автор: Hiester Paul

Принадлежит: UNITED TECHNOLOGIES CORPORATION

Cooling systems for high pressure compressor systems are provided. The cooling systems may comprise tangential on board injectors (“TOBIs”). The TOBIs may comprise one or more fluid channels configured to conduct cooling fluid flow to components of the compressor, including, for example, disk-hub portions of the compressor. In this regard, the TOBI may be configured to exhaust cooling air in a manner such that the exhausted air has a similar linear velocity of the disk-hub portion. The cooling air may also be exhausted in a manner that is substantially parallel to the disk-hub portion. 1. A compressor , comprising:a disk-hub;a stator portion;a rotor portion coupled to the disk hub, the rotor portion adjacent to and aft the stator portion;an exit guide vane adjacent to and aft the rotor portion;a dual tangential on-board injector (“dual TOBI”) disposed radially inward of the exit guide vane and the rotor portion, wherein the dual TOBI is configured to conduct a cooling flow to a section of the disk hub adjacent the stator portion.2. The compressor of claim 1 , wherein the rotor portion is coupled to the disk-hub by a blade attachment.3. The compressor of claim 2 , wherein the blade attachment defines a fluid conduit.4. The compressor of claim 3 , wherein the dual TOBI includes a first channel defined within a portion of a root of the exit guide vane and a second channel defined within a portion of a root of the rotor portion.5. The compressor of claim 4 , wherein the first channel and the second channel are in fluid communication.6. The compressor of claim 4 , wherein the first channel is operatively coupled to the second channel via the fluid conduit.7. The compressor of claim 4 , wherein a first pressure (P) in the first channel is equivalent to a second pressure (P) adjacent and aft the exit guide vane.8. The compressor of claim 7 , wherein a third pressure (P) in the second channel is equivalent to a fourth pressure (P) that is in a section between the stator ...

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Номер записи: 88

08-06-2017 дата публикации

MICRO-TURBINE GAS GENERATOR AND PROPULSIVE SYSTEM

Номер: US20170159565A1

Автор: Evulet Andrei

Принадлежит:

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor. 1. A propulsion system , comprising:a first compressor in fluid communication with a fluid source;a first conduit coupled to the first compressor;a heat exchanger in fluid communication with the first compressor via the first conduit;a second conduit positioned proximal to the heat exchanger;a combustor in fluid communication with the heat exchanger via the second conduit and configured to generate a high-temperature gas stream;a third conduit coupled to the combustor; anda first thrust augmentation device in fluid communication with the combustor via the third conduit, the heat exchanger being positioned within the gas stream generated by the combustor.2. The propulsion system of claim 1 , wherein the heat exchanger is disposed within the third conduit.3. The propulsion system of claim 1 , further comprising a turbine coupled to the first compressor and positioned between the combustor and the heat exchanger.4. The propulsion system of claim 3 , wherein the turbine comprises ceramic matrix composites.5. The propulsion system of claim 3 , further comprising a second compressor coupled to the turbine.6. The propulsion system of claim 5 , wherein the turbine is fixedly coupled to the first compressor and is coupled to the second compressor via a clutch.7. The propulsion system of claim 1 , further ...

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Номер записи: 89

23-05-2019 дата публикации

INTERCOOLED COOLING AIR TAPPED FROM PLURAL LOCATIONS

Номер: US20190154059A1

Автор: Chandler Jesse M., Merry Brian D., Staubach Joseph Brent, Suciu Gabriel L.

Принадлежит:

A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed. 1. A gas turbine engine comprising;a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations;a turbine section having a high pressure turbine;a first tap tapping air from at least one of said more upstream locations in said main compressor section, passing said tapped air through a heat exchanger and then to a cooling compressor, said cooling compressor compressing air downstream of said heat exchanger; anda second tap tapping air from a location closer to said downstream most end than the location(s) of said first tap, and said first and second tap mixing together and being delivered into said high pressure turbine.2. The gas turbine engine as set forth in claim 1 , wherein a main fan delivers bypass air into a bypass duct and into said main compressor section and said heat exchanger positioned within said bypass duct to be cooled by bypass air.3. The gas turbine engine as set forth in claim 1 , wherein air temperatures at said downstream most location of said high pressure compressor are greater than or equal to 1350° F.4. The gas turbine engine as set forth in claim 1 , wherein the second tap is at said downstream most end.5. The gas turbine engine as set forth in claim 4 , wherein air from said first ...

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Номер записи: 90

23-05-2019 дата публикации

Contoured wall heat exchanger

Номер: US20190154345A1

Автор: Curt Edward Hogan, Jared Matthew Wolfe, Jeffrey Douglas Rambo, Michael Stephen Popp, Nicolas Kristopher Sabo, Ramon Martinez

Принадлежит: General Electric Co

A heat exchanger and heat exchanger core are provided. The heat exchanger core includes a plurality of columnar passages extending between an inlet plenum of the heat exchanger core and an outlet plenum of the heat exchanger core, the columnar passages formed monolithically in a single fabrication process.

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Номер записи: 91

21-06-2018 дата публикации

System for reducing inlet air temperature of a device

Номер: US20180172294A1

Автор: Charles Melvin Owen

Принадлежит: AAF Ltd

The present embodiments disclose a system ( 100 ) for reducing inlet air temperature of a device, comprising: a fogging system that provides air cooling, wherein the fogging system comprises at least one low pressure atomiser ( 110 ).

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Номер записи: 92

06-06-2019 дата публикации

MAGNETIC COOLING SYSTEMS

Номер: US20190170407A1

Автор: Hammer Kimberly Nicole, Johnson Francis, Santini Marco, Srivastava Vijay Kumar, Zia Jalal Hunain

Принадлежит:

A magnetic cooling system is presented. The system includes at least one magnetic assembly, at least one magnetic regenerator including a magnetocaloric material, movably arranged in a closed loop to cyclically pass through the at least one magnetic assembly and a fluid supply device in fluid communication with the at least one magnetic assembly to supply a cooling fluid to the at least one magnetic assembly. A turbine assembly including a magnetic cooling system disposed in a path of an inlet air to a turbine system is also presented. 1. A magnetic cooling system , comprising:at least one magnetic assembly;at least one magnetic regenerator comprising a magnetocaloric material, movably arranged in a closed loop to cyclically pass through the at least one magnetic assembly; anda fluid supply device in fluid communication with the at least one magnetic assembly to supply a cooling fluid to the at least one magnetic assembly.2. The magnetic cooling system of claim 1 , wherein the at least one magnetic assembly is disposed in a casing having an inlet port allowing the magnetic assembly in fluid communication with the fluid supply device and an outlet port allowing the magnetic assembly in fluid communication with an outside environment of the casing.3. The magnetic cooling system of claim 1 , wherein the at least one magnetic regenerator comprises a plate claim 1 , a sheet claim 1 , a strip claim 1 , a foil claim 1 , or a combination thereof.4. The magnetic cooling system of claim 1 , wherein the at least one magnetic regenerator is arranged on a conveyor that passes through the at least one magnetic assembly and forms the closed loop.5. The magnetic cooling system of claim 1 , further comprising an inlet and an outlet allowing a to-be-cooled fluid to pass across the closed loop.6. The magnetic cooling system of claim 1 , wherein the magnetic cooling system comprises a plurality of magnetic regenerators movably arranged in the closed loop to cyclically pass through the ...

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Номер записи: 93

28-05-2020 дата публикации

STEAM TURBINE SYSTEM AND COMBINED CYCLE PLANT

Номер: US20200165971A1

Автор: ISHIGURO Tatsuo, Uechi Hideyuki

Принадлежит:

A steam turbine system () includes a steam turbine () in which a main flow path (C) through which a main steam flows is formed, and a saturated steam generation portion () that is configured to generate a saturated steam. The saturated steam generation portion () is configured to feed the saturated steam into a wet region (C) in which the main steam in the main flow path (C) is in a wet state via a hollow portion formed inside a stator vane () of the steam turbine (). The stator vane () has a plurality of supply ports that are formed such that the hollow portion is configured to communicate with the main flow path (C), and a discharge amount of the saturated steam increases from an inner circumferential side toward an outer circumferential side in a blade height direction. 112-. (canceled)13. An exhaust heat recovery plant comprising:a saturated steam generation portion that is configured to generate a saturated steam; andan exhaust heat recovery boiler that is configured to generate steam by using heat of an exhaust gas,wherein the saturated steam generation portion is configured to generate, as the saturated steam, a flash steam obtained by flashing water generated by the exhaust heat recovery boiler, andwherein the exhaust heat recovery plant is configured to heat at least one of water flowing through a water supply system which is configured to supply the water to the exhaust heat recovery boiler or condensed water generated by flushing the water, using a heat source other than the exhaust gas.14. A combined cycle plant comprising:{'claim-ref': {'@idref': 'CLM-00013', 'claim 13'}, 'the exhaust heat recovery plant according to ; and'}a gas turbine,wherein the exhaust gas from the gas turbine is supplied to the exhaust heat recovery boiler of the exhaust heat recovery plant, andwherein the exhaust heat recovery boiler is configured to generate the steam by using heat of the exhaust gas from the gas turbine.15. The exhaust heat recovery plant according to claim 13 ...

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Номер записи: 94

08-07-2021 дата публикации

Gas Turbine Engine Heat Exchanger for Annular Flowpaths

Номер: US20210207534A1

Автор: Boucher Amanda Jean, Chandler Jesse M., Staubach Joseph B.

Принадлежит:

A heat exchanger has arcuate inlet and outlet manifolds and a plurality of tube banks, each tube bank coupling one of the inlet manifold outlets to an associated one of the outlet manifold inlets. Each tube bank partially nests with one or more others of the tube banks and has: a first header coupled to the associated inlet manifold outlet and the associated the outlet manifold inlet; a second header; and a plurality of tube bundles each having a first end coupled to the associated first header and a second end coupled to the associated second header. A flowpath from the each inlet manifold outlet passes sequentially through flowpath legs formed by each of the tube bundles in the associated tube bank to exit the tube bank to the associated outlet manifold inlet. 2. The heat exchanger of wherein: a first end coupled to the associated inlet manifold outlet;', 'a second end coupled to the associated outlet manifold inlet;', 'at least one dividing wall between an upstream end of one said leg and a downstream end of the next adjacent downstream leg; and, 'each first header comprises a closed first end;', 'a closed second end; and', 'at least one dividing wall between a downstream end of one said leg and an upstream end of the next adjacent upstream leg., 'each second header comprises3. The heat exchanger of wherein: [ an inlet end;', 'an outlet end; and', 'a barrier between the inlet end and the outlet end and separating an inlet plenum from an outlet plenum;, 'a first header segment having, a closed first end; and', 'a closed second end;, 'a second header segment having, 'a first of the tube bundles extending between the inlet plenum and the second header segment; and', 'a second of the tube bundles extending between the second header segment and the outlet plenum;', 'the first header segments are secured end-to-end to form the first header; and', 'the second header segments are secured end-to-end to form the second header., 'each tube bank comprises a plurality of ...

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Номер записи: 95

04-06-2020 дата публикации

GAS TURBINE ENGINE AND METHODS OF OPERATING SAME

Номер: US20200173360A1

Автор: Cuevas-Alvarez Jose Antonio, Doublet Christophe, Kapoor Tarun, Wifling Ronald

Принадлежит:

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 ...

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Номер записи: 96

15-07-2021 дата публикации

MOBILE GAS TURBINE INLET AIR CONDITIONING SYSTEM AND ASSOCIATED METHODS

Номер: US20210215099A1

Автор: Rodriguez-Ramon Ricardo, Yeung Tony

Принадлежит: BJ Energy Solutions, LLC

A system, as well as associated methods, for increasing the efficiency of a gas turbine including an inlet assembly and a compressor may include a housing configured to channel airstream towards the inlet assembly, an air treatment module positioned at a proximal end the housing, and at least one air conditioning module mounted downstream of the air treatment module for adjusting the temperature of the airstream entering the compressor. The air treatment module may include a plurality of inlet air filters and at least one blower configured to pressurize the air entering the air treatment module. 1. An air treatment system to increase the efficiency of a gas turbine comprising an inlet assembly and a compressor , the inlet assembly located upstream of the compressor and forming an input side of the gas turbine , the air treatment system comprising:a housing positioned to channel an airstream towards the inlet assembly, the housing positioned upstream of the input side; and one or more inlet air filters to provide fluid flow to a first internal chamber, and', 'one or more blowers mounted in the first internal chamber and providing fluid flow to an interior of the housing via at least one outlet of the first internal chamber, the one or more blowers configured to pressurize the air entering the air treatment module, and', 'one or more air conditioning modules mounted downstream of the air treatment module to decrease the temperature of the airstream entering the compressor, such that the airstream enters the one or more air conditioning modules at a first temperature and exits the one or more air conditioning modules at a second temperature lower than the first temperature., 'an air treatment module positioned at a proximal end of the housing, the air treatment module comprising2. The air treatment system of claim 1 , wherein the one or more air conditioning modules comprise at least one chiller module.3. The air treatment system of claim 2 , wherein the at least one ...

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Номер записи: 97

05-07-2018 дата публикации

INTERCOOLED COOLING AIR

Номер: US20180187602A1

Автор: Chandler Jesse M., Merry Brian, Schwarz Frederick M., Snape Nathan, Suciu Gabriel L.

Принадлежит:

A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap and configured to deliver air to an aircraft fuselage. A cooling compressor is connected downstream of the heat exchanger. A high pressure feed is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor is configured to deliver air to at least one of the plurality of rotating components. A valve assembly that can select whether air from the first tap or air from the high pressure feed is delivered to the aircraft pneumatic system. 1. A gas turbine engine comprising:a plurality of rotating components housed within a compressor section and a turbine section;a first tap connected to said compressor section and configured to deliver air at a first pressure;a heat exchanger connected downstream of said first tap and configured to deliver air to an aircraft fuselage;a cooling compressor connected downstream of said heat exchanger;a high pressure feed configured to deliver air at a second pressure which is higher than said first pressure;said cooling compressor is configured to deliver air to at least one of said plurality of rotating components; anda valve assembly that can select whether air from said first tap or air from said high pressure feed is delivered to the aircraft pneumatic system.2. The gas turbine engine as set forth in claim 1 , wherein a mixer is provided downstream of said cooling compressor to receive air from a second tap to mix with the air downstream of the cooling compressor.3. The gas turbine engine as set forth in claim 2 , wherein air temperatures at said high pressure feed may be greater than or equal to 1350° F.4. The gas turbine engine as set forth in claim 2 , wherein said high pressure feed is connected to said ...

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Номер записи: 98

06-07-2017 дата публикации

SYSTEM AND METHOD FOR COMPRESSOR INTERCOOLER

Номер: US20170191750A1

Автор: Angel Paul R., De Barros Ian Alexandre Araujo, Richmond Paul, Stanley David, Storage Michael Ralph

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A method includes compressing an air flow to a first pressure, transferring heat from the air flow to a liquefaction fluid via an intercooler heat exchanger, compressing the air flow to a second pressure greater than the first pressure, combusting the air flow and a fuel to generate a combustion product flow, and driving a turbine with the combustion product flow. The turbine is configured to drive machinery of a liquefaction system. The liquefaction fluid includes at least one of a pre-cooling fluid, a refrigerant, and a liquefied product of the liquefaction system. 1. A system comprising: a first compressor stage configured to compress an air flow to a first pressure;', 'a second compressor stage configured to compress the air flow to a second pressure greater than the first pressure; and', 'a turbine disposed along an axis of the gas turbine system;, 'a gas turbine system comprising a body comprising a plurality of channels configured to receive a cooling fluid; and', 'a plurality of fins extending from the body, wherein the air flow is configured to flow over the plurality of fins, and the intercooler heat exchanger is configured to transfer heat from the air flow to the cooling fluid; and, 'an intercooler heat exchanger disposed between the first compressor stage and the second compressor stage, wherein the intercooler comprisesa liquefaction system indirectly coupled to the intercooler heat exchanger, wherein the liquefaction system comprises a liquefaction fluid, and the liquefaction fluid is configured to receive heat from the cooling fluid.2. The system of claim 1 , comprising a working fluid system coupled to the intercooler heat exchanger and to the liquefaction system claim 1 , wherein the working fluid system comprises a working fluid heat exchanger and a pumping system claim 1 , the pumping system is configured to circulate the cooling fluid from the intercooler heat exchanger to the working fluid heat exchanger claim 1 , and the working fluid heat ...

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Номер записи: 99

20-06-2019 дата публикации

GAS TURBINE EFFICIENCY AND POWER AUGMENTATION IMPROVEMENTS UTILIZING HEATED COMPRESSED AIR

Номер: US20190186301A1

Автор: AUERBACH SCOTT, KRAFT Robert J.

Принадлежит:

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 ...

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Номер записи: 100