Design method for subsea equipment subject to hydrogen induced stress cracking

Systems and methods for generating transfer functions associated with calculating local stresses on pipe elements by post processing forces and moments of a pipe model representing the piping system. The transfer functions are reusable and allow recalculation with different sets of user data without requiring regeneration of the transfer functions.

Device and method for gas turbine unlocking

An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.

Cooling system for gas turbine load coupling

The disclosure relates to a cooling system for a gas turbine load coupling. A gas turbine (33) is described, comprising at least a compressor (43), a power turbine (47), a load coupling (35) connecting said gas turbine (33) to a load (37), a load-coupling guard (65) at least partly surrounding the load coupling (35), a cooling air channeling (51, 61, 63) designed and arranged to circulate a cooling air flow in the load-coupling guard sufficient to remove heat from the load coupling (35).

Method for Subsea Equipment Subject to Hydrogen Induced Stress Cracking

Systems and methods for generating transfer functions associated with calculating local stresses on pipe elements by post processing forces and moments of a pipe model representing the piping system. The transfer functions are reusable and allow recalculation with different sets of user data without requiring regeneration of the transfer functions. 17.-. (canceled)8. A method for generating a transfer function for predicting local stresses on a subsea piping system element , the method comprising:(a) determining a three-dimensional model for said subsea piping system element;(b) iteratively running said three-dimensional model with a plurality of pipe geometric dimensions and loads and generating a series of component transfer functions describing local stress associated with said subsea piping system element; and(c) summing said series of component transfer functions to generate said transfer function.9. The method of claim 8 , wherein said pipe loads comprise moments and forces.10. The method of claim 8 , wherein said geometric dimensions comprise said subsea piping system element inner radius and outer radius.11. The method of claim 8 , wherein said local stress comprises hoop stress and radial stress.1220.-. (canceled) This application is a divisional application of U.S. patent application No. 12/772,289, filed May 3, 2010, which claims priority and benefit from, U.S. Provisional Patent Application Ser. No. 61/267,234, entitled “Design Method for Subsea Equipment Subject to Hydrogen Induced Stress Cracking”, filed on Dec. 7, 2009, the disclosure of which is incorporated here by reference.The present invention relates generally to subsea equipment piping design and, more specifically, to designing subsea piping systems subject to Hydrogen Induced Stress Cracking (HISC).The world's use of fossil fuels has grown exponentially over the past several decades. With this growth, the oil and gas industry has broadened the search for new oil and gas reserves to meet the ...

COOLING SYSTEM FOR GAS TURBINE LOAD COUPLING

A gas turbine is provided. The gas turbine comprises a compressor, a power turbine, a load coupling connecting the gas turbine to a load, a gas turbine package comprising a turbomachinery compartment housing the gas turbine, a load-coupling guard at least partly surrounding the load coupling, a cooling air circulation system for circulating cooling air in the turbomachinery compartment, and a cooling air channeling configured to circulate a cooling air flow from the cooling air circulation system in the load-coupling guard sufficient to remove heat from the load coupling. 1. A gas turbine comprising:a compressor;a power turbine;a load coupling connecting the gas turbine to a load;a gas turbine package comprising a turbomachinery compartment housing the gas turbine;a load-coupling guard at least partly surrounding the load coupling;a cooling air circulation system for circulating cooling air in the turbomachinery compartment; anda cooling air channeling configured to circulate a cooling air flow from the cooling air circulation system in the load-coupling guard sufficient to remove heat from the load coupling.2. The gas turbine according to claim 1 , comprising an air forcing device configured to force cooling air in the turbomachinery compartment and through the cooling air channeling in the load-coupling guard.3. The gas turbine according to claim 1 , further comprising an air intake line in fluid communication with the cooling air circulation system and with the cooling air channeling.4. The gas turbine according to claim 3 , wherein the air intake line is in fluid communication with an air intake plenum claim 3 , wherein combustion air enters the compressor from the air intake plenum.5. The gas turbine according to claim 3 , further comprising a filter arrangement configured to filter ambient air entering the air intake line.6. The gas turbine according to claim 1 , wherein the gas turbine is an aeroderivative gas turbine.7. The gas turbine according to claim 1 , ...

Gas Turbine with Primary and Secondary Lubricating Oil Cooler

A gas turbine including: a turbine package, a gas turbine, a ventilation system for cooling the interior of the turbine package, and a lubricating oil circuit. The lubricating oil circuit comprises a lubricating oil pump, a lubricating oil tank, a primary lubricating oil cooler, and a secondary lubricating oil cooler. The secondary lubricating oil cooler is arranged in the turbine package, in a position lower than a rotary shaft of the gas turbine. The ventilation system is arranged and designed such that at least part of a package cooling airflow contacts the secondary lubricating oil cooler to remove heat from the lubricating oil circulating in the secondary lubricating oil cooler. 1. A gas turbine comprising:a turbine package;a gas turbine arranged in the turbine package;a ventilation system for cooling the interior of the turbine package;a lubricating oil circuit, comprising a lubricating oil pump, a lubricating oil tank, a primary lubricating oil cooler, and a secondary lubricating oil cooler arranged in the turbine package, in a position lower than a rotary shaft of the gas turbine;wherein the ventilation system is arranged and designed such that at least part of a cooling airflow circulating in the turbine package contacts the secondary lubricating oil cooler for removing heat from the lubricating oil circulating in the secondary lubricating oil cooler.2. The gas turbine according to claim I , wherein the lubricating oil circuit further comprises a scavenger pump arranged upstream of the primary lubricating oil cooler.3. The gas turbine according to claim 2 , wherein the scavenger pump is arranged between the primary lubricating oil cooler and bearings of the gas turbine claim 2 , and the secondary lubricating oil cooler is arranged in a position lower than the bearings.4. The gas turbine according to claim 1 , comprising a combustion-air intake plenum in fluid communication with the compressor claim 1 , wherein lateral airflow passages are formed between ...

DEVICE AND METHOD FOR GAS TURBINE UNLOCKING

An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine. 1. An aeroderivative gas turbine comprising:an air intake plenum;a compressor with a compressor air intake in fluid communication with the air intake plenum;a combustor;a high pressure turbine;a power turbine;a forced air-stream generator arranged in fluid communication with the air intake plenum; anda shutter arrangement provided in a combustion-air flow path through which air enters the air intake plenum, the shutter arrangement being arranged and controlled to close the combustion-air flow path to pressurize the air intake plenum by the forced air-stream generator, up to a pressure sufficient to force pressurized air through the aeroderivative gas turbine.2. The aeroderivative gas turbine according to claim 1 , further comprising a silencer arrangement arranged in the combustion-air flow path claim 1 , wherein the shutter arrangement is disposed downstream of the silencer arrangement with respect to an air stream in the combustion-air flow path.3. The aeroderivative gas turbine according to claim 1 , wherein:the silencer arrangement comprises a plurality of parallel arranged silencer panels,an air passageway is defined between each pair of adjacent silencer panels, each air passageway having an air outlet aperture, anda shutter is movably arranged at each air outlet aperture, to selectively open and close the air passageway.4. The aeroderivative gas turbine ...

STATOR AERODYNAMIC COMPONENTS WITH NOZZLES AND METHODS FOR CLEANING A TURBOMACHINE

A stator aerodynamic component is disclosed to be placed inside a flow path of a working fluid of a turbomachine; the component has one or more nozzles for ejecting a liquid into the flow path; the liquid to be ejected comes from a duct internal to the component and in fluid communication with a pipe that is external to the component. Also disclosed is a method for cleaning a turbomachine by ejecting a washing liquid from one or more one stator aerodynamic components. 2. The stator aerodynamic component of claim 1 , wherein the component has a leading edge region and a trailing edge region claim 1 , and wherein said one or more nozzles are located in the trailing edge region.3. The stator aerodynamic component of claim 1 , wherein the component has a leading edge region and a trailing edge region claim 1 , and wherein said duct is located in the leading edge region.42. The stator aerodynamic component of claim 1 , wherein at least one of said nozzles is arranged to eject liquid in an ejection direction (ED-) corresponding to a flow direction (FD) of said flow path.534. The stator aerodynamic component of claim 1 , wherein at least one of said nozzles is arranged to eject liquid in an ejection direction (ED- claim 1 , ED-) inclined with respect to a flow direction (FD) of said flow path.645. The stator aerodynamic component of claim 5 , wherein said ejection direction (ED-) is inclined by an angle between +5° and +90° or wherein said ejection direction (ED-) is inclined by an angle between −5° and −90°.7. The stator aerodynamic component of claim 1 , wherein said nozzles are arranged to eject liquid in different directions.8. The stator aerodynamic component of claim 1 , wherein said one or more nozzles are arranged to eject liquid so to reach one or more blades and/or one or more vanes of the turbomachine.9161718262728. The stator aerodynamic component of claim 1 , wherein said one or more nozzles are arranged to eject liquid so to reach suction side (V-P- claim 1 , ...

COMPOSITE MATERIAL INLET PLENUM AND GAS TURBINE ENGINE SYSTEM COMPRISING SAID PLENUM

An air inlet plenum for a gas turbine engine is described. The air inlet plenum comprises a hollow body having an air inlet aperture and an air outlet aperture arranged and configured for connection to the gas turbine engine. The air inlet plenum comprises at least one removable portion, which is removable from the hollow body when the air inlet plenum is connected to a gas turbine engine. The air inlet plenum is at least partly made of fiber-reinforced plastic. 1. An air inlet plenum for a gas turbine engine , comprising: a hollow body having an air inlet aperture and an air outlet aperture arranged and configured for connection to the gas turbine engine; at least one removable portion , which is removable from the hollow body when the air inlet plenum is connected to a gas turbine engine; wherein the air inlet plenum is at least partly made of fiber-reinforced plastic.2. The air inlet plenum of claim 1 , having a weight of less than 1000 kg.3. The air inlet plenum of claim 1 , wherein said at least one removable portion has a weight of 40 kg or less claim 1 , and preferably of 20 kg or less.4. The air inlet plenum of claim 1 , wherein said air outlet is provided with a connection flange formed by at least two flange portions claim 1 , and wherein at least one of said flange portions is removable from the hollow body and forms said at least one removable portion of the air inlet plenum.5. The air inlet plenum of claim 4 , wherein both said at least two flange portions are removable from the hollow body.6. The air inlet plenum of claim 4 , wherein said connection flange is formed by two substantially symmetrical flange portions claim 4 , and wherein at least one of said two flange portions is removable from the hollow body.7. The air inlet plenum of claim 4 , wherein both said two flange portions are removable from the hollow body.8. The air inlet plenum of claim 4 , wherein said connection flange is provided with a sealing ring.9. The air inlet plenum of claim 1 , ...

DEVICE AND METHOD FOR GAS TURBINE UNLOCKING

An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine. 1. A method for unlocking a rotor in an aeroderivative gas turbine following shutdown of the aeroderivative gas turbine , the method comprising:arranging an air intake plenum of the aeroderivative gas turbine in fluid communication with a combustion-air flow path of the aeroderivative gas turbine, a compressor air intake, and a forced air-stream generator;arranging and controlling a shutter arrangement to selectively open and close the combustion-air flow path, wherein the shutter arrangement is in the combustion-air flow path through which air enters the air intake plenum;selectively opening and closing, by at least one shutter in the shutter arrangement, a plurality of air passageway defined between respective pairs of adjacent parallel arranged silencer panels, each air passageway having an air outlet aperture; andcooling the rotor when the rotor is locked following shut down of the aeroderivative gas turbine, by closing the shutters of the shutter arrangement and generating an overpressure in the air intake plenum by using the forced air-stream generator, the overpressure being sufficient to force pressurized air through the locked rotor of the aeroderivative gas turbine.2. The method according to claim 1 , wherein the overpressure ranges between 0.05 and 0.3 Bar above ambient pressure.3. The method according to claim 1 , wherein the overpressure ranges between ...

MOUNTING SYSTEM FOR ROTATING MACHINERY

A mounting system for supporting rotary machinery on a supporting structure of an off-shore installation, the system including a base frame provided with an upper side, for mounting the rotary machinery and a lower side, a set of at least four supporting members arranged at the lower side of the base frame and adapted to be placed on the supporting structure to act as an intermediate layer or frame between the base frame and the supporting structure in mounting condition. The supporting members include resilient elements generating a reaction force when subject to load and are configured to transfer to the base frame stresses and/or strains lower than allowable limits also in case of deformation of the supporting structures; the base frame has stiffness such as to guarantee design acceptance criteria for example for rotary machinery alignment, terminal points or interface point displacement, dynamic behavior or like parameters. 1. A mounting system for supporting rotary machineries on a supporting structure of an off-shore installation , the system comprising:a base frame having an upper side for mounting the rotary machineries and a lower side; anda set of at least four supporting members arranged at the lower side of the base frame and adapted to be placed on the supporting structure;wherein the supporting members comprise resilient elements generating a reaction force when subject to a load;wherein the system has stiffness adapted to guarantee rotary machineries alignment, or to minimize the displacement between a point on the machineries and an absolute reference point located in a fixed position with respect to the supporting structure, or to minimize the dynamic behavior of the base frame; andwherein the supporting members are configured to transfer to the base plate stresses and/or strains lower than allowable limits also in case of deformation of the supporting structures.2. The mounting system according to claim 1 , wherein the supporting members are ...

DEVICE AND METHOD FOR SLOW TURNING OF AN AERODERIVATIVE GAS TURBINE

An aeroderivative gas turbine, including a gas generator, a gas generator rotor, a power turbine section, and a slow turning device, wherein said slow turning device is designed and arranged to keep said rotor in rotary motion after turbine shut-down. 1. An aeroderivative gas turbine comprising:a gas generator;a gas generator rotor;a power turbine section; anda slow turning device,wherein the slow turning device is configured to keep the gas generator rotor in rotary motion after the aeroderivative gas turbine is shutdown.2. The aeroderivative gas turbine according to claim 1 , further comprising an auxiliary gear box claim 1 , wherein the slow turning device is selectively engageable to and disengageable from the auxiliary gear box.3. The aeroderivative gas turbine according to claim 2 , wherein the slow turning device is selectively engageable to and disengageable from a fuel pump port of the auxiliary gear box.4. The aeroderivative gas turbine according to claim 2 , wherein the auxiliary gear box is drivingly connected to the gas generator rotor.5. The aeroderivative gas turbine according to claim 1 , further comprising an auxiliary gear box comprising a hollow splined shaft claim 1 , wherein a first clutch portion is rotatingly engaged to the hollow splined shaft claim 1 , and wherein a second clutch portion is selectively connectable to and disconnectable from the first clutch portion.6. The aeroderivative gas turbine according to claim 5 , wherein the first clutch portion comprises slots claim 5 , and the second clutch portion comprises pins selectively engageable into the slots claim 5 , or vice-versa.7. The aeroderivative gas turbine according to claim 1 , wherein the slow turning device comprises an actuator configured to selectively engage the slow turning device to the gas generator rotor.8. The aeroderivative gas turbine according to claim 7 , wherein the actuator is an electric actuator claim 7 , and is configured to be energized when the aeroderivative ...

Multilayered panel for machinery enclosure

A panel for machinery enclosure, particularly for turbomachine enclosures. More specifically, a multilayered panel including several different layers each performing a specific function. In particular, the multilayered panel is capable to provide high levels of jet fire and fire/blast protection together with high performances in term of noise abatement with a lighter structure with respect to the panels of the prior art.

Device and method for gas turbine unlocking after shut down

An aeroderivative gas turbine (102) is disclosed, comprising: an air intake plenum (103); a compressor with a compressor air intake in fluid communication with the air intake plenum(103); a combustor; a high pressure turbine; a power turbine. A forced air-stream generator (111) is arranged in fluid communication with the air intake plenum (103). A shutter arrangement (123) is provided in a combustion-air flow path (105), arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator (111) to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine (102).

Composite material inlet plenum and gas turbine engine system comprising said plenum

An air inlet plenum for a gas turbine engine is described. The air inlet plenum (3) comprises a hollow body (17) having an air inlet aperture (19) and an air outlet aperture (21) arranged and configured for connection to the gas turbine engine (6). The air inlet plenum (3) comprises at least one removable portion (23L, 23R), which is removable from the hollow body (17) when the air inlet plenum (3) is connected to a gas turbine engine (6). The air inlet plenum is at least partly made of fiber-reinforced plastic.

Multilayered panel for machinery enclosure

The present invention relates to a panel for machinery enclosure, particularly for turbomachine enclosures. More specifically, the present invention relates to a multilayered panel comprising several different layers (1, 2, 3, 4) each performing a specific function. In particular, the multilayered panel according to the present invention is capable to provide high levels of jet fire and fire/blast protection together with high performances in term of noise abatement with a lighter structure with respect to the panels of the prior art.

Device and method for slow turning of an aeroderivative gas turbine

An aeroderivative gas turbine is described, comprising a gas generator (20), a gas generator rotor, a power turbine section, and a slow turning device (33), wherein said slow turning device is designed and arranged to keep said rotor in rotary motion after turbine shut-down.

Device and method for slow turning of an aeroderivative gas turbine

An aeroderivative gas turbine is described, comprising a gas generator (20), a gas generator rotor, a power turbine section, and a slow turning device (33), wherein said slow turning device is designed and arranged to keep said rotor in rotary motion after turbine shut-down.

Gas turbine with primary and secondary lubricating oil cooler

A gas turbine is described, comprising a turbine package (101) housing a compressor (105; 107), a high pressure turbine (109) and a power turbine (111). The gas turbine comprises a ventilation system for cooling the interior of the turbine package, as well as a lubricating oil circuit. The lubricating oil circuit comprises a lubricating oil pump (177), a lubricating oil tank (173), a primary lubricating oil cooler (189). A secondary lubricating oil cooler (163) is arranged in the turbine package (101), in a position lower than a rotary shaft (115) of the gas turbine. The ventilation system is arranged and designed such that at least part of a package cooling airflow contacts the secondary lubricating oil cooler (163) to remove heat from the lubricating oil circulating in the secondary lubricating oil cooler.

Design method for subsea equipment subject to hydrogen induced stress cracking

Cooling system for gas turbine load coupling

A gas turbine (33) is described, comprising at least a compressor (43), a power turbine (47), a load coupling (35) connecting said gas turbine (33) to a load (37), a load-coupling guard (65) at least partly surrounding the load coupling (35), a cooling air channeling (51, 61, 63) designed and arranged to circulate a cooling air flow in the load-coupling guard sufficient to remove heat from the load coupling (35).

Design method for subsea equipment subject to hydrogen induced stress cracking

Systems and methods for generating transfer functions associated with calculating local stresses on pipe elements by post processing forces and moments of a pipe model representing the piping system. The transfer functions are reusable and allow recalculation with different sets of user data without requiring regeneration of the transfer functions.

Heat recovery steam generator with parallel tube bundles

The disclosure concerns a heat exchanger, and in particular a waste heat recovery unit used to generate steam. In particular, the heat exchanger is provided with two or more separate tube bundles, each tube bundle being arranged in a separate section of a shell. An additional separate by-pass section is arranged in the middle of the shell. A first heat exchanging fluid, in particular a waste heat fluid, flows through the shell and is distributed between the separate sections of the shell and a second heat exchanging fluid, in particular water, flows through each tube bundle and exchanges heat with the first heat exchanging fluid. Alternatively, at least one tube bundle is flown by a different heat exchanging fluid.

Multilayered panel for machinery enclosure

The present invention relates to a panel for machinery enclosure, particularly for turbomachine enclosures. More specifically, the present invention relates to a multilayered panel comprising several different layers (1, 2, 3, 4) each performing a specific function. In particular, the multilayered panel according to the present invention is capable to provide high levels of jet fire and fire/blast protection together with high performances in term of noise abatement with a lighter structure with respect to the panels of the prior art.

Multilayered panel for machinery enclosure

Sistema de montagem para suportar maquinaria rotativa em uma estrutura de suporte de uma instalação em alto mar

SISTEMA DE MONTAGEM PARA SUPORTAR MAQUINARIA ROTATIVA EM UMA ESTRUTURA DE SUPORTE DE UMA INSTALAÇÃO EM ALTO MAR. Um sistema de montagem para suportar a maquinaria rotativa em uma estrutura de apoio de uma instalação em alto mar, o sistema compreendendo um quadro de base fornecido com um lado superior, para a montagem da maquinaria rotativa e um lado inferior, um conjunto de pelo menos quatro membros de suporte dispostos no lado inferior do quadro de base e adaptado para ser colocado na estrutura de suporte para atuar como uma camada intermediária ou quadro entre o quadro de base e a estrutura de suporte na condição de montagem. Os membros de suporte compreendem elementos resilientes que geram uma força de reação quando sujeitos a carga e estão configurados para transferir para o quadro de base tensões e/ou deformações inferiores aos limites admissíveis também em caso de deformação das estruturas de suporte; o quadro de base tem rigidez, como para garantir critérios de aceitação de design, por exemplo, para o alinhamento de maquinarias rotativas, pontos terminais ou deslocamento de ponto de interface, comportamento dinâmico ou parâmetros semelhantes.

Macchina di stampa con dispositivo di regolazione automatico e micrometrico delle pressioni di stampa per hot foil.

Macchina goffratrice a regolazioni multiple

Método para estimar craqueamento

método para estimar craqueamento e sistema executável por computador. a presente invenção refere-se, em geral a um projeto de tubulação de equipamento submarino e mais especificamente, ao projeto de sistemas de tubulação submarina e,submetida a craqueamento por estresse induzido por hidrogênio (hisc-hydrogen induced stress cracking).o método associado a um sistema de tubulação submarino compreende determinar um modelo unidimensional para um elemento do dito sistema de tubulação submarino, realizar uma análise unidimensional para o dito elemento com o uso do dito modelo unidimensional e uma pluralidade de condições operacionais para identificar pelo menos um ponto associado ao craqueamento sob estresse induzido por hidrogênio para o dito elemento,aplicar pelo menos uma função de transferência ao dito pelo menos um ponto para transformar. o dito pelo menos um ponto de uma representação de uma dimensão em uma estimativa de estresse local, para uma primeira conformidade predeterminada, e se a dita estimativa de estresse local for não compatível, então, determinar e executar um submodelo tridimensional para o dito elemento e analisar a capacidade do dito submodelo tridimensional (112,208) para uma seguinte conformidade predeterminada.

Macchina goffratrice a regolazioni multiple

Macchina goffratrice a regolazioni multiple

sistema de montagem para suportar maquinaria rotativa em uma estrutura de suporte de uma instalação em alto mar

sistema de montagem para suportar maquinaria rotativa em uma estrutura de suporte de uma instalação em alto mar. um sistema de montagem para suportar a maquinaria rotativa em uma estrutura de apoio de uma instalação em alto mar, o sistema compreendendo um quadro de base fornecido com um lado superior, para a montagem da maquinaria rotativa e um lado inferior, um conjunto de pelo menos quatro membros de suporte dispostos no lado inferior do quadro de base e adaptado para ser colocado na estrutura de suporte para atuar como uma camada intermediária ou quadro entre o quadro de base e a estrutura de suporte na condição de montagem. os membros de suporte compreendem elementos resilientes que geram uma força de reação quando sujeitos a carga e estão configurados para transferir para o quadro de base tensões e/ou deformações inferiores aos limites admissíveis também em caso de deformação das estruturas de suporte; o quadro de base tem rigidez, como para garantir critérios de aceitação de design, por exemplo, para o alinhamento de maquinarias rotativas, pontos terminais ou deslocamento de ponto de interface, comportamento dinâmico ou parâmetros semelhantes.

Turbina a gás e método para operar uma turbina a gás

Zusammensetzbare Teile zur Herstellung eines sonnenbrechenden Gitters und entsprechender Verbindungselemente

Generatore di vapore a recupero di calore a fasci paralleli

Componente aerodinâmico de estator e turbomáquina

COMPONENTES AERODINÂMICOS DE ESTATOR COM BOCAIS E ME'TODOS DE LIMPEZA DE UMA TURBOMÁQUINA. Trata-se de um componente aerodinâmico de estator (130, 250) que é colocado dentro de uma trajetória de fluxo (500) de um fluido de trabalho de uma turbomáquina (1000); sendo que o componente (130, 250) tem um ou mais bocais (135, 255) para ejetar um líquido na trajetória de fluxo (500); o líquido a ser ejetado vem de um duto (134 e 254) interno ao componente (130 e 250) e em comunicação fluida com um tubo (120 e 220) que é externo ao componente (130 e 250). É revelado também um método de limpeza de uma turbomáquina mediante a ejeção de um líquido de lavagem a partir de um ou mais componentes aerodinâmicos de estator.