US20140255145A1 - Systems and Methods for Providing a Flow of Purge Air and an Adjustable Flow of Cooling Air in a Gas Turbine Application - Google Patents
Systems and Methods for Providing a Flow of Purge Air and an Adjustable Flow of Cooling Air in a Gas Turbine Application Download PDFInfo
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- US20140255145A1 US20140255145A1 US13/790,863 US201313790863A US2014255145A1 US 20140255145 A1 US20140255145 A1 US 20140255145A1 US 201313790863 A US201313790863 A US 201313790863A US 2014255145 A1 US2014255145 A1 US 2014255145A1
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- Prior art keywords
- cooling air
- flow
- assembly
- stator
- cavity
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- Embodiments of the disclosure relate generally to gas turbine engines and more particularly to systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity and/or a stator cavity.
- a typical gas turbine engine includes a compressor at the front, one or more combustors around the middle, and a turbine at the rear.
- the compressor imparts kinetic energy to the working fluid (e.g., air) to produce a compressed working fluid at a highly energized state.
- the compressed working fluid exits the compressor and flows to the combustors where it mixes with fuel and ignites to generate combustion gases having a high temperature and pressure.
- the combustion gases flow to the turbine where they expand to produce work. Consequently, the turbine is exposed to very high temperatures due to the combustion gases.
- the various turbine components typically need to be cooled and/or supplied purge air. Accordingly, there is a need to provide improved turbine cooling systems and methods.
- a turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly.
- At least one fixed purge air orifice may be associated with the stator assembly.
- the fixed purge air orifice may be configured to provide a flow of purge air to the wheel space cavity.
- at least one adjustable cooling air orifice may be associated with the stator assembly.
- the at least one adjustable cooling air orifice may be configured to provide a flow of cooling air to the wheel space cavity.
- the turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly.
- At least one purge air circuit may be associated with the stator assembly.
- the purge air circuit may be configured to provide a flow of purge air to the wheel space cavity.
- at least one cooling air circuit may be associated with the stator assembly.
- the cooling air circuit may be configured to provide a flow of cooling air to the wheel space cavity.
- a method for providing a flow of purge air and a flow of cooling air to a cavity in a gas turbine assembly may include providing the flow purge air to the cavity by way of at least one fixed purge air orifice. Moreover, the method may include varying the flow of cooling air to the cavity by way of at least one adjustable cooling air orifice.
- the cavity may include a wheel space cavity and/or a stator cavity.
- a system for providing an adjustable flow of cooling air from a stator cavity to a wheel space cavity of a turbine assembly may include at least one cooling air passage configured to provide the adjustable flow of cooling air to the wheel space cavity from the stator cavity.
- the system may also include a flow control device associated with the at least one cooling air passage.
- the flow control device may include a valve configured to control the adjustable flow of cooling air within the at least one cooling air passage.
- the flow control device may include a temperature dependent actuator positioned at least partially within the wheel space cavity and in mechanical communication with the valve. The temperature dependent actuator may be configured to open and close the valve.
- FIG. 1 is an example schematic view of a gas turbine engine, according to an embodiment of the disclosure.
- FIG. 2 is an example schematic cross-sectional view of a system for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity, according to an embodiment of the disclosure.
- FIG. 3 is an example schematic cross-sectional view of a system for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity, according to an embodiment of the disclosure.
- FIG. 4 is an example schematic cross-sectional view of a system for providing an adjustable flow of cooling air to a wheel space cavity, according to an embodiment of the disclosure.
- FIG. 5 is an example schematic cross-sectional view of a system for providing an adjustable flow of cooling air to a wheel space cavity, according to an embodiment of the disclosure.
- Illustrative embodiments are directed to, among other things, systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity and/or a stator cavity. That is, the systems and methods described herein provide a means to modulate cooling airflow extracted from the compressor and provided to the wheel space cavity and/or the stator cavity. The cooling airflow may be modulated by way of an adjustable cooling air orifice and/or an adjustable cooling air circuit.
- a turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly.
- At least one fixed purge air orifice and at least one adjustable cooling air orifice may be associated with the stator assembly.
- the fixed purge air orifice may be configured to provide a flow of purge air to the wheel space cavity
- the adjustable cooling air orifice may be configured to provide an adjustable flow of cooling air to the wheel space cavity. In this manner, the flow of purge air may purge the wheel space cavity, and the adjustable flow of cooling air may cool the rotor assembly.
- a flow control device may be associated with the adjustable cooling air orifice.
- the flow control device may be configured to vary the flow of cooling air to the wheel space cavity by varying the size of the adjustable cooling air orifice.
- the flow control device may include a value associated with the adjustable cooling air orifice or a cooling air circuit in communication with the wheel space cavity.
- the stator assembly may include a stator cavity defined by a stator wall.
- the fixed purge air orifice and the adjustable cooling air orifice may be positioned in the stator wall.
- the stator cavity may be in communication with a flow of compressor extraction air.
- the flow of compressor extraction air may at least partially form a portion of the flow of purge air and the flow of cooling air. That is, the flow of compressor extraction air may enter the stator cavity, wherein a portion of the flow of compressor extraction may pass through the fixed purge air orifice in the stator wall and into the wheel space cavity, and a portion of the flow of compressor extraction may pass through the adjustable cooling air orifice in the stator wall and into the wheel space cavity.
- the flow of purge air may purge the wheel space cavity, and the flow of cooling air may cool the rotor assembly.
- the flow control device may be positioned within the stator cavity. In other instances, the flow control device may be positioned eternal to the gas turbine engine.
- a temperature sensor and/or actuator may be in communication with the flow device or valve and may be associated with the wheel space cavity and/or stator assembly.
- the temperature sensor and/or actuator may be in communication with the flow device or valve and may be mounted to the stator wall and at least partially protrude into the wheel space cavity.
- the temperature sensor and/or actuator may be configured to manipulate the flow device or valve.
- an inter-stage seal may be positioned between the rotor assembly and the stator assembly.
- the turbine assembly may include at least one purge air circuit and at least one cooling air circuit associated with the stator assembly.
- a flow control device may be associated with the cooling air circuit. That is, the flow control device may be configured to vary the flow of cooling air to the wheel space cavity.
- the flow control device may include a valve in communication with the cooling air circuit.
- the cooling air circuit may include a flow circuit that directs a flow of compressor extraction air through a tube or pipe which connects to the wheel space cavity.
- the valve may modulate the cooling flow to the wheel space cavity by responding to the wheel space and/or rotor assembly temperature as measured by one or more monitoring instruments, such as the temperature sensor.
- the systems and methods described herein may be configured to provide the cooling and purge flow to a stator cavity. That is, in some instances, a fixed amount of purge air flow may be provided from one stator cavity to another, and an additional amount of modulated cooling flow may also be provided between stator cavities.
- FIG. 1 depicts an example schematic view of a gas turbine engine 100 as may be used herein.
- the gas turbine engine 100 may include a gas turbine having a compressor 102 .
- the compressor 102 may compress an incoming flow of air 104 .
- the compressor 102 may deliver the compressed flow of air 104 to a combustor 106 .
- the combustor 106 may mix the compressed flow of air 104 with a pressurized flow of fuel 108 and ignite the mixture to create a flow of combustion gases 110 .
- the gas turbine engine may include any number of combustors 106 .
- the flow of combustion gases 110 may be delivered to a turbine 112 .
- the flow of combustion gases 110 may drive the turbine 112 so as to produce mechanical work.
- the mechanical work produced in the turbine 112 may drive the compressor 102 via a shaft 114 and an external load 116 , such as an electrical generator or the like.
- the gas turbine engine may use natural gas, various types of syngas, and/or other types of fuels.
- the gas turbine engine may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y., including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like.
- the gas turbine engine may have different configurations and may use other types of components.
- the gas turbine engine may be an aeroderivative gas turbine, an industrial gas turbine, or a reciprocating engine. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
- the turbine 112 of FIG. 1 may include a rotor assembly 118 and a stator assembly 120 .
- the stator assembly 120 may be positioned adjacent to the rotor assembly 118 .
- a wheel space cavity 122 may be formed between the rotor assembly 118 and the stator assembly 120 .
- an inter-stage seal 121 may be positioned between the rotor assembly 118 and the stator assembly 120 .
- the stator assembly 120 may include a stator wall 124 . That stator wall 124 may define a stator cavity 126 therein.
- the stator cavity 126 may be in communication with a flow of compressor extraction air 128 . That is, the flow of compressor extraction air 128 may at least partially fill the stator cavity 126 .
- a fixed purge air orifice 130 and an adjustable cooling air orifice 132 may be positioned in the stator wall 124 .
- the fixed purge air orifice 130 may be configured to provide a flow of purge air 134 to the wheel space cavity 122
- the adjustable cooling air orifice 132 may be configured to provide an adjustable flow of cooling air 136 to the wheel space cavity 122 .
- the flow of compressor extraction air 128 may enter the stator cavity 126 , wherein a first portion 134 of the flow of compressor extraction 128 may pass through the fixed purge air orifice 130 and a second portion 136 may pass through the adjustable cooling air orifice 132 .
- the flow of purge air 134 may purge the wheel space cavity 122
- the adjustable flow of cooling air 136 may cool the rotor assembly 118 .
- a flow control device 138 may be positioned within the stator cavity 126 .
- the flow control device 138 may also be associated with the adjustable cooling air orifice 132 .
- the flow control device 138 may be configured to vary the flow of cooling air 136 to the wheel space cavity 122 .
- the flow control device 138 may vary the flow of cooling air 136 to the wheel space cavity 122 by varying the size of the adjustable cooling air orifice 132 .
- the flow control device 138 may include a valve-type mechanism or actuator associated with the adjustable cooling air orifice 132 for varying the flow of cooling air 136 to the wheel space cavity 122 .
- a temperature sensor 140 may be associated with the wheel space cavity 122 and/or the stator assembly 120 .
- the temperature sensor 140 may be part of the flow control device 138 or a separate component.
- the temperature sensor 140 and/or actuator may be in communication with the flow control device 138 and may be mounted to the stator wall 124 and at least partially protrude into the wheel space cavity 122 .
- the flow control device 138 may increase or decrease the flow of cooling air 136 entering the wheel space cavity 122 via the adjustable cooling air orifice 132 by way of a temperature dependent actuator or the like.
- the fixed purge air orifice 130 may provide a constant metered flow of purge air 134 to the wheel space cavity 122 .
- FIG. 3 schematically depicts a system 300 for providing a flow of purge air 322 and an adjustable flow of cooling air 324 to a wheel space cavity 306 .
- the system 300 may include a stator assembly 302 positioned adjacent to a rotor assembly 304 .
- the wheel space cavity 306 may be formed between the rotor assembly 304 and the stator assembly 302 .
- an inter-stage seal 307 may be positioned between the rotor assembly 304 and the stator assembly 302 .
- the stator assembly 302 may include at least one purge air circuit 308 and at least one cooling air circuit 310 . Both the purge air circuit 308 and the cooling air circuit 310 may be in communication with the wheel space cavity 306 and a flow of compressor extrusion air 312 .
- a flow control device 314 may be associated with the cooling air circuit 310 . That is, the flow control device 314 may be configured to vary the flow of cooling air to the wheel space cavity 306 .
- the flow control device 314 may include a valve 316 in communication with the cooling air circuit 310 .
- the cooling air circuit 310 may include a flow circuit that directs a flow of compressor extraction air 312 through a tube or pipe to the wheel space cavity 306 .
- the valve 316 may modulate the cooling flow to the wheel space cavity 306 by responding to the wheel space, stator assembly, and/or rotor assembly temperature as measured by one or more monitoring instruments, such as a temperature sensor 320 in communication with the valve 316 .
- a temperature sensor 320 in communication with the valve 316 .
- the temperature sensor 320 and/or an actuator may be in communication with the valve 316 and may be mounted to the stator wall and at least partially protrude into the wheel space cavity 306 .
- the valve 316 may be disposed external to the gas turbine engine.
- the purging orifices e.g., holes
- the rotor cooling airflow provided by the adjustable cooling air orifice and/or cooling air circuit may be modulated and can therefore be optimized to ambient conditions. For example, during cold ambient conditions, less cooling airflow is required to maintain the wheel space cavity temperature; in this case, the flow device may restrict or stop the cooling airflow. During hot ambient conditions, more cooling airflow may be required to maintain the wheel space cavity temperature under the design limit; under these conditions, the flow device may allow more cooling airflow.
- the flow device used to control rotor cooling air may respond directly to the wheel space cavity temperature and adjust the flow of cooling air as required to maintain rotor temperature within design limits. Having a variable flow area, and therefore the ability to vary the effective flow area of the cooling circuit, provides the additional benefit of optimizing and improving back flow margin.
- variable holes and/or circuits Any number of fixed and/or variable holes and/or circuits may be used herein.
- the fixed and/or variable holes and/or circuits may be any size, shape, and/or configuration.
- the variable flow holes and/or circuits do not necessarily have to operate in unison. That is, some may open and some may close.
- the variable flow holes and/or circuits may be adjusted in response to any parameter, such as, but not limited to, temperature, power output, ambient conditions, cost, etc.
- FIGS. 4 and 5 schematically depict an example cross-sectional view of a system 400 for providing an adjustable flow of cooling air to a wheel space cavity 406 .
- the system 400 may include a stator assembly 402 positioned adjacent to a rotor assembly 404 .
- the stator assembly 402 may include a stator wall 405 that defines a stator cavity 407 .
- the wheel space cavity 406 may be formed between the rotor assembly 404 and the stator assembly 402 .
- an inter-stage seal 408 may be positioned between the rotor assembly 404 and the stator assembly 402 .
- the system 400 may be configured to sense, control, and/or modulate the temperature within wheel space cavity 406 by increasing or decreasing an adjustable flow of cooling air 412 to the wheel space cavity 406 .
- the system 400 may include at least one cooling air passage 410 configured to provide the adjustable flow of cooling air 412 to the wheel space cavity 406 from the stator cavity 407 .
- the cooling air passage 410 may include any opening or passage between the stator cavity 407 and the wheel space cavity 406 .
- the adjustable flow of cooling air 412 provided to the wheel space cavity 406 by the cooling air passage 410 may be controlled by a flow control device 414 .
- the flow control device 414 may be associated with the cooling air passage 410 , but not necessarily positioned within the cooling air passage 410 , so as to modulate the adjustable flow of cooling air 412 provided to the wheel space cavity 406 by the cooling air passage 410 .
- portions of the flow control device 414 may be mounted to the stator wall 405 .
- the flow control device 414 may include a valve 418 that is configured to open and close, thereby increasing or decreasing the adjustable flow of cooling air 412 provided to the wheel space cavity 406 by the cooling air passage 410 .
- the valve 418 is in the closed position, thereby preventing and/or limiting the adjustable flow of cooling air 412 from entering the wheel space cavity 406 .
- the valve 418 is in the open position, thereby enabling the adjustable flow of cooling air 412 to enter the wheel space cavity 406 .
- a temperature dependent actuator 420 may be in mechanical communication with the valve 418 .
- the temperature dependent actuator 420 may be configured to open and close the valve 418 .
- the temperature dependent actuator 420 may be positioned at least partially within the wheel space cavity 406 so as to be at least partially exposed to the wheel space cavity 406 . In this manner, the temperature dependent actuator 420 may sense and/or react to the temperature within the wheel space cavity 406 . In response, the temperature dependent actuator 420 may open or close the valve 418 to regulate the temperature within the wheel space cavity 406 .
- the temperature dependent actuator 420 may include an actuator housing 422 .
- the actuator housing 422 may be positioned at least partially within the wheel space cavity 406 and/or at least partially within the stator cavity 407 . That is, the actuator housing 422 may be at least partially exposed to the wheel space cavity 406 .
- a temperature dependent element 424 may be positioned within the actuator housing 422 . The temperature dependent element 424 may be configured to expand or contract in response to a temperature of the wheel space cavity 406 .
- the temperature dependent element 424 may push a rod 426 (or other mechanical linkage) attached to the valve 418 , thereby opening the valve 418 and allowing the adjustable flow of cooling air 412 to enter the wheel space cavity 406 by way of the cooling air passage 410 .
- the temperature dependent element 424 contracts, it may pull the rod 426 (or other mechanical linkage) attached to the valve 418 , thereby closing the valve 418 and preventing or limiting the adjustable flow of cooling air 412 from enter the wheel space cavity 406 by way of the cooling air passage 410 .
- the valve 418 may include a valve body 428 and a valve disc 430 .
- the valve body 428 may include an opening 432 to the stator cavity 407
- the valve disc 430 may be configured to open and close the opening 432 . That is, the valve disc 430 may be configured to open or close in response to the temperature dependent actuator 420 expanding or contracting. In this manner, the position of the valve disc 430 about the opening 432 may determine the adjustable flow of cooling air 412 that is provided to the wheel space cavity 406 by the cooling air passage 410 .
- the cooling air passage 410 may be positioned upstream of the temperature dependent actuator 420 so as to deliver the adjustable flow of cooling air 412 upstream of the temperature dependent actuator 420 . That is, the fluid flow 436 within the wheel space 406 may be radially outward. In certain embodiments, the flow control device 420 may not be directly mounted to the cooling air passage 410 .
Abstract
Embodiments of the disclosure include systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity or a stator cavity. According to one embodiment, there is disclosed a turbine assembly. The turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly. At least one fixed purge air orifice may be associated with the stator assembly. The fixed purge air orifice may be configured to provide a flow of purge air to the wheel space cavity. Moreover, at least one adjustable cooling air orifice may be associated with the stator assembly. The at least one adjustable cooling air orifice may be configured to provide a flow of cooling air to the wheel space cavity.
Description
- Embodiments of the disclosure relate generally to gas turbine engines and more particularly to systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity and/or a stator cavity.
- Gas turbine engines are widely used in industrial and commercial operations. A typical gas turbine engine includes a compressor at the front, one or more combustors around the middle, and a turbine at the rear. The compressor imparts kinetic energy to the working fluid (e.g., air) to produce a compressed working fluid at a highly energized state. The compressed working fluid exits the compressor and flows to the combustors where it mixes with fuel and ignites to generate combustion gases having a high temperature and pressure. The combustion gases flow to the turbine where they expand to produce work. Consequently, the turbine is exposed to very high temperatures due to the combustion gases. As a result, the various turbine components (such as the shroud assemblies, rotor assemblies, wheel space cavities, and the like) typically need to be cooled and/or supplied purge air. Accordingly, there is a need to provide improved turbine cooling systems and methods.
- Some or all of the above needs and/or problems may be addressed by certain embodiments of the disclosure. According to one embodiment, there is disclosed a turbine assembly. The turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly. At least one fixed purge air orifice may be associated with the stator assembly. The fixed purge air orifice may be configured to provide a flow of purge air to the wheel space cavity. Moreover, at least one adjustable cooling air orifice may be associated with the stator assembly. The at least one adjustable cooling air orifice may be configured to provide a flow of cooling air to the wheel space cavity.
- According to another embodiment, there is disclosed a turbine assembly. The turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly. At least one purge air circuit may be associated with the stator assembly. The purge air circuit may be configured to provide a flow of purge air to the wheel space cavity. Moreover, at least one cooling air circuit may be associated with the stator assembly. The cooling air circuit may be configured to provide a flow of cooling air to the wheel space cavity.
- According to another embodiment, there is disclosed a method for providing a flow of purge air and a flow of cooling air to a cavity in a gas turbine assembly. The method may include providing the flow purge air to the cavity by way of at least one fixed purge air orifice. Moreover, the method may include varying the flow of cooling air to the cavity by way of at least one adjustable cooling air orifice. In some instances, the cavity may include a wheel space cavity and/or a stator cavity.
- According to another embodiment, there is disclosed a system for providing an adjustable flow of cooling air from a stator cavity to a wheel space cavity of a turbine assembly. The system may include at least one cooling air passage configured to provide the adjustable flow of cooling air to the wheel space cavity from the stator cavity. The system may also include a flow control device associated with the at least one cooling air passage. The flow control device may include a valve configured to control the adjustable flow of cooling air within the at least one cooling air passage. Moreover, the flow control device may include a temperature dependent actuator positioned at least partially within the wheel space cavity and in mechanical communication with the valve. The temperature dependent actuator may be configured to open and close the valve.
- Other embodiments, aspects, and features of the invention will become apparent to those skilled in the art from the following detailed description, the accompanying drawings, and the appended claims.
- Reference will now be made to the accompanying drawings, which are not necessarily drawn to scale.
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FIG. 1 is an example schematic view of a gas turbine engine, according to an embodiment of the disclosure. -
FIG. 2 is an example schematic cross-sectional view of a system for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity, according to an embodiment of the disclosure. -
FIG. 3 is an example schematic cross-sectional view of a system for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity, according to an embodiment of the disclosure. -
FIG. 4 is an example schematic cross-sectional view of a system for providing an adjustable flow of cooling air to a wheel space cavity, according to an embodiment of the disclosure. -
FIG. 5 is an example schematic cross-sectional view of a system for providing an adjustable flow of cooling air to a wheel space cavity, according to an embodiment of the disclosure. - Illustrative embodiments will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all embodiments are shown. The disclosure may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Like numbers refer to like elements throughout.
- Illustrative embodiments are directed to, among other things, systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity and/or a stator cavity. That is, the systems and methods described herein provide a means to modulate cooling airflow extracted from the compressor and provided to the wheel space cavity and/or the stator cavity. The cooling airflow may be modulated by way of an adjustable cooling air orifice and/or an adjustable cooling air circuit.
- In certain embodiments, a turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly. At least one fixed purge air orifice and at least one adjustable cooling air orifice may be associated with the stator assembly. The fixed purge air orifice may be configured to provide a flow of purge air to the wheel space cavity, and the adjustable cooling air orifice may be configured to provide an adjustable flow of cooling air to the wheel space cavity. In this manner, the flow of purge air may purge the wheel space cavity, and the adjustable flow of cooling air may cool the rotor assembly.
- In some instances, a flow control device may be associated with the adjustable cooling air orifice. For example, the flow control device may be configured to vary the flow of cooling air to the wheel space cavity by varying the size of the adjustable cooling air orifice. In other instances, the flow control device may include a value associated with the adjustable cooling air orifice or a cooling air circuit in communication with the wheel space cavity.
- In certain embodiments, the stator assembly may include a stator cavity defined by a stator wall. In some instances, the fixed purge air orifice and the adjustable cooling air orifice may be positioned in the stator wall. In other instances, the stator cavity may be in communication with a flow of compressor extraction air. In this manner, the flow of compressor extraction air may at least partially form a portion of the flow of purge air and the flow of cooling air. That is, the flow of compressor extraction air may enter the stator cavity, wherein a portion of the flow of compressor extraction may pass through the fixed purge air orifice in the stator wall and into the wheel space cavity, and a portion of the flow of compressor extraction may pass through the adjustable cooling air orifice in the stator wall and into the wheel space cavity. The flow of purge air may purge the wheel space cavity, and the flow of cooling air may cool the rotor assembly.
- In some instances, the flow control device may be positioned within the stator cavity. In other instances, the flow control device may be positioned eternal to the gas turbine engine. In certain embodiments, a temperature sensor and/or actuator may be in communication with the flow device or valve and may be associated with the wheel space cavity and/or stator assembly. For example, the temperature sensor and/or actuator may be in communication with the flow device or valve and may be mounted to the stator wall and at least partially protrude into the wheel space cavity. The temperature sensor and/or actuator may be configured to manipulate the flow device or valve. In other embodiments, an inter-stage seal may be positioned between the rotor assembly and the stator assembly.
- In certain embodiments, the turbine assembly may include at least one purge air circuit and at least one cooling air circuit associated with the stator assembly. In some instances, a flow control device may be associated with the cooling air circuit. That is, the flow control device may be configured to vary the flow of cooling air to the wheel space cavity. For example, the flow control device may include a valve in communication with the cooling air circuit. In this manner, the cooling air circuit may include a flow circuit that directs a flow of compressor extraction air through a tube or pipe which connects to the wheel space cavity. The valve may modulate the cooling flow to the wheel space cavity by responding to the wheel space and/or rotor assembly temperature as measured by one or more monitoring instruments, such as the temperature sensor.
- In certain embodiments, the systems and methods described herein may be configured to provide the cooling and purge flow to a stator cavity. That is, in some instances, a fixed amount of purge air flow may be provided from one stator cavity to another, and an additional amount of modulated cooling flow may also be provided between stator cavities.
- Turning now to the drawings,
FIG. 1 depicts an example schematic view of agas turbine engine 100 as may be used herein. Thegas turbine engine 100 may include a gas turbine having acompressor 102. Thecompressor 102 may compress an incoming flow ofair 104. Thecompressor 102 may deliver the compressed flow ofair 104 to acombustor 106. Thecombustor 106 may mix the compressed flow ofair 104 with a pressurized flow offuel 108 and ignite the mixture to create a flow ofcombustion gases 110. Although only asingle combustor 106 is shown, the gas turbine engine may include any number ofcombustors 106. The flow ofcombustion gases 110 may be delivered to aturbine 112. The flow ofcombustion gases 110 may drive theturbine 112 so as to produce mechanical work. The mechanical work produced in theturbine 112 may drive thecompressor 102 via ashaft 114 and anexternal load 116, such as an electrical generator or the like. - The gas turbine engine may use natural gas, various types of syngas, and/or other types of fuels. The gas turbine engine may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y., including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like. The gas turbine engine may have different configurations and may use other types of components. The gas turbine engine may be an aeroderivative gas turbine, an industrial gas turbine, or a reciprocating engine. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
- In certain embodiments, as schematically depicted in
FIG. 2 , theturbine 112 ofFIG. 1 may include arotor assembly 118 and astator assembly 120. Thestator assembly 120 may be positioned adjacent to therotor assembly 118. Awheel space cavity 122 may be formed between therotor assembly 118 and thestator assembly 120. In some instances, aninter-stage seal 121 may be positioned between therotor assembly 118 and thestator assembly 120. - The
stator assembly 120 may include astator wall 124. Thatstator wall 124 may define astator cavity 126 therein. Thestator cavity 126 may be in communication with a flow ofcompressor extraction air 128. That is, the flow ofcompressor extraction air 128 may at least partially fill thestator cavity 126. - In some instances, a fixed
purge air orifice 130 and an adjustablecooling air orifice 132 may be positioned in thestator wall 124. The fixedpurge air orifice 130 may be configured to provide a flow ofpurge air 134 to thewheel space cavity 122, and the adjustablecooling air orifice 132 may be configured to provide an adjustable flow of coolingair 136 to thewheel space cavity 122. For example, the flow ofcompressor extraction air 128 may enter thestator cavity 126, wherein afirst portion 134 of the flow ofcompressor extraction 128 may pass through the fixedpurge air orifice 130 and asecond portion 136 may pass through the adjustablecooling air orifice 132. The flow ofpurge air 134 may purge thewheel space cavity 122, and the adjustable flow of coolingair 136 may cool therotor assembly 118. - In some instances, a
flow control device 138 may be positioned within thestator cavity 126. Theflow control device 138 may also be associated with the adjustablecooling air orifice 132. For example, theflow control device 138 may be configured to vary the flow of coolingair 136 to thewheel space cavity 122. In one example, theflow control device 138 may vary the flow of coolingair 136 to thewheel space cavity 122 by varying the size of the adjustablecooling air orifice 132. In other instances, theflow control device 138 may include a valve-type mechanism or actuator associated with the adjustablecooling air orifice 132 for varying the flow of coolingair 136 to thewheel space cavity 122. For example, in certain embodiments, atemperature sensor 140 may be associated with thewheel space cavity 122 and/or thestator assembly 120. Thetemperature sensor 140 may be part of theflow control device 138 or a separate component. In some instances, thetemperature sensor 140 and/or actuator may be in communication with theflow control device 138 and may be mounted to thestator wall 124 and at least partially protrude into thewheel space cavity 122. Depending on the temperature of thewheel space cavity 122, thestator assembly 120, and/or the rotor assembly 118 (as determined by the temperature sensor 140) theflow control device 138 may increase or decrease the flow of coolingair 136 entering thewheel space cavity 122 via the adjustablecooling air orifice 132 by way of a temperature dependent actuator or the like. However, in certain embodiments, regardless of the temperature of thewheel space cavity 122, the fixedpurge air orifice 130 may provide a constant metered flow ofpurge air 134 to thewheel space cavity 122. -
FIG. 3 schematically depicts asystem 300 for providing a flow ofpurge air 322 and an adjustable flow of coolingair 324 to awheel space cavity 306. For example, thesystem 300 may include astator assembly 302 positioned adjacent to arotor assembly 304. Thewheel space cavity 306 may be formed between therotor assembly 304 and thestator assembly 302. In some instances, aninter-stage seal 307 may be positioned between therotor assembly 304 and thestator assembly 302. - The
stator assembly 302 may include at least onepurge air circuit 308 and at least one cooling air circuit 310. Both thepurge air circuit 308 and the cooling air circuit 310 may be in communication with thewheel space cavity 306 and a flow ofcompressor extrusion air 312. In some instances, aflow control device 314 may be associated with the cooling air circuit 310. That is, theflow control device 314 may be configured to vary the flow of cooling air to thewheel space cavity 306. For example, theflow control device 314 may include avalve 316 in communication with the cooling air circuit 310. In this manner, the cooling air circuit 310 may include a flow circuit that directs a flow ofcompressor extraction air 312 through a tube or pipe to thewheel space cavity 306. Thevalve 316 may modulate the cooling flow to thewheel space cavity 306 by responding to the wheel space, stator assembly, and/or rotor assembly temperature as measured by one or more monitoring instruments, such as atemperature sensor 320 in communication with thevalve 316. In some instances, thetemperature sensor 320 and/or an actuator may be in communication with thevalve 316 and may be mounted to the stator wall and at least partially protrude into thewheel space cavity 306. In some instances, thevalve 316 may be disposed external to the gas turbine engine. - As described above, the purging orifices (e.g., holes) and/or circuits are fixed and sized to provide the required purge flow to meet purge requirements in the wheel space cavity. The rotor cooling airflow provided by the adjustable cooling air orifice and/or cooling air circuit may be modulated and can therefore be optimized to ambient conditions. For example, during cold ambient conditions, less cooling airflow is required to maintain the wheel space cavity temperature; in this case, the flow device may restrict or stop the cooling airflow. During hot ambient conditions, more cooling airflow may be required to maintain the wheel space cavity temperature under the design limit; under these conditions, the flow device may allow more cooling airflow. Accordingly, the flow device used to control rotor cooling air may respond directly to the wheel space cavity temperature and adjust the flow of cooling air as required to maintain rotor temperature within design limits. Having a variable flow area, and therefore the ability to vary the effective flow area of the cooling circuit, provides the additional benefit of optimizing and improving back flow margin.
- Any number of fixed and/or variable holes and/or circuits may be used herein. The fixed and/or variable holes and/or circuits may be any size, shape, and/or configuration. Moreover, the variable flow holes and/or circuits do not necessarily have to operate in unison. That is, some may open and some may close. In addition, the variable flow holes and/or circuits may be adjusted in response to any parameter, such as, but not limited to, temperature, power output, ambient conditions, cost, etc.
-
FIGS. 4 and 5 schematically depict an example cross-sectional view of asystem 400 for providing an adjustable flow of cooling air to awheel space cavity 406. For example, thesystem 400 may include astator assembly 402 positioned adjacent to arotor assembly 404. Thestator assembly 402 may include astator wall 405 that defines astator cavity 407. Thewheel space cavity 406 may be formed between therotor assembly 404 and thestator assembly 402. In some instances, aninter-stage seal 408 may be positioned between therotor assembly 404 and thestator assembly 402. - In certain embodiments, the
system 400 may be configured to sense, control, and/or modulate the temperature withinwheel space cavity 406 by increasing or decreasing an adjustable flow of coolingair 412 to thewheel space cavity 406. For example, thesystem 400 may include at least onecooling air passage 410 configured to provide the adjustable flow of coolingair 412 to thewheel space cavity 406 from thestator cavity 407. The coolingair passage 410 may include any opening or passage between thestator cavity 407 and thewheel space cavity 406. The adjustable flow of coolingair 412 provided to thewheel space cavity 406 by the coolingair passage 410 may be controlled by aflow control device 414. In this manner, theflow control device 414 may be associated with the coolingair passage 410, but not necessarily positioned within the coolingair passage 410, so as to modulate the adjustable flow of coolingair 412 provided to thewheel space cavity 406 by the coolingair passage 410. In some instances, portions of theflow control device 414 may be mounted to thestator wall 405. - In order to control the adjustable flow of cooling
air 412 provided to thewheel space cavity 406 by the coolingair passage 410, theflow control device 414 may include avalve 418 that is configured to open and close, thereby increasing or decreasing the adjustable flow of coolingair 412 provided to thewheel space cavity 406 by the coolingair passage 410. For example, as depicted inFIG. 4 , thevalve 418 is in the closed position, thereby preventing and/or limiting the adjustable flow of coolingair 412 from entering thewheel space cavity 406. Conversely, as depicted inFIG. 5 , thevalve 418 is in the open position, thereby enabling the adjustable flow of coolingair 412 to enter thewheel space cavity 406. - In certain embodiments, a temperature
dependent actuator 420 may be in mechanical communication with thevalve 418. The temperaturedependent actuator 420 may be configured to open and close thevalve 418. For example, the temperaturedependent actuator 420 may be positioned at least partially within thewheel space cavity 406 so as to be at least partially exposed to thewheel space cavity 406. In this manner, the temperaturedependent actuator 420 may sense and/or react to the temperature within thewheel space cavity 406. In response, the temperaturedependent actuator 420 may open or close thevalve 418 to regulate the temperature within thewheel space cavity 406. - In certain embodiments, the temperature
dependent actuator 420 may include anactuator housing 422. In some instances, theactuator housing 422 may be positioned at least partially within thewheel space cavity 406 and/or at least partially within thestator cavity 407. That is, theactuator housing 422 may be at least partially exposed to thewheel space cavity 406. In addition, a temperaturedependent element 424 may be positioned within theactuator housing 422. The temperaturedependent element 424 may be configured to expand or contract in response to a temperature of thewheel space cavity 406. For example, as the temperaturedependent element 424 expands, it may push a rod 426 (or other mechanical linkage) attached to thevalve 418, thereby opening thevalve 418 and allowing the adjustable flow of coolingair 412 to enter thewheel space cavity 406 by way of the coolingair passage 410. Conversely, as the temperaturedependent element 424 contracts, it may pull the rod 426 (or other mechanical linkage) attached to thevalve 418, thereby closing thevalve 418 and preventing or limiting the adjustable flow of coolingair 412 from enter thewheel space cavity 406 by way of the coolingair passage 410. - In some instances, the
valve 418 may include avalve body 428 and avalve disc 430. For example, thevalve body 428 may include anopening 432 to thestator cavity 407, and thevalve disc 430 may be configured to open and close theopening 432. That is, thevalve disc 430 may be configured to open or close in response to the temperaturedependent actuator 420 expanding or contracting. In this manner, the position of thevalve disc 430 about theopening 432 may determine the adjustable flow of coolingair 412 that is provided to thewheel space cavity 406 by the coolingair passage 410. - In certain embodiments, the cooling
air passage 410 may be positioned upstream of the temperaturedependent actuator 420 so as to deliver the adjustable flow of coolingair 412 upstream of the temperaturedependent actuator 420. That is, thefluid flow 436 within thewheel space 406 may be radially outward. In certain embodiments, theflow control device 420 may not be directly mounted to the coolingair passage 410. - Although embodiments have been described in language specific to structural features and/or methodological acts, it is to be understood that the disclosure is not necessarily limited to the specific features or acts described. Rather, the specific features and acts are disclosed as illustrative forms of implementing the embodiments.
Claims (25)
1. A turbine assembly, comprising:
a rotor assembly;
a stator assembly positioned adjacent to the rotor assembly;
a wheel space cavity formed between the rotor assembly and the stator assembly;
at least one fixed purge air orifice associated with the stator assembly; and
at least one adjustable cooling air orifice associated with the stator assembly, wherein the at least one fixed purge air orifice is configured to provide a flow of purge air to the wheel space cavity, and wherein the at least one adjustable cooling air orifice is configured to provide an adjustable flow of cooling air to the wheel space cavity.
2. The assembly of claim 1 , further comprising a flow control device associated with the at least one adjustable cooling air orifice, wherein the flow control device is configured to vary the flow of cooling air to the wheel space cavity by varying the size of the at least one adjustable cooling air orifice.
3. The assembly of claim 2 , wherein the stator assembly comprises:
a stator wall; and
a stator cavity defined by the stator wall, wherein the stator cavity is in communication with a flow of compressor extraction air.
4. The assembly of claim 3 , wherein the at least one fixed purge air orifice is positioned in the stator wall.
5. The assembly of claim 3 , wherein the at least one adjustable cooling air orifice is positioned in the stator wall.
6. The assembly of claim 3 , wherein the flow control device is positioned within the stator cavity.
7. The assembly of claim 3 , wherein the flow of compressor extraction air forms at least a portion of the flow of purge air and the flow of cooling air.
8. The assembly of claim 1 , further comprising a temperature sensor associated with the wheel space cavity and in communication with the at least one adjustable cooling air orifice.
9. The assembly of claim 1 , further comprising an inter-stage seal positioned between the rotor assembly and the stator assembly.
10. A turbine assembly, comprising:
a rotor assembly;
a stator assembly positioned adjacent to the rotor assembly;
a wheel space cavity formed between the rotor assembly and the stator assembly;
at least one purge air circuit associated with the stator assembly; and
at least one cooling air circuit associated with the stator assembly, wherein the at least one purge air circuit is configured to provide a flow of purge air to the wheel space cavity, and wherein the at least one cooling air circuit is configured to provide an adjustable flow of cooling air to the wheel space cavity.
11. The assembly of claim 10 , further comprising a flow control device associated with the at least one cooling air circuit, wherein the flow control device is configured to vary the flow of cooling air to the wheel space cavity.
12. The assembly of claim 11 , wherein the flow control device comprises a valve in communication with the at least one cooling air circuit.
13. The assembly of claim 10 , wherein the stator assembly comprises:
a stator wall; and
a stator cavity defined by the stator wall, wherein the stator cavity is in communication with a flow of compressor extraction air.
14. The assembly of claim 13 , wherein the at least one purge air circuit comprises an orifice positioned in the stator wall.
15. The assembly of claim 14 , wherein the orifice is fixed
16. The assembly of claim 13 , wherein the at least one cooling air circuit comprises an adjustable orifice positioned in the stator wall.
17. The assembly of claim 10 , further comprising a temperature sensor associated with the wheel space cavity and in communication with the at least one cooling air circuit.
18. The assembly of claim 10 , further comprising an inter-stage seal positioned between the rotor assembly and the stator assembly.
19. A method for providing a flow of purge air and a flow of cooling air to a cavity in a gas turbine assembly, comprising:
providing the flow purge air to the cavity by way of at least one fixed purge air orifice; and
varying the flow of cooling air to the cavity by way of at least one adjustable cooling air orifice, wherein the cavity comprises a wheel space cavity or a stator cavity.
20. The method of claim 19 , further comprising varying the size of the at least one adjustable cooling air orifice with a flow control device.
21. A system for providing an adjustable flow of cooling air from a stator cavity to a wheel space cavity of a turbine assembly, the system comprising:
at least one cooling air passage configured to provide the adjustable flow of cooling air to the wheel space cavity from the stator cavity; and
a flow control device associated with the at least one cooling air passage, the flow control device comprising:
a valve configured to control the adjustable flow of cooling air within the at least one cooling air passage; and
a temperature dependent actuator positioned at least partially within the wheel space cavity and in mechanical communication with the valve, wherein the temperature dependent actuator is configured to open and close the valve.
22. The system of claim 21 , wherein the temperature dependent actuator comprises:
an actuator housing positioned at least partially within the wheel space cavity; and
a temperature dependent element positioned within the actuator housing, wherein the temperature dependent element is configured to expand or contract in response to a temperature of the wheel space cavity to open and close the valve.
23. The system of claim 21 , wherein the valve comprises:
a valve body in fluid communication with the at least one cooling air passage; and
a valve disc configured to open and close in response to the temperature dependent actuator to modulate the adjustable flow of cooling air provided to the wheel space cavity by the at least one cooling air passage.
24. The system of claim 21 , wherein the at least one cooling air passage is positioned upstream of the temperature dependent actuator so as to deliver the adjustable flow of cooling air upstream of the temperature dependent actuator.
25. The system of claim 21 , further comprising at least one fixed purge air orifice in communication with the wheel space cavity, wherein the at least one fixed purge air orifice is configured to provide a constant flow of purge air to the wheel space cavity.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/790,863 US20140255145A1 (en) | 2013-03-08 | 2013-03-08 | Systems and Methods for Providing a Flow of Purge Air and an Adjustable Flow of Cooling Air in a Gas Turbine Application |
CH00330/14A CH707753A2 (en) | 2013-03-08 | 2014-03-05 | Turbine arrangement and method for providing a purge airflow, and an adjustable flow of cooling air to a cavity in a gas turbine. |
JP2014042236A JP2014173596A (en) | 2013-03-08 | 2014-03-05 | Systems and methods for providing flow of purge air and adjustable flow of cooling air in gas turbine application |
DE102014103078.8A DE102014103078A1 (en) | 2013-03-08 | 2014-03-07 | Systems and methods for providing purging airflow and adjustable cooling airflow in a gas turbine application |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/790,863 US20140255145A1 (en) | 2013-03-08 | 2013-03-08 | Systems and Methods for Providing a Flow of Purge Air and an Adjustable Flow of Cooling Air in a Gas Turbine Application |
Publications (1)
Publication Number | Publication Date |
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US20140255145A1 true US20140255145A1 (en) | 2014-09-11 |
Family
ID=51385725
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/790,863 Abandoned US20140255145A1 (en) | 2013-03-08 | 2013-03-08 | Systems and Methods for Providing a Flow of Purge Air and an Adjustable Flow of Cooling Air in a Gas Turbine Application |
Country Status (4)
Country | Link |
---|---|
US (1) | US20140255145A1 (en) |
JP (1) | JP2014173596A (en) |
CH (1) | CH707753A2 (en) |
DE (1) | DE102014103078A1 (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20160326878A1 (en) * | 2014-02-03 | 2016-11-10 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine, gas turbine control device, and gas turbine cooling method |
EP3187694A1 (en) * | 2015-12-30 | 2017-07-05 | General Electric Company | Passive flow modulation device and gas turbine cooling system comprising such a device |
EP3187698A1 (en) * | 2015-12-30 | 2017-07-05 | General Electric Company | Passive flow modulation of cooling flow with telemetry |
US10208764B2 (en) | 2016-02-25 | 2019-02-19 | General Electric Company | Rotor wheel and impeller inserts |
US10337411B2 (en) | 2015-12-30 | 2019-07-02 | General Electric Company | Auto thermal valve (ATV) for dual mode passive cooling flow modulation |
US10337343B2 (en) | 2015-08-13 | 2019-07-02 | General Electric Company | Turbine component surface cooling system with passive flow modulation |
US10337739B2 (en) | 2016-08-16 | 2019-07-02 | General Electric Company | Combustion bypass passive valve system for a gas turbine |
US10335900B2 (en) | 2016-03-03 | 2019-07-02 | General Electric Company | Protective shield for liquid guided laser cutting tools |
US10712007B2 (en) | 2017-01-27 | 2020-07-14 | General Electric Company | Pneumatically-actuated fuel nozzle air flow modulator |
US10738712B2 (en) | 2017-01-27 | 2020-08-11 | General Electric Company | Pneumatically-actuated bypass valve |
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US20110162384A1 (en) * | 2010-01-07 | 2011-07-07 | General Electric Company | Temperature activated valves for gas turbines |
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JP2007146787A (en) * | 2005-11-29 | 2007-06-14 | Mitsubishi Heavy Ind Ltd | Gas turbine |
-
2013
- 2013-03-08 US US13/790,863 patent/US20140255145A1/en not_active Abandoned
-
2014
- 2014-03-05 JP JP2014042236A patent/JP2014173596A/en active Pending
- 2014-03-05 CH CH00330/14A patent/CH707753A2/en not_active Application Discontinuation
- 2014-03-07 DE DE102014103078.8A patent/DE102014103078A1/en not_active Withdrawn
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GB2246836A (en) * | 1981-05-07 | 1992-02-12 | Rolls Royce | Fluid flow valve |
US4815928A (en) * | 1985-05-06 | 1989-03-28 | General Electric Company | Blade cooling |
US20110162384A1 (en) * | 2010-01-07 | 2011-07-07 | General Electric Company | Temperature activated valves for gas turbines |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20160326878A1 (en) * | 2014-02-03 | 2016-11-10 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine, gas turbine control device, and gas turbine cooling method |
US10267153B2 (en) * | 2014-02-03 | 2019-04-23 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine, gas turbine control device, and gas turbine cooling method |
US10337343B2 (en) | 2015-08-13 | 2019-07-02 | General Electric Company | Turbine component surface cooling system with passive flow modulation |
US20170191372A1 (en) * | 2015-12-30 | 2017-07-06 | General Electric Company | Passive flow modulation of cooling flow with telemetry |
CN107023331A (en) * | 2015-12-30 | 2017-08-08 | 通用电气公司 | Into the passive stream regulation of the cooling stream in chamber |
CN107035437A (en) * | 2015-12-30 | 2017-08-11 | 通用电气公司 | Utilize the passive stream regulation of the cooling stream of remote measurement |
EP3187698A1 (en) * | 2015-12-30 | 2017-07-05 | General Electric Company | Passive flow modulation of cooling flow with telemetry |
US10337411B2 (en) | 2015-12-30 | 2019-07-02 | General Electric Company | Auto thermal valve (ATV) for dual mode passive cooling flow modulation |
EP3187694A1 (en) * | 2015-12-30 | 2017-07-05 | General Electric Company | Passive flow modulation device and gas turbine cooling system comprising such a device |
CN107035437B (en) * | 2015-12-30 | 2021-01-26 | 通用电气公司 | Passive flow regulation of cooling flow using telemetry |
US10208764B2 (en) | 2016-02-25 | 2019-02-19 | General Electric Company | Rotor wheel and impeller inserts |
US10335900B2 (en) | 2016-03-03 | 2019-07-02 | General Electric Company | Protective shield for liquid guided laser cutting tools |
US10337739B2 (en) | 2016-08-16 | 2019-07-02 | General Electric Company | Combustion bypass passive valve system for a gas turbine |
US10712007B2 (en) | 2017-01-27 | 2020-07-14 | General Electric Company | Pneumatically-actuated fuel nozzle air flow modulator |
US10738712B2 (en) | 2017-01-27 | 2020-08-11 | General Electric Company | Pneumatically-actuated bypass valve |
Also Published As
Publication number | Publication date |
---|---|
JP2014173596A (en) | 2014-09-22 |
CH707753A2 (en) | 2014-09-15 |
DE102014103078A1 (en) | 2014-09-11 |
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