Method for operating a gas turbine engine including a combustor shell air recirculation system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-009/00
F02C-003/30
출원번호
US-0603804
(2012-09-05)
등록번호
US-8820090
(2014-09-02)
발명자
/ 주소
Lee, Ching-Pang
Landrum, Evan C.
Zhang, Jiping
출원인 / 주소
Siemens Aktiengesellschaft
인용정보
피인용 횟수 :
3인용 특허 :
8
초록▼
During full load operation of gas turbine engine operation, a valve system is maintained in a closed position to substantially prevent air from passing through a piping system of a shell air recirculation system. Upon initiation of a turn down operation, which is implemented to transition the engine
During full load operation of gas turbine engine operation, a valve system is maintained in a closed position to substantially prevent air from passing through a piping system of a shell air recirculation system. Upon initiation of a turn down operation, which is implemented to transition the engine to a turning gear state or a shut down state, the valve system is opened to allow air to pass through the piping system. A blower is operated to extract air through at least one outlet port of the shell air recirculation system from an interior volume of an engine casing portion associated with the combustion section, to convey the extracted air through the piping system, and to inject the air into the interior volume of the engine casing portion through at least one inlet port of the shell air recirculation system to circulate air within the engine casing portion.
대표청구항▼
1. A method for operating a gas turbine engine including a longitudinal axis defining an axial direction of the engine and a casing having an engine casing portion including a casing wall having a top wall section defining a top dead center, left and right side wall sections, and a bottom wall secti
1. A method for operating a gas turbine engine including a longitudinal axis defining an axial direction of the engine and a casing having an engine casing portion including a casing wall having a top wall section defining a top dead center, left and right side wall sections, and a bottom wall section defining a bottom dead center, the method comprising: during a first mode of engine operation: compressing air in a compressor section;mixing at least a portion of the compressed air with a fuel and burning the mixture in a combustion section to create hot combustion gases;expanding the hot combustion gases in a turbine section to extract energy from the combustion gases, wherein at least a portion of the extracted energy is used to rotate a turbine rotor; andmaintaining a valve system in a closed position to substantially prevent air from passing through a piping system of a shell air recirculation system, the shell air recirculation system being associated with the engine casing portion, which is disposed about the combustion section, the shell air recirculation system comprising: at least one outlet port formed in the engine casing portion;at least one inlet port formed in the top wall section of the casing wall;the piping system, which provides fluid communication between the at least one outlet port and the at least one inlet port;a blower for extracting air from an interior volume of the engine casing portion through the at least one outlet port and for conveying the extracted air to the at least one inlet port; andthe valve system, which selectively allows and prevents air from passing through the piping system; andupon initiation of a turn down operation, which is implemented to transition the engine to a second mode of engine operation that is less than full load operation; decreasing the amounts of air and fuel burned in the combustion section so as to decrease the amount of hot combustion gases created in the combustion section;expanding the decreased amount of hot combustion gases in the turbine section to extract energy from the decreased amount of combustion gases, wherein at least a portion of the extracted energy is used to rotate the turbine rotor;opening the valve system to allow air to pass through the piping system of the shell air recirculation system; andoperating the blower to: extract air from the interior volume of the casing portion through the at least one outlet port;convey the extracted air to the at least one inlet port; andinject the air into the interior volume of the engine casing portion through the at least one inlet port to circulate air within the engine casing portion, wherein the at least one inlet port is configured such that the air injected thereby flows from the top wall section of the casing wall down the left and right side wall sections of the casing wall toward the bottom wall section of the casing wall. 2. The method of claim 1, further comprising, upon the engine reaching the second mode of engine operation, maintaining the valve system in an open position to allow air to pass through the piping system of the shell air recirculation system and continuing to operate the blower to: extract air from the interior volume of the casing portion through the at least one outlet port;convey the extracted air to the at least one inlet port; andinject the air into the engine casing portion through the at least one inlet port to circulate air within the engine casing portion. 3. The method of claim 2, wherein the first mode of engine operation is full load operation. 4. The method of claim 3, wherein the second mode of engine operation is a turning gear state, and further comprising, after completion of the turning gear state, entering a shut down state, wherein operation of the blower is disabled. 5. The method of claim 1, wherein the at least one outlet port is formed in the bottom wall section of the casing wall. 6. The method of claim 5, wherein the at least one inlet port comprises two circumferentially spaced apart inlet ports located at generally the same axial location. 7. The method of claim 6, wherein the inlet ports are configured such that the air injected thereby includes a velocity component in the circumferential direction. 8. The method of claim 7, wherein the inlet ports are configured such that they inject air at least partially in directions toward one another and toward the top dead center of the casing wall, which is located circumferentially between the inlet ports. 9. The method of claim 7, wherein the inlet ports are configured such that the air injected thereby includes a velocity component in the axial direction. 10. The method of claim 9, wherein the inlet ports are configured such that the air injected thereby is injected in the axial direction toward the compressor section and away from the turbine section. 11. The method of claim 1, further comprising, during the first mode of engine operation, injecting high pressure steam into the interior volume of the casing portion through at least one of the at least one outlet port and the at least one inlet port. 12. The method of claim 1, further comprising, during the first mode of engine operation, injecting high pressure steam into the interior volume of the casing portion through each of the outlet and inlet ports. 13. A method for operating a gas turbine engine including a longitudinal axis defining an axial direction of the engine, the method comprising: during full load engine operation: compressing air in a compressor section;mixing at least a portion of the compressed air with a fuel and burning the mixture in a combustion section to create hot combustion gases;expanding the hot combustion gases in a turbine section to extract energy from the combustion gases, wherein at least a portion of the extracted energy is used to rotate a turbine rotor,maintaining a valve system in a closed position to substantially prevent air from passing through a piping system of a shell air recirculation system, the shell air recirculation system being associated with a portion of a casing wall of an engine casing disposed about the combustion section and comprising: at least one outlet port formed in the engine casing portion;at least one inlet port formed in the engine casing portion;the piping system, which provides fluid communication between the at least one outlet port and the at least one inlet port;a blower for extracting air from an interior volume of the casing portion through the at least one outlet port and for conveying the extracted air to the at least one inlet port; andthe valve system, which selectively allows and prevents air from passing through the piping system; andinjecting high pressure steam into the interior volume of the casing portion through at least one of the outlet and inlet ports;upon initiation of a turn down operation, which is implemented to transition the engine to a turning gear state; decreasing the amounts of air and fuel burned in the combustion section so as to decrease the amount of hot combustion gases created in the combustion section;expanding the decreased amount of hot combustion gases in the turbine section to extract energy from the decreased amount of combustion gases, wherein at least a portion of the extracted energy is used to rotate the turbine rotor;opening the valve system to allow air to pass through the piping system of the shell air recirculation system; andoperating the blower to: extract air from the interior volume of the casing portion through the at least one outlet port;convey the extracted air to the at least one inlet port; andinject the air into the interior volume of the engine casing portion through the at least one inlet port to circulate air within the engine casing portion; andupon the engine being transitioned to the turning gear state by the turn down operation:ceasing delivery of fuel to the combustion section so as to stop the creation of hot combustion gases in the combustion section;maintaining the valve system in an open position to allow air to pass through the piping system of the shell air recirculation system; andcontinuing to operate the blower to: extract air from the interior volume of the casing portion through the at least one outlet port;convey the extracted air to the at least one inlet port; andinject the air into the interior volume of the engine casing portion through the at least one inlet port to circulate air within the engine casing portion, wherein the at least one inlet port is configured such that the air injected thereby flows from a top wall section of the casing wall down left and right side wall sections of the casing wall toward a bottom wall section of the casing wall. 14. The method of claim 13, further comprising disabling operation of the blower upon the engine entering a shut down state after completion of the turning gear state. 15. The method of claim 13, wherein the at least one inlet port is configured such that the air injected thereby is injected in the axial direction toward the compressor section and away from the turbine section. 16. The method of claim 13, wherein the at least one inlet port comprises two circumferentially spaced apart inlet ports located at generally the same axial location in the top wall section of the casing wall. 17. The method of claim 16, further comprising, during full load engine operation, injecting high pressure steam into the interior volume of the casing portion through each of the inlet ports. 18. The method of claim 13, further comprising, upon the engine being transitioned to the turning gear state by the turn down operation, using an external source of power to effect rotation of the turbine rotor.
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이 특허에 인용된 특허 (8)
Kondo, Mitsuru; Ishizaka, Koichi; Iwasaki, Yoshifumi, Casing and gas turbine.
Iwasaki, Yoichi; Iwasaki, Yoshifumi; Yoshioka, Shinichi, Gas turbine, method of controlling air supply and computer program product for controlling air supply.
Iwasaki, Yoichi; Iwasaki, Yoshifumi; Yoshioka, Shinichi, Gas turbine, method of controlling air supply and computer program product for controlling air supply.
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