[특허]Gas turbine engine compressors having optimized stall enhancement feature configurations and methods for the production thereof

HONEYWELL INTERNATIONAL INC.

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Gas turbine engine compressors having optimized stall enhancement feature configurations and methods for the production thereof

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F04D-027/02 F04D-019/02 F04D-029/32 F01D-025/24 F04D-027/00 F04D-029/52 F04D-029/68
출원번호	US-0612404 (2015-02-03)
등록번호	US-9932985 (2018-04-03)
발명자 / 주소	Reynolds, Bruce David Nolcheff, Nick
출원인 / 주소	HONEYWELL INTERNATIONAL INC.
대리인 / 주소	Lorenz & Kopf, LLP
인용정보	피인용 횟수 : 0 인용 특허 : 4

초록
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Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.

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1. A method for producing a multistage Gas Turbine Engine (GTE) compressor including a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine, the method comprising: selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine;identifying one or more stall limiting rotors at each of the selected engine speeds, the one or more stall limiting rotors identified based at least in part upon numerical instabilities generated by computational fluid dynamic analysis of a virtual model of the multistage GTE compressor;establishing an optimized stall enhancement feature (SEF) configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors; andproducing the multistage GTE compressor in accordance with the optimized SEF configuration;wherein establishing comprises: after identifying one or more stall limiting rotors at each of the selected engine speeds, applying SEFs to the virtual model of the multistage GTE compressor at the selected locations;re-testing the virtual model to determine if a predetermined stall threshold is surpassed at each of the selected engine speeds;if the predetermined stall threshold is surpassed at each of the selected engine speeds, utilizing the locations at which the SEFs have been applied to the virtual model to establish the optimized SEF configuration; andif the predetermined stall threshold is not surpassed at each of the selected engine speeds, repeating the steps of applying and retesting. 2. The method of claim 1 wherein identifying comprises: plotting a speed line for each of the selected engine speeds on a compressor performance map, while increasing the axial pressure ratio applied across the virtual model of the multistage GTE compressor until stall is reached; andafter reaching stall at each of the selected engine speeds, utilizing data gathered from the virtual model to determine which of the rotors contained within the series of axial compressor stages is the stall limiting rotor for each of the selected engine speeds. 3. The method of claim 1 wherein the SEFs comprise casing treatment features, and wherein the casing treatment features are positioned around at least one of the stall limiting rotors in the optimized SEF configuration. 4. The method of claim 3 wherein the casing treatment features comprise grooves formed in an engine casing and circumscribing at least one of the stall limiting rotors in the optimized SEF configuration. 5. The method of claim 1 wherein the SEFs comprise upstream injection features, and wherein the upstream injection features are positioned upstream of at least one of the stall limiting rotors within a flow field thereof. 6. The method of claim 5 wherein the upstream injection features comprise stator hub flow injection features. 7. The method of claim 1 wherein establishing comprises establishing the optimized SEF configuration to include a first type of stall enhancing feature disposed at a location corresponding to a first stall limiting rotor and to include a second, different type of stall enhancing feature disposed at location corresponding to a second stall limiting rotor. 8. The method of claim 7 wherein the first stall limiting rotor comprises the leading rotor in the multistage GTE compressor. 9. The method of claim 8 wherein the first type of stall enhancing feature comprises casing treatment features disposed at a location circumscribing the leading rotor. 10. A method for producing a multistage Gas Turbine Engine (GTE) compressor including a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine, the method comprising: selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine;identifying one or more stall limiting rotors at each of the selected engine speeds utilizing a physical model of the multistage GTE compressor having non-treated removable casing sections;establishing an optimized stall enhancement feature (SEF) configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors; andproducing the multistage GTE compressor in accordance with the optimized SEF configuration;wherein establishing comprises: after identifying one or more stall limiting rotors at each of the selected engine speeds, applying SEFs to the physical model at selected locations corresponding to the stall limiting rotors by replacing corresponding ones of the non-treated casing sections with treated casing sections;after applying SEFs to the physical model, re-testing the model to determine if a predetermined stall threshold is surpassed at each of the selected engine speeds;if the predetermined stall threshold is surpassed at each of the selected engine speeds, utilizing the locations at which the SEFs have been applied to the model to establish the optimized SEF configuration; andif the predetermined stall threshold is not surpassed at each of the selected engine speeds, repeating the steps of applying and retesting. 11. The method of claim 10 wherein identifying comprises: plotting a speed line for each of the selected engine speeds on a compressor performance map, while increasing the axial pressure ratio applied across the physical model of the multistage GTE compressor until stall is reached; andafter reaching stall at each of the selected engine speeds, utilizing data gathered from the physical model to determine which of the rotors contained within the series of axial compressor stages is the stall limiting rotor for each of the selected engine speeds. 12. The method of claim 10 wherein the SEFs comprise grooves formed in an engine casing and circumscribing at least one of the stall limiting rotors in the optimized SEF configuration. 13. The method of claim 10 wherein the SEFs comprise upstream injection features, and wherein the upstream injection features are positioned upstream of at least one of the stall limiting rotors within a flow field thereof. 14. The method of claim 10 wherein establishing comprises establishing the optimized SEF configuration to include a first type of stall enhancing feature disposed at a location corresponding to a first stall limiting rotor and to include a second, different type of stall enhancing feature disposed at location corresponding to a second stall limiting rotor. 15. The method of claim 14 wherein the first stall limiting rotor comprises an upstream rotor and a plurality of additional rotors downstream of the upstream rotor, and wherein the first type of stall enhancing feature comprises casing treatment features disposed at a location circumscribing the upstream rotor.

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Gas turbine engine compressors having optimized stall enhancement feature configurations and methods for the production thereof

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Gas turbine engine compressors having optimized stall enhancement feature configurations and methods for the production thereof

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