[특허]Flow control redistribution to mitigate high cycle fatigue

Lockheed Martin Corporation

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Flow control redistribution to mitigate high cycle fatigue

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B63H-011/00
미국특허분류(USC)	060/204; 060/269
출원번호	US-0497225 (2009-07-02)
등록번호	US-8402738 (2013-03-26)
발명자 / 주소	Truax, Philip P. Miller, Daniel N. Ma, Edward C.
출원인 / 주소	Lockheed Martin Corporation
대리인 / 주소	Bracewell & Giuliani LLP
인용정보	피인용 횟수 : 1 인용 특허 : 5

초록
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A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow. The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.

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1. A method operable to improve pressure recovery and distortion of an inlet, comprising: providing a first fluid flow to at least one primary jet vortex generator, wherein the at least one primary jet vortex generator injects fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet;providing a second fluid flow to at least one secondary jet vortex generator wherein the at least one secondary jet vortex generator injects inject fluid at a second injection rate into the boundary layer of the primary fluid flow within the inlet, and wherein the fluid injected at the first injection rate and second injection rate are operable to induce secondary flow structure(s) within the boundary layer; andredistributing a ratio of the first injection rate and second injection rate to improve pressure recovery and distortion of the inlet when at least one particular engine condition exists;wherein redistributing the first injection rate and second injection rate comprises adjusting a ratio of a first pressure within a first manifold and a second pressure within a second manifold, wherein the first manifold provides the first fluid flow to the at least one primary jet vortex generator and the second manifold provides the second fluid flow to the at least one secondary j et vortex generator. 2. The method of claim 1, further comprising sensing the at least one particular engine condition. 3. The method of claim 2, wherein the at least one particular engine condition comprises at least one engine speed corresponding to a blade frequency. 4. The method of claim 1, wherein the at least one primary jet vortex generator and at least one secondary jet vortex generator are positioned laterally relative to one another within the engine inlet. 5. The method of claim 1, wherein the at least one primary jet vortex generator is positioned forward of the at least one secondary jet vortex generator. 6. The method of claim 1, wherein the redistribution of the ratio of the first injection rate and second injection rate mitigate blade vibration at the at least one particular engine condition. 7. The method of claim 1, wherein the redistribution of the ratio of the first injection rate and second injection rate alters circumferential distortion across the engine inlet. 8. The method of claim 1, further comprising: sensing, circumferential distortion across the engine inlet;comparing the sensed circumferential distortion across the engine inlet to a desired circumferential distortion across the engine inlet; andredistributing the ratio of the first injection rate and second injection rate when the sensed circumferential distortion across the engine inlet compares unfavorably to the desired circumferential distortion across the engine inlet. 9. The method of claim 1, further comprising: sensing flow conditions within the primary fluid flow, with a flow sensor system; andwherein dynamically redistributing the ratio of the first injection rate and second injection rate allows a desired pressure recovery and/or distortion of the inlet to be achieved. 10. The method of claim 1, wherein the at least one primary jet vortex generator and at least one secondary jet vortex generator comprise micro jets operable to inject momentum into a near-wall boundary region. 11. The method of claim 10, wherein the micro-jets comprise micro fabricated mechanical structures. 12. A method operable to improve pressure recovery and distortion of an inlet, comprising: injecting fluid from at least one primary vortex generator at a first injection rate into a boundary layer of a primary fluid flow within the inlet;injecting fluid from at least one secondary jet vortex generator at a second injection rate into the boundary layer of the primary fluid flow within the inlet, wherein the fluid injected at the first injection rate and second injection rate are operable to induce secondary flow structures within the boundary layer, and wherein the at least one primary jet vortex generator and at least one secondary jet vortex generator are positioned laterally relative to one another within the engine inlet;redistributing a ratio of the first injection rate and second injection rate to improve pressure recovery and distortion of the inlet when at least one particular engine condition exists; andsensing the at least one particular engine condition, the particular engine condition comprising at least one engine speed corresponding to a blade frequency;wherein redistributing the first injection rate and second injection rate comprises adjusting a ratio of a first pressure within a first manifold mad a second pressure within a second manifold, wherein the first manifold provides a first fluid flow to the at least one primary jet vortex generator and the second manifold provides a second fluid flow to the at least one secondary jet vortex generator. 13. The method of claim 12, further comprising: sensing, circumferential distortion across the engine inlet;comparing the sensed circumferential distortion across the engine inlet to a desired circumferential distortion across the engine inlet; andredistributing the ratio of the first injection rate and second injection rate when the sensed circumferential distortion across the engine inlet compares unfavorably to the desired circumferential distortion across the engine inlet. 14. A method operable to improve pressure recovery and distortion of an inlet, comprising: providing a first fluid flow to at least one primary jet vortex generator, wherein the at least one primary jet vortex generator injects fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet;providing a second fluid flow to at least one secondary jet vortex generator wherein the at least one secondary jet vortex generator injects inject fluid at a second injection rate into the boundary layer of the primary fluid flow within the inlet, and wherein the fluid injected at the first injection rate and second injection rate are operable to induce secondary flow structure(s) within the boundary layer; andredistributing a ratio of the first injection rate and second injection rate to improve pressure recovery and distortion of the inlet when at least one particular engine condition exists;wherein redistributing the first injection rate and second injection rate comprises adjusting a ratio of a first pressure within a first manifold and a second pressure within a second manifold, wherein the first manifold provides the first fluid flow to the at least one primary jet vortex generator and the second manifold provides the second fluid flow to the at least one secondary jet vortex generator;wherein redistributing the first injection rate and second injection rate is achieved dynamically and allows a desired pressure recovery to be achieved; andsensing flow conditions within the primary fluid flow, with a flow sensor system.

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이 특허를 인용한 특허 피인용횟수: 1

Efremkin, Artem P.; Efremkin, Pavel V.. Method and device to increase thrust and efficiency of jet engine. USP2015069046057.

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Flow control redistribution to mitigate high cycle fatigue

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Flow control redistribution to mitigate high cycle fatigue

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