Apparatus and method for preventing inlet vortex
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0063900
(2002-05-22)
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발명자
/ 주소 |
- Clark, Terry A.
- Urban, Justin R.
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출원인 / 주소 |
- United Technologies Corporation
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인용정보 |
피인용 횟수 :
8 인용 특허 :
8 |
초록
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A method of operating a gas turbine engine for testing, comprising: providing an aircraft on a tarmac, the aircraft having a gas turbine engine with an inlet; selecting a power setting for the engine that is capable of producing a vortex between the inlet and the tarmac; and inhibiting formation of
A method of operating a gas turbine engine for testing, comprising: providing an aircraft on a tarmac, the aircraft having a gas turbine engine with an inlet; selecting a power setting for the engine that is capable of producing a vortex between the inlet and the tarmac; and inhibiting formation of the vortex. A suppressor for preventing a vortex between an inlet of a gas turbine engine on an aircraft and a tarmac. The suppressor comprises: a base facing the tarmac; and an inclined surface extending in a direction from the tarmac towards the inlet at an angle to the base. The suppressor prevents formation of the vortex.
대표청구항
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1. A method of operating a gas turbine engine for testings comprising the steps of:providing an aircraft on a tarmac, said aircraft having a gas turbine engine with a centerline height (h) and an inlet having a diameter (D); selecting a power setting for said engine that is capable of producing a vo
1. A method of operating a gas turbine engine for testings comprising the steps of:providing an aircraft on a tarmac, said aircraft having a gas turbine engine with a centerline height (h) and an inlet having a diameter (D); selecting a power setting for said engine that is capable of producing a vortex between said inlet and said tarmac; and placing an object between said inlet and said tarmac, said object having a height (w) ranging between approximately (2h-D)/8 and (2h-D)/4; wherein airflow travels around said object to inhibit formation of said vortex. 2. The method of claim 1, wherein said placing step comprises removably placing said object between said inlet and said tarmac.3. The method of claim 1, wherein said engine is located on a wing of said aircraft.4. The method of claim 1, wherein said aircraft remains static on said tarmac while testing said engine.5. The method of claim 1, wherein said power setting comprises up to a full power setting.6. A method of preventing vortex formation, comprising the steps of:providing an aircraft on a tarmac, said aircraft having a gas turbine engine with a centerline height (h) and an inlet having a diameter (D); operating said engine; determining whether said operating step is likely to produce a vortex between said inlet and said tarmac; placing an object between said tarmac and said inlet should said determining step indicate a likelihood of said vortex, said object having a surface with a height (w) ranging between approximately (2h-D)/8 and (2h-D)/4; and directing airflow near said tarmac along said surface of said object towards said engine to inhibit vortex formation. 7. The method of claim 6, wherein said placing step comprises removably placing said object between said tarmac and said inlet.8. The method of claim 6, wherein said engine is located on a wing of said aircraft.9. The method of claim 6, wherein said operating step occurs while said aircraft remains static on said tarmac.10. A method of operating a gas turbine engine mounted on an aircraft located on a tarmac at an elevated engine pressure ratio (EPR) greater than a threshold EPR, said engine having a centerline height (h) and an inlet with a diameter of (D), comprising the steps of:placing an object between said tarmac and said engine to turn airflow near said tarmac towards said engine, said object having a height (w) ranging between approximately (2h-D)/8 and (2h-D)/4; and operating said engine at said elevated EPR to inhibit vorte formation. 11. The method of claim 10, wherein said placing step comprises removably placing said object between said tarmac end said engine.12. The method of claim 10, wherein said engine is located on a wing of said aircraft.13. The method of claim 10, wherein said operating step occurs while said aircraft remains static on said tarmac.14. The method of claim 10, wherein said elevated EPR is up to a full power setting.15. In a method of performing a test including a step of operating a gas turbine engine at an engine pressure ratio that typically requires removing said engine from an aircraft located on a tarmac and placing said engine on a test stand, said engine having a centerline height (h) and an inlet with a diameter (D), wherein the improvement comprises positioning a movable object with a height ranging between approximately (2h-D)/8 and (2h-D)/4 between said engine and said tarmac so that airflow travels around said object to allow said engine to remain on said aircraft for said test and to inhibit vortex formation.16. A suppressor for preventing a vortex between an inlet of a gas turbine engine on an aircraft and a tarmac, said engine having a centerline height (h) and said inlet having a diameter(D), comprising:a base facing said tarmac; and an inclined surface extending in a direction from said tarmac towards said inlet at an angle to said base and having a height ranging between approximately (2h-D)/8 and (2h-D)/4; wherein airflow near said tarmac travels along said incline surface towards said inlet so that said suppressor prevents formation of said vortex. 17. The suppressor of claim 16, wherein said angle is approximately 45°.18. The suppressor of claim 16, wherein said suppressor is portable.19. A suppressor for preventing a vortex between an inlet of a gas turbine engine on an aircraft and a tarmac, said engine having a centerline height (h) and said inlet having a diameter (D), the suppressor:a base; and an inclined surface extending from said base; wherein said inclined surface has a height (w) ranging between approximately (2h-D)/8 and (2h-D)/4 to prevent formation of said vortex. 20. The suppressor of claim 19, wherein h/D is less than approximately 2.5.
이 특허에 인용된 특허 (8)
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Rodyniuk Michael (Calgary CAX) Berg Keevin (Calgary CAX), Aircraft wing cover and method of attachment.
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Norman Lewis Helgeson, Annular after reactor with sound attenuator for use in a jet engine test cell and test stand.
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Schafhaupt Horst (Egenhofen DEX) Ballmann Josef (Aachen DEX), Apparatus for diminishing intake vortexes in jet engines.
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Clark Terry A. (East Hartford CT) Peszko Mark W. (Malborough CT) Roberts John H. (Bolton CT) Muller George L. (Middletown CT) Nikkanen John P. (West Hartford CT), Gas turbine engine test cell.
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Boet Jean-Paul (Villeneuve d\Ascq FRX), Ground test installation for the jet engines of an airliner.
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Bothe Hans-Jurgen,CAX, Hybrid aircraft.
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Gerhardt Hans-Joachim,DEX ; Krueger Oliver,DEX ; Meessen Horst,DEX ; Estadieu Jean-B.,DEX, Method and apparatus for stabilizing an intake air flow of a ground-based turbine engine.
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Lynn Christopher, Stable flow enhancements for ground runup enclosure.
이 특허를 인용한 특허 (8)
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Roark, Michael E.; Boe, Mark S.; Hoelmer, Werner; Gooden, Joop H. M.; de Valk, Gerold; Parchen, Rene; Brettmann, Barie, Aircraft ground run-up enclosure.
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Manning, Robert Francis; Correia, Victor Hugo Silva; Buhler, Jared Peter; Pritchard, Jr., Byron Andrew; Vining, William Collins; Bourassa, Corey; Laskowski, Gregory Michael; Parker, David Vickery, Engine component for a turbine engine.
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Cicala, Robert John, Flush drop-glass window module.
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Murray, Robert Carl; Bourassa, Corey; Parker, David Vickery; Pritchard, Jr., Byron Andrew; Ratzlaff, Jonathan Russell; Vining, William Collins; Krammer, Erich Alois, Separator assembly for a gas turbine engine.
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Nasr, Hojjat; Laskowski, Gregory Michael; Stover, Curtis Walton; Vining, William Collins, Shroud assembly for a gas turbine engine.
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Murray, Robert Carl; Laskowski, Gregory Michael; Bourassa, Corey; Pritchard, Jr., Byron Andrew; Stover, Curtis Walton, Shroud assembly for turbine engine.
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Winter, Michael, Systems and methods for altering inlet airflow of gas turbine engines.
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Krumanaker, Matthew Lee; Dooley, Weston Nolan; Brassfield, Steven Robert; Helmer, David Benjamin; Bailey, Jeremy Clyde; Briggs, Robert David, Turbine blade.
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