[특허]Nacelle assembly having inlet airfoil for a gas turbine engine

United Technologies Corporation

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Nacelle assembly having inlet airfoil for a gas turbine engine

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-033/02
미국특허분류(USC)	244/053B; 060/226.2; 060/230; 060/262; 060/226.1; 415/119; 415/914; 415/126; 415/220; 415/221
출원번호	US-0739216 (2007-04-24)
등록번호	US-8408491 (2013-04-02)
발명자 / 주소	Jain, Ashok K. Winter, Michael
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Carlson, Gaskey & Olds PC
인용정보	피인용 횟수 : 2 인용 특허 : 80

초록

A nacelle assembly includes an inlet lip section and an airfoil adjacent to the inlet lip section. The airfoil is selectively moveable between a first position and a second position to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly.

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1. A nacelle assembly, comprising: an inlet lip section; andat least one airfoil stored in a cavity defined inside said inlet lip section, wherein said cavity is disposed between a radially outer and a radially inner wall of said inlet lip section, and said at least one airfoil is selectively moveable between a first position and a second position in response to a sensing signal and without moving any other portion of the nacelle assembly to influence a flow of oncoming airflow and influence an effective boundary layer thickness of the nacelle assembly. 2. The assembly as recited in claim 1, wherein said first position is within said cavity and said second position is radially outward relative to said inlet lip section. 3. The assembly as recited in claim 1, wherein said first position is within said cavity and said second position is radially inward relative to said nacelle assembly. 4. The assembly as recited in claim 1, comprising an arm attached to said at least one airfoil. 5. The assembly as recited in claim 4, wherein said at least one airfoil is pivotally attached to said arm via a pivot mount. 6. The assembly as recited in claim 1, wherein an exterior surface of said at least one airfoil is flush with an exterior surface of said nacelle assembly in said first position. 7. The assembly as recited in claim 1, comprising a plurality of airfoils positioned circumferentially about said nacelle assembly adjacent to said inlet lip section. 8. The assembly as recited in claim 1, wherein said at least one airfoil is selectively introduced at both an interior wall and an exterior wall of the nacelle assembly. 9. The assembly as recited in claim 1, comprising an arm connected between opposing ends of said at least one airfoil, wherein said at least one airfoil is pivotally mounted to said arm at a pivot mount. 10. The assembly as recited in claim 1, wherein said at least one airfoil is an intip. 11. The assembly as recited in claim 1, wherein said cavity and said at least one airfoil are of the same shape. 12. A gas turbine engine, comprising: at least one fan section, at least one compressor section, at least one combustor section and at least one turbine section, wherein said fan section includes a geartrain;a nacelle assembly at least partially surrounding said at least one compressor section, said at least one combustor section and said at least one turbine section, wherein said nacelle assembly includes an inlet lip section and at least one airfoil adjacent to said inlet lip section, said at least one airfoil selectively moveable between a first position and a second position to influence an effective boundary layer thickness of said nacelle assembly;a controller that identifies an operability condition, wherein said controller selectively commands movement of said at least one airfoil between said first position and said second position in response to said operability condition; anda sensor that produces a sensing signal representing said operability condition and communicates said sensing signal to said controller. 13. The gas turbine engine as recited in claim 12, comprising an actuator assembly in communication with said controller to move said at least one airfoil between said first position and said second position in response to detecting said operability condition. 14. The gas turbine engine as recited in claim 12, comprising an arm attached to said at least one airfoil, said at least one airfoil pivotally attached to said arm. 15. The gas turbine engine as recited in claim 12, wherein said nacelle assembly includes a cavity and said at least one airfoil is stored within said cavity in said first position. 16. The gas turbine engine as recited in claim 12, wherein an exterior surface of said at least one airfoil is flush with an exterior surface of said nacelle assembly in said first position. 17. The gas turbine engine as recited in claim 12, comprising a plurality of airfoils positioned circumferentially about said nacelle assembly adjacent to said inlet lip section. 18. The gas turbine engine as recited in claim 12, wherein said at least one airfoil is stored in a cavity defined inside said inlet lip section, said cavity disposed between a radially outer and a radially inner wall of said inlet lip section. 19. A method of increasing an effective boundary layer thickness of an inlet section of a nacelle of a gas turbine engine, comprising the steps of: (a) sensing an operability condition;(b) communicating a sensing signal representative of the operability condition; and(c) selectively translating an airfoil positioned adjacent to the inlet lip section in a radial outward direction from the nacelle without moving any other portion of the nacelle in response to the sensing signal. 20. The method as recited in claim 19, wherein said step (b) comprises: moving the airfoil between a first position and a second position, wherein the second position is radially outward from the first position. 21. The method as recited in claim 20, comprising the step of: (c) returning the airfoil to the first position in response to sensing a cruise condition. 22. The method as recited in claim 20, comprising the step of: (d) pivoting the airfoil from the second position to a third position different than the first position to control a flow stagnation point of oncoming airflow. 23. The method as recited in claim 22, wherein the step of pivoting the airfoil from the second position to the third position includes pivoting the airfoil until the airfoil is substantially perpendicular to a direction of the oncoming airflow.

이 특허에 인용된 특허 (80)

이 특허를 인용한 특허 피인용횟수: 2

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특허 상세정보

Nacelle assembly having inlet airfoil for a gas turbine engine

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특허 상세정보

Nacelle assembly having inlet airfoil for a gas turbine engine

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이 특허에 인용된 특허 (80)

이 특허를 인용한 특허 피인용횟수: 2

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