[특허]System and method for operating a thrust reverser for a turbofan propulsion system

Woodward HRT, Inc.

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특허 상세정보

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System and method for operating a thrust reverser for a turbofan propulsion system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/02 F02K-001/72 F02K-001/76
미국특허분류(USC)	060/226.2; 060/771; 060/226.3; 244/110B; 239/265.19
출원번호	US-0969258 (2010-12-15)
등록번호	US-8713911 (2014-05-06)
발명자 / 주소	Kopecek, Joseph Thomas Walker, Peter William
출원인 / 주소	Woodward HRT, Inc.
대리인 / 주소	Fish & Richardson P.C.
인용정보	피인용 횟수 : 5 인용 특허 : 18

초록
▼

A thrust reverser assembly for use in a turbofan engine assembly. The engine assembly includes a core gas turbine engine and a core cowl which circumscribes the core gas turbine engine. A nacelle is positioned radially outward from the core cowl to define a fan nozzle duct between the core cowl and a portion of the nacelle. The nacelle includes a stationary cowl. The thrust reverser assembly includes a first translating cowl that is slidably coupled to the nacelle. The first translating cowl is positionable with respect to the stationary cowl. A second translating cowl is slidably coupled to the nacelle such that the first translating cowl is positioned between the stationary cowl and the second translating cowl. The second translating cowl is positionable with respect to the first translating cowl. A positioning assembly is coupled to the first translating cowl. An actuator assembly is operatively coupled to the second translating cowl for selectively moving the second translating cowl. The actuator assembly is configured to engage the positioning assembly to selectively move the first translating cowl.

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1. A thrust reverser assembly for use in a turbofan engine assembly, the engine assembly including a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl to define a fan nozzle duct between the core cowl and a portion of the nacelle, the nacelle including a stationary cowl, said thrust reverser assembly comprising: a first translating cowl slidably coupled to the nacelle, said first translating cowl positionable with respect to the stationary cowl;a second translating cowl slidably coupled to the nacelle such that said first translating cowl is positioned between the stationary cowl and said second translating cowl, said second translating cowl positionable with respect to said first translating cowl;an actuator coupled to a positioning assembly, said positioning assembly operatively coupled to said first translating cowl and said second translating cowl for selectively moving said first translating cowl and said second translating cowl; andan actuator lock coupled to said actuator to releasably lock said second translating cowl to the stationary cowl. 2. A thrust reverser assembly in accordance with claim 1, wherein said actuator is configured to move said first translating cowl and said second translating cowl between a first operational position, a second operational position, and a third operational position, said first translating cowl and said second translating cowl positioned adjacent the stationary cowl in the first operational position, said second translating cowl positioned a distance from said first translating cowl in the second operational position, and said first translating cowl positioned a distance from the stationary cowl in the third operational position. 3. A thrust reverser assembly in accordance with claim 2, wherein said actuator engages said positioning assembly to move said first translating cowl between the first and third operational positions. 4. A thrust reverser assembly in accordance with claim 2, wherein said actuator comprises a plurality of cowl locks coupled to the stationary cowl to releasably lock said first translating cowl to the stationary cowl. 5. A thrust reverser assembly in accordance with claim 2, wherein said first translating cowl comprises a slider assembly, said thrust reverser assembly further comprising a track lock coupled to the stationary cowl and configured to selectively engage said slider assembly to releasably lock said first translating cowl to the stationary cowl. 6. A thrust reverser assembly in accordance with claim 2, wherein said positioning assembly comprises a positioning member coupled to said first translating cowl, said positioning member defining a slot extending between a forward sidewall and a aft sidewall, a rod assembly extending through said slot and configured to contact said aft sidewall to move said first translating cowl from the first operational position to the third operational position and to contact said forward sidewall to move said first translating cowl from the third operational position to the first operational position. 7. A turbofan engine assembly comprising: a core gas turbine engine;a core cowl which circumscribes said core gas turbine engine;a nacelle positioned radially outward from said core cowl to define a fan nozzle duct between said nacelle and said core cowl, said nacelle comprising a stationary cowl;a thrust reverser assembly coupled to said nacelle for adjusting a thrust of said gas turbine engine, said thrust reverser assembly comprising:a first translating cowl slidably coupled to said nacelle, said first translating cowl positionable with respect to said stationary cowl;a second translating cowl slidably coupled to said nacelle such that said first translating cowl is positioned between said stationary cowl and said second translating cowl, said second translating cowl positionable with respect to said first translating cowl;an actuator coupled to a positioning assembly, said positioning assembly operatively coupled to said first translating cowl and said second translating cowl for selectively moving said first translating cowl and said second translating cowl; andan actuator lock coupled to said actuator to releasably lock said second translating cowl to the stationary cowl. 8. A turbofan engine assembly in accordance with claim 7, wherein said actuator is configured to move said first translating cowl and said second translating cowl between a first operational position, a second operational position, and a third operational position, said first translating cowl and said second translating cowl positioned adjacent said stationary cowl in the first operational position, said second translating cowl positioned a distance from said first translating cowl in the second operational position, and said first translating cowl positioned a distance from the said stationary cowl in the third operational position. 9. A turbofan engine assembly in accordance with claim 8, wherein said actuator engages said positioning assembly to move said first translating cowl between the first and third operational positions. 10. A turbofan engine assembly in accordance with claim 8, wherein said actuator comprises a plurality of cowl locks coupled to said stationary cowl to releasably lock said first translating cowl to said stationary cowl. 11. A turbofan engine assembly in accordance with claim 8, wherein said first translating cowl comprises a slider assembly, said thrust reverser assembly further comprising a track lock coupled to said stationary cowl and configured to selectively engage said slider assembly to releasably lock said first translating cowl to said stationary cowl. 12. A turbofan engine assembly in accordance with claim 8, wherein said positioning assembly includes a positioning member coupled to said first translating cowl, said positioning member defining a slot extending between a forward sidewall and a aft sidewall, a rod assembly extending through said slot and configured to contact said aft sidewall to move said first translating cowl from the first operational position to the third operational position and to contact said forward sidewall to move said first translating cowl from the third operational position to the first operational position. 13. A method for operating a turbofan engine assembly, the turbofan engine assembly including a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl to define a fan nozzle duct between the core cowl and a portion of the nacelle, a stationary cowl coupled to the nacelle, a first translating cowl coupled to the nacelle and positionable with respect to the stationary cowl, a second translating cowl coupled to the nacelle and positionable with respect to the first translating cowl, and a thrust reverser assembly coupled to the nacelle, said method comprising: selectively positioning the second translating cowl between a first operational position and a second operational position using an actuator and a positioning assembly, to adjust an area of the fan nozzle duct;selectively positioning the first translating cowl between the first operational position and a third operational position using the actuator and the positioning assembly, to adjust an amount of air flowing through the fan duct nozzle and the thrust reverser assembly to facilitate effecting reverse thrust of the turbofan engine assembly;releasably locking the first translating cowl to the stationary cowl; andreleasably locking the second translating cowl to the stationary cowl using an actuator lock coupled to the actuator. 14. A method in accordance with claim 13, further comprising positioning the first translating cowl and the second translating cowls adjacent the stationary cowl in the first operational position, positioning the second translating cowl a distance from the first translating cowl in the second operational position, and positioning the first translating cowl a distance from the stationary cowl in the third operational position. 15. A method in accordance with claim 14, wherein the thrust reverser assembly includes a positioning assembly coupled to the first translating cowl and an actuator operatively coupled to the first translating cowl and the second translating cowl, said method further comprises operating the actuator to engage the positioning assembly to selectively position the first translating cowl between the first and third operational positions. 16. A method in accordance with claim 15, wherein the thrust reverser assembly includes a plurality of locks coupled to the stationary cowl and configured to releasably lock the first translating cowl to the stationary cowl, said method further comprises: locking the first translating cowl to the stationary cowl; andpositioning the second translating cowl between the first and second operational positions with the first translating cowl locked to the stationary cowl.

이 특허에 인용된 특허 (18)

이 특허를 인용한 특허 피인용횟수: 5

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System and method for operating a thrust reverser for a turbofan propulsion system

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System and method for operating a thrust reverser for a turbofan propulsion system

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