[특허]Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser

[미국특허] Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-001/09 F02K-001/04 F02K-003/04
출원번호	US-0719080 (1996-09-24)
발명자 / 주소	Cariola Roy E. Aten Michael R.
출원인 / 주소	Rohr, Inc.
대리인 / 주소	Schlesinger
인용정보	피인용 횟수 : 115 인용 특허 : 0

초록 ▼

A structure to provide a variable nozzle for the fan air flow of a turbofan aircraft gas turbine engine with the nozzle being defined by the exit throat area defined by the aft edge of a trailing edge portion of the fan cowl and the core engine housing. A trailing edge cowl portion is slidably positioned in a rearwardly opening annular cavity in the aft end of the fan cowl for reciprocal axial translation between a deployed position to provide an enlarged exit throat area to provide enhanced performance of the aircraft engine during take off and climb to a cruising altitude and a stowed position to provide an optimum exit throat area for cruise condition of the engine. The trailing edge portion is sealably secured within the core cowl cavity to preclude any air leakage from the fan air stream of the fan duct around the trailing edge portion. A unique dual slider and track arrangement is provided to permit the variable nozzle to be translated aft simultaneously with and/or independently of a translating cowl portion of the fan cowl which may form a portion of a blocker door/cascade thrust reverser structure. The trailing edge portion includes sound attenuation treatment on its inner surface for exposure which when deployed enhances the sound attenuation capability of the nacelle system. The variable nozzle may also be used to advantage with other thrust reverser systems such as a four pivoting door structure positioned in the fan cowl.

대표청구항 ▼

[ What is claimed is:] [1.] A structure to provide a variable nozzle for the fan air flow of an aircraft gas turbine engine, the nozzle being defined by the spacing between a trailing edge portion of the translating cowl and the core engine housing to provide a determinable exit throat area for such fan air flow, said structure comprising:a generally annularly shaped translating cowl that is spaced from and which surrounds a portion of an aft portion of the housing of the core jet engine, said cowl being translatable for thrust reverser purposes and having an annular horizontally extending cavity provided at its trailing edge;a first actuator means cooperating with said translating cowl to reciprocally translate said cowl longitudinally;a generally annularly shaped nozzle trailing edge portion which is positionable within said cavity and reciprocally extensible from a first stowed position to a second extended deployed position, anda second actuator means cooperating with said nozzle trailing edge portion to provide reciprocal determinable extension thereof whereby the throat area defined by the trailing edge portion and the core engine housing may be varied by a predetermined amount in order to provide an optimum throat area for a flight condition of such aircraft jet engine without choking the core jet engine by diminishing the flow of such fan air upstream of such variable nozzle during an extension of said nozzle trailing edge portion. [16.] A method for varying the exit throat area of a nozzle for the fan air stream of an aircraft gas turbine engine, the exit throat area being determined by the core engine housing and the trailing edge of the translating cowl, which method comprises;providing a translating cowl for an aircraft gas turbine engine;providing an axially extending cavity in the aft portion of the translating cowl;positioning a trailing edge cowl portion in such cavity to provide a trailing edge portion and determinably translating the trailing edge cowl portion independently of translation of said translating cowl, to provide a desired exit throat area for a particular aircraft flight condition without choking such aircraft gas turbine engine by restricting said fan air flow during such period as said trailing edge cowl portion has been determinably translated. The method of claim 16 which further includes the step of providing a forward fixed fan cowl immediately adjacent to said translatable cowl and translating the translatable cowl and the trailing edge independently to provide a desired exit throat area. The method of claim 17 which further includes the step of providing the translating cowl with thrust reverser structure which is operable, when the translating cowl is deployed aft, to block the fan air stream and to direct it outwardly and forwardly in a predetermined direction. The method of claim 18 which further includes the step of providing actuator means which are determinably actuable to translate reciprocally the trailing edge portion within the cavity provided in the translating cowl.

이 특허를 인용한 특허 (115) 인용/피인용 타임라인 분석

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[미국특허] Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser 원문보기

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[미국특허] Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser 원문보기

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