[특허]Power plant for a rotary wing aircraft

Eurocopter

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Power plant for a rotary wing aircraft

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-035/08
미국특허분류(USC)	244/055; 244/017.11
출원번호	UP-0790976 (2007-04-30)
등록번호	US-7717369 (2010-06-10)
우선권정보	FR-06 03869(2006-04-28)
발명자 / 주소	Chaniot, Daniel Gaulmin, François-Xavier Iraudo, Lionel
출원인 / 주소	Eurocopter
대리인 / 주소	Young & Thompson
인용정보	피인용 횟수 : 1 인용 특허 : 9

초록

The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.

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What is claimed is: 1. A power plant (18), comprising: at least one turboshaft engine (8) for driving a main rotor (3) of a rotary wing aircraft (1) via a main gearbox (7) and a rotor shaft (6), the engine (8) being disposed substantially in a longitudinal direction, lying on or parallel with the longitudinal axis X of the aircraft (1) and behind the main gearbox (7) relative to the longitudinal direction of axis X, wherein the main gearbox (7) is driven in rotation by a power transmission shaft (10) connected to a free turbine (11) of the engine (8), the free turbine (11) is driven in rotation by the gas generator (30) of the engine (8), which is fed with air via an air inlet body (20), the hot gas is exhausted via a nozzle (15), and said air inlet body (20) is substantially parallel to the engine (8) and has a first end (21) defining an air inlet exposed to ambient atmosphere in front of the hot gas exhaust nozzle (15), the air inlet being substantially in a transverse Y,Z plane containing the rotor shaft (6) of the main rotor (3), and a second end (22) connected to the engine (8) at a rearmost zone of the engine (8) that is rearmost relative to the longitudinal direction X. 2. A power plant according to claim 1, wherein the air inlet body (20) is elongate and of length L greater than a length l of the engine (8). 3. A power plant (18) according to claim 1, wherein the second end (22) of the air inlet body (20) is a plenum chamber (23) for the drawn-in air, that is substantially annular in shape so as to surround said engine (8). 4. A power plant (18) according to claim 1, wherein a distance d between the first end (21) of the air inlet body and the outlet (16) of the hot gas exhaust nozzle (15) is of the order of 1.5 m. 5. A power plant (18) according to claim 1, wherein the distance d between the first end (21) of the air inlet body and the outlet (16) of the hot gas exhaust nozzle (15) is substantially equal to the length l of the engine. 6. A power plant (18) according to claim 1, wherein an air flow section of the air inlet body (20) is less than a hot gas flow section of the nozzle (15). 7. A power plant (18) according to claim 1, wherein the air inlet body (20) is made of composite materials. 8. A power plant (18) according to claim 1, wherein the air inlet body (20) is situated above the engine (8), and the outlet (16) from the hot gas exhaust nozzle (15) opens laterally outwards from the helicopter (1), being substantially parallel to the transverse axis Y, either towards positive Y coordinates, or towards negative Y coordinates. 9. A power plant (18) according to claim 1, wherein the air inlet body (20) is situated substantially laterally, beside the engine (8), and wherein the outlet (16) from the hot gas exhaust nozzle (15) opens out substantially towards positive Z coordinates. 10. A power plant (18) according to claim 1, wherein each power plant (18) is disposed in an individual compartment containing a single engine (8) and a single piece of equipment for ventilation, drainage, detecting fire, and combating fire. 11. A power plant (18) comprising: two turboshaft engines (8) for driving a main rotor (3) of a rotary wing aircraft (1) via a main gearbox (7) and a rotor shaft (6), the engines (8) being disposed substantially in a longitudinal direction, lying parallel with the longitudinal axis X of the aircraft (1) and behind the main gearbox (7) relative to the longitudinal direction of axis X, wherein the main gearbox (7) is driven in rotation by a respective power transmission shaft (10) connected to a free turbine (11) of the engines (8), the free turbine (11) is driven in rotation by the gas generator (30) of the engines (8), each of the engines (8) has only a single respective air inlet body (20) for feeding air thereto, the hot gas is exhausted via a nozzle (15), and each said air inlet body (20) is substantially parallel to the engines (8) and has a first end (21) with an air inlet in front of the hot gas exhaust nozzle (15) and substantially in a transverse Y,Z plane containing the rotor shaft (6) of the main rotor (3), and a second end (22) connected to a respective one of the engines (8) at at a rearmost zone of the respective engine (8) that is rearmost relative to the longitudinal direction X. 12. A power plant according to claim 11, wherein a port one of the engines (8) is fed air from a first said air inlet body (20) disposed to a port side of the port engine and a starboard one of the engines (8) is fed air from a second said air inlet body (20) disposed to a starboard side of the starboard engine, and body (20) disposed to a starboard side of the port engine and a starboard one of the engines (8) is fed air from a second said air inlet body (20) disposed to a port side of the starboard engine.

이 특허에 인용된 특허 (9)

이 특허를 인용한 특허 피인용횟수: 1

Wagner, Joel H.; Magge, Shankar S.; Santeler, Keith A.. Centrifugal compressor with bleed flow splitter for a gas turbine engine. USP2015018935926.

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Power plant for a rotary wing aircraft

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Power plant for a rotary wing aircraft

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이 특허에 인용된 특허 (9)

이 특허를 인용한 특허 피인용횟수: 1

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IPC 상세정보(version : 201201)

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