[특허]Low noise aeroengine inlet system

PRATT & WHITNEY CANADA CORP.

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Low noise aeroengine inlet system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/045 F02C-007/042 F02K-003/06
출원번호	US-0463031 (2014-08-19)
등록번호	US-9957889 (2018-05-01)
발명자 / 주소	Labrecque, Michel Couture-Gagnon, Vincent Ullyott, Richard
출원인 / 주소	PRATT & WHITNEY CANADA CORP.
대리인 / 주소	Norton Rose Fulbright Canada
인용정보	피인용 횟수 : 0 인용 특허 : 26

초록

An aeroengine is provided with a splitter apparatus disposed in a section of an inlet duct. The splitter apparatus can be actuated from a stowed position to a deployed position to allow splitter(s) to selectively move from out of the inlet flow to a position extending into the inlet duct to divide the inlet flow into multiple passages.

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1. An aeroengine comprising an inlet duct for directing an air flow from an inlet opening to a compressor rotor, and an inlet splitter apparatus disposed within a section of the inlet duct and having at least one splitter plate pivotally mounted to a wall of the inlet duct about an axis substantially parallel to a direction of the air flow, the at least one splitter plate being pivotally moveable between a deployed position in which the at least one splitter plate extends from the wall of the inlet duct into the inlet duct to expose both sides of the plate to the air flow, and a stowed position in which one side of the at least one plate is positioned against the wall of the inlet duct and the other side of the at least one plate is substantially exposed to the air flow, the at least one splitter plate extends from said one of the top and bottom walls across the inlet duct to the other one of the top and bottom walls, thereby forming a partition wall between the top and bottom walls in said section of the inlet duct when the splitter apparatus is in the deployed position. 2. The aeroengine as defined in claim 1, wherein the at least one splitter plate comprises perforations extending therethrough. 3. The aeroengine as defined in claim 1, wherein the at least one splitter plate comprises acoustic treatment material applied to at least one side of the at least splitter one plate. 4. The aeroengine as defined in claim 1, wherein said section of the inlet duct comprises a flat top wall and a flat bottom wall opposite one to the other, the at least one splitter plate being pivotally mounted to one of the flat top and bottom walls. 5. The aeroengine as defined in claim 4, wherein said section of the inlet duct is disposed adjacent the inlet opening. 6. The inlet system as defined in claim 1, wherein said one of the top and bottom walls includes at least one acoustic treatment area that is covered by the at least one splitter plate when the at least one splitter plate is in the stowed position and is exposed when the at least one splitter plate is in the deployed position. 7. An aeroengine inlet system, the inlet system comprising an inlet duct for directing an air flow from an inlet opening to a compressor rotor of an aeroengine, the inlet duct having a section including opposed and substantially flat first and second peripheral walls, an inlet splitter apparatus disposed within said section of the inlet duct and including first and third splitter plates pivotally mounted to the first peripheral wall about respective first and third axes substantially parallel to a direction of the air flow, and second and fourth splitter plates pivotally mounted to the second peripheral wall about respective second and fourth axes substantially parallel to the direction of the air flow, the splitter apparatus being operative between a stowed position in which the first and third splitter plates are pivoted to a position parallel to and adjacent the first peripheral wall and the second and fourth splitter plates are pivoted to a position parallel to and adjacent the second peripheral wall, and a deployed position in which the first and second splitter plates are pivoted to extend from the respective first and second peripheral walls into the inlet duct such that the first splitter plate extends to the second splitter plate to in combination form a first partition wall extending through said section between the first and second peripheral walls and the third and fourth splitter plates are pivoted to extend from the respective first and second peripheral walls into the inlet duct such that the third splitter plate extends to the fourth splitter plate to in combination form a second partition wall extending through said section of the inlet duct between the first and second peripheral walls. 8. The inlet system as defined in claim 7, wherein the first and third axes are spaced apart by a first distance to allow free pivotal motion of the respective first and third splitter plates, and wherein the second and fourth axes are spaced apart by a second distance to allow free pivotal motion of the respective second and fourth splitter plates. 9. The inlet system as defined in claim 8, wherein the first and second distances are substantially equal. 10. The inlet system as defined in claim 7, comprising an actuation apparatus for actuating the pivotal motion of the respective first, second, third and fourth splitter plates. 11. The inlet system as defined in claim 7, wherein the first, second, third and fourth splitter plates comprise acoustic treatment areas on both sides of the respective splitter plates. 12. The inlet system as defined in claim 7, wherein an inner surface of the respective first and second peripheral walls in said section of the inlet duct defines an acoustic treatment area on the respective first and second peripheral walls.

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Low noise aeroengine inlet system

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