[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)	F01D-017/08 F02C-007/045 F02C-007/042 F02C-007/052 F01D-017/10 F02C-007/05 F02K-003/02
출원번호	US-0463114 (2014-08-19)
등록번호	US-10054050 (2018-08-21)
발명자 / 주소	Labrecque, Michel Couture-Gagnon, Vincent Ullyott, Richard
출원인 / 주소	PRATT & WHITNEY CANADA CORP.
대리인 / 주소	Norton Rose Fulbright Canada LLP
인용정보	피인용 횟수 : 0 인용 특허 : 26

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An aeroengine has an inlet system with a forward end with respect to a flight direction. The inlet system includes a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system and a secondary inlet duct for directing a second air flow from a secondary intake opening of the secondary inlet duct to the compressor rotor only when the main inlet duct is closed. A control apparatus is provided fo...

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1. A compressor inlet system for an aeroengine, the compressor inlet system comprising: a main inlet duct for directing a first air flow from a main intake opening to a compressor, the main intake opening defined at a forward end of the compressor inlet system with respect to a flight direction, a secondary inlet duct in fluid communication with the main inlet duct for directing a second air flow from a secondary opening to the compressor, and a control apparatus for selecting which of the first and second air flows to provide to the compressor, the control apparatus comprising a main valve selectively opening the main inlet duct for directing a portion of the first air flow to bypass the compressor and to be discharged from the secondary opening when the first air flow is selected to enter the compressor, and selectively closing the main inlet duct to discontinue the first air flow and to thereby cause the secondary inlet duct to draw air from the secondary opening, wherein the secondary inlet duct is operable to function as an inertial particle separator (IPS) duct of the compressor inlet system, the IPS duct extending from the main inlet duct rearward and terminating at the secondary opening, the secondary opening being a rear opening of the IPS duct, the main valve selectively opening the main inlet duct to operate the IPS duct such that particles and debris carried by the first air flow keep a motion thereof substantially rearward and pass through the IPS duct to be discharged out of the rear opening, the main valve selectively closing the main inlet duct to discontinue the first air flow causing the secondary inlet duct to draw air from the secondary opening for directing the second air flow to the compressor. 2. The compressor inlet system as defined in claim 1 wherein the control apparatus is configured so that the second air flow flows to the compressor only when the main inlet duct is closed to discontinue the first air flow. 3. The compressor inlet system as defined in claim 1 wherein the main inlet duct and the secondary inlet duct share a common downstream portion. 4. The compressor inlet system as defined in claim 1 wherein the main valve is positioned within the main inlet duct, upstream of a location at which the IPS duct is connected to the main inlet duct with respect to the first air flow. 5. The compressor inlet system as defined in claim 1 wherein the secondary inlet duct comprises an acoustic treatment area on an inner surface thereof. 6. The compressor inlet system as defined in claim 1 wherein the secondary inlet duct is in fluid communication with the main inlet duct and extends substantially in a transverse direction with respect to the flight direction. 7. The compressor inlet system as defined in claim 1 wherein the control apparatus comprises the main valve mounted to and for selectively closing the main inlet duct to discontinue the first air flow, and a secondary valve mounted to and for selectively closing the secondary inlet duct and being only open when the main valve is closed. 8. The compressor inlet system as defined in claim 1 wherein the secondary opening is oriented substantially facing a transverse direction with respect to the flight direction. 9. The compressor inlet system as defined in claim 1 wherein the secondary opening is oriented substantially facing forwardly with respect to the flight direction. 10. The compressor inlet system defined in claim 1, wherein the main inlet duct is connected in fluid communication with an annular duct for selectively directing the first air flow from the main intake opening of the main inlet duct to a compressor rotor located downstream of the annular duct with respect to the first air flow, the secondary inlet duct extends substantially in a transverse direction with respect to the flight direction and is connected in fluid communication with the annular duct for selectively directing the second air flow from the secondary opening through the annular duct to the compressor rotor, and the compressor inlet system includes a secondary valve for selectively closing the secondary inlet duct and being only open when the main inlet duct is closed. 11. An aeroengine comprising: an inlet system with a forward end with respect to a flight direction, the inlet system comprising a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system, an inertial particle separator (IPS) duct connected in fluid communication with the main inlet duct and extending rearward for directing a portion of the first air flow to bypass the compressor rotor and to be discharged through an exit opening of the IPS, the exit opening being disposed in a rear location with respect to the forward end of the inlet system, and a valve mounted to the main inlet duct in a location upstream of the IPS duct with respect to the first air flow, the valve selectively opening the main inlet duct to operate the IPS duct such that particles and debris carried by the first air flow keep a motion thereof substantially rearward and pass through the IPS duct to be discharged out of the rear opening, the valve selectively closing the main inlet duct to discontinue the first air flow such that the IPS duct draws a second air flow from the exit opening and directs the second air flow to the compressor rotor. 12. The aeroengine as defined in claim 11 wherein the inlet system comprises an annular duct connected in fluid communication with the main inlet duct and positioned immediately upstream of the compressor rotor, the IPS duct being connected to the main inlet duct immediately upstream of the annular duct. 13. The aeroengine as defined in claim 11 wherein the IPS duct extends from the main inlet duct substantially rearward and terminates at the exit opening. 14. The aeroengine as defined in claim 11 wherein the IPS duct comprises an acoustic treatment area on an inner surface thereof. 15. An aeroengine comprising: an inlet system with a forward end with respect to a flight direction, the inlet system comprising a main inlet duct connected in fluid communication with an annular duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor located downstream of the annular duct with respect to the first air flow, the forward main intake opening being defined at the forward end of the inlet system, and a secondary inlet duct having a secondary intake opening and extending substantially in a transverse direction with respect to the flight direction and being connected in fluid communication with the annular duct, the secondary inlet duct selectively directing a secondary air flow from the secondary intake opening through the annular duct to the compressor rotor, and an inertial particle separator (IPS) duct connected in fluid communication with the main inlet duct immediately upstream of the annular duct and extending rearward for directing a portion of the first air flow to bypass the compressor rotor and to be discharged through an exit opening at a rear end of the IPS duct, the inlet system including a valve apparatus having a main valve for selectively opening the main inlet duct to operate the IPS duct such that particles and debris carried by the first air flow keep a motion thereof substantially rearward and pass through the IPS duct to be discharged out of the rear opening, the main valve selectively closing the main inlet duct to discontinue the first air flow, and a secondary valve device for selectively closing the secondary inlet duct and being only open when the main inlet duct is closed. 16. The aeroengine as defined in claim 15 wherein the secondary inlet duct comprises a pair of secondary inlet branches in a bifurcated configuration, the secondary inlet branches being connected in fluid communication with the annular duct, each of the secondary inlet branches having said secondary intake opening, the secondary valve device selectively and simultaneously closing or opening both of the secondary inlet branches. 17. The aeroengine as defined in claim 16 wherein each of the secondary intake openings is oriented facing forwardly with respect to the flight direction in order to increase a pressure of the secondary air flow to a level greater than an ambient air pressure in order to prevent the IPS duct from drawing the ambient air through the exit opening. 18. The aeroengine as defined in claim 16 wherein each of the secondary inlet branches comprises an acoustic treatment area on an inner surface thereof.

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Low noise aeroengine inlet system

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Low noise aeroengine inlet system

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IPC 상세정보(version : 201201)

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