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公开(公告)号：US12018615B2
公开(公告)日：2024-06-25
申请号：US17977680
申请日：2022-10-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Eray Akcayoz , Mark Cunningham , Raja Ramamurthy , Roberto Marrano
Abstract: An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, and a flow control device. The air inlet duct includes an intake inlet of the air intake. The core flow duct includes a core flow outlet. The core flow duct extends between and to the air inlet duct and the core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct extends between and to the air inlet duct and the bypass flow outlet. The bypass flow duct includes an interior surface forming and surrounding a bypass flow passage through the bypass flow duct. The flow control device is disposed on the interior surface. The flow control device is configured to variably control an area of a cross-sectional flow area of the bypass flow passage.
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2.发明公开公开(公告)号：US20240141832A1
公开(公告)日：2024-05-02
申请号：US17977722
申请日：2022-10-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Mark Cunningham , Eray Akcayoz , Raja Ramamurthy , Roberto Marrano
CPC classification number: F02C7/042 , F02C9/20 , F05D2220/323 , F05D2240/12 , F05D2270/60
Abstract: An air intake for an aircraft propulsion system includes an air inlet duct and a flow control device. The air inlet duct includes an interior surface and an intake inlet. The interior surface extends from the intake inlet. The interior surface forms and surrounds an inlet flow passage through the air inlet duct. The intake inlet includes a top side, a bottom side, a first lateral side, and a second lateral side. Each of the first lateral side and the second lateral side extend between and to the top side and the bottom side. The flow control device is disposed inside the air inlet duct at the first lateral side. The flow control device is configured to form an asymmetrical shape of the intake inlet at the first lateral side relative to the second lateral side.
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公开(公告)号：US11952962B1
公开(公告)日：2024-04-09
申请号：US18162269
申请日：2023-01-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Eray Akcayoz , Mark Cunningham
IPC: F02K1/40
CPC classification number: F02K1/40 , F05D2220/323 , F05D2250/51 , F05D2250/52 , F05D2250/71 , F05D2250/73
Abstract: An exhaust duct of an aircraft engine includes an annular inlet conduit having an inlet central axis, and at least two outlet conduits in flow communication with the inlet conduit. The at least two outlet conduits are located non-parallel to the inlet central axis. Each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits. At least one of the outlet ports is non-circular in cross-sectional shape.
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公开(公告)号：US11933220B1
公开(公告)日：2024-03-19
申请号：US17977737
申请日：2022-10-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Raja Ramamurthy , Eray Akcayoz , Mark Cunningham , Roberto Marrano
CPC classification number: F02C7/05 , F02C7/042 , F02C7/057 , F02C9/18 , F05D2220/323
Abstract: An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, a splitter, and a flow control device. The air inlet duct includes an intake inlet and a gas path floor. The core flow duct includes a core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct includes the gas path floor. The splitter separates the core flow duct and the bypass flow duct. The flow control device is disposed on a portion of the gas path floor. The flow control device is configured to be selectively positioned to control an air flow path for air flowing through the air inlet duct, the core flow duct, and the bypass flow duct.
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5.发明公开公开(公告)号：US20240141833A1
公开(公告)日：2024-05-02
申请号：US17977680
申请日：2022-10-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Eray Akcayoz , Mark Cunningham , Raja Ramamurthy , Roberto Marrano
Abstract: An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, and a flow control device. The air inlet duct includes an intake inlet of the air intake. The core flow duct includes a core flow outlet. The core flow duct extends between and to the air inlet duct and the core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct extends between and to the air inlet duct and the bypass flow outlet. The bypass flow duct includes an interior surface forming and surrounding a bypass flow passage through the bypass flow duct. The flow control device is disposed on the interior surface. The flow control device is configured to variably control an area of a cross-sectional flow area of the bypass flow passage.
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Patent Agency Ranking
公开(公告)号：US11919654B2
公开(公告)日：2024-03-05
申请号：US17817749
申请日：2022-08-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Eray Akcayoz
CPC classification number: B64D33/02 , F02C7/042 , B64D2033/0293 , F05D2220/323 , F05D2250/51
Abstract: An aircraft engine, has: an inlet leading to a compressor section, the inlet extending circumferentially around a central axis; an annular inlet duct extending circumferentially around the central axis, the annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet, the duct outlet extending circumferentially around the central axis; and a flow restrictor located within the annular inlet duct, the flow restrictor extending across the annular inlet duct, being movable within the annular inlet duct along a circumferential direction relative to the central axis in response to a fluid pressure differential on opposed sides of the flow restrictor.
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公开(公告)号：US11808207B1
公开(公告)日：2023-11-07
申请号：US17817758
申请日：2022-08-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Eray Akcayoz
CPC classification number: F02C7/057 , F01D17/08 , F01D17/141 , F02C7/042 , F05D2270/3015
Abstract: An aircraft engine, has: an inlet extending circumferentially around a central axis; an annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet; a flow restrictor extending across the annular inlet duct and being movable within the annular inlet duct; an actuator engaged to the flow restrictor and operable to move the flow restrictor; and a controller operatively connected to at least one sensor and the actuator, the controller having a processing unit and a computer-readable medium operatively connected to the processing unit and containing instructions for: receiving a signal indicative of a pressure difference between opposite sides of the flow restrictor; and powering the actuator to move the flow restrictor with the actuator from a first position to a second position offset from the first position as a function of the pressure difference.
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公开(公告)号：US11319897B2
公开(公告)日：2022-05-03
申请号：US16834180
申请日：2020-03-30
Applicant: HANWHA AEROSPACE CO., LTD. , Pratt & Whitney Canada Corp.
Inventor： Young Jung Joo , Hee Yoon Chung , Eray Akcayoz
Abstract: Provided are an exhaust duct, an exhaust duct assembly, and an aircraft using the exhaust duct. The exhaust duct has a structure that enables combustion gas to be diverged and discharged from an inlet end to a first outlet end and a second outlet end at respective sides of the exhaust duct. The exhaust duct includes a first housing including a first body forming an outer wall of the inlet end, and further includes second bodies respectively extending on respective sides from the first body and respectively forming the first outlet end and the second outlet end; a second housing spaced apart from the first body, forming an inner wall of the inlet end, and extending curvedly toward the second bodies; and a connection housing connecting the first housing to the second housing and including at least one recess portion recessed toward the inlet end.
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公开(公告)号：US20250116229A1
公开(公告)日：2025-04-10
申请号：US18377180
申请日：2023-10-05
Applicant: Pratt & Whitney Canada Corp.
Inventor： Eray Akcayoz , Mark Cunningham , Roberto Marrano , Corentin Brette
Abstract: A system is provided for an aircraft. This aircraft system includes an aircraft engine, an inlet guard and an actuation system. The aircraft engine has a flowpath projecting into the aircraft engine from an airflow inlet. The inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen, a second screen and a plurality of perforations. The first screen is adjacent and overlaps the second screen. The perforations project through the inlet guard and are formed by the first screen and the second screen. The actuation system is configured to move the first screen along the second screen. The movement of the first screen along the second screen changes a geometry of each of the perforations.
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公开(公告)号：US20250115366A1
公开(公告)日：2025-04-10
申请号：US18377186
申请日：2023-10-05
Applicant: Pratt & Whitney Canada Corp.
Inventor： Mark Cunningham , Eray Akcayoz , Roberto Marrano , Corentin Brette
IPC: B64D33/02
Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine, a flowpath and an inlet guard. The gas turbine engine includes a compressor section. The flowpath projects longitudinally into the gas turbine engine from an airflow inlet and longitudinally through the compressor section. The inlet guard extends across the flowpath longitudinally upstream of the compressor section. The inlet guard extends circumferentially about an axis. The inlet guard includes a first screen and a second screen. The first screen includes a plurality of first perforations with a first perforation size. The second screen is circumferentially adjacent the first screen about the axis. The second screen includes a plurality of second perforations with a second perforation size that is different than the first perforation size.
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