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1.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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公开(公告)号：US12241412B1
公开(公告)日：2025-03-04
申请号：US18481705
申请日：2023-10-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Roberto Marrano , Mark Cunningham , Eray Akcayoz , Corentin Brette
Abstract: A system for an aircraft includes an aircraft engine having a central axis with a flowpath projecting into the aircraft engine from an airflow inlet. An inlet plenum at the airflow inlet extends between a front wall and a rear wall along the central axis. An inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen extending circumferentially about the central axis. The first screen has a first screen axial width L1 extending from the front wall to the rear wall. The inlet guard further includes a second screen extending at least partially circumferentially about the central axis. The second screen is disposed radially outward of the first screen and axially overlaps the first screen. The second screen has a second screen axial width L2 less than the first screen axial width L1.
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3.发明授权公开(公告)号：US11994064B2
公开(公告)日：2024-05-28
申请号：US17977722
申请日：2022-10-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Mark Cunningham , Eray Akcayoz , Raja Ramamurthy , Roberto Marrano
IPC: F02C7/042
CPC classification number: F02C7/042 , F05D2220/323 , 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：US11965460B1
公开(公告)日：2024-04-23
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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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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Patent Agency Ranking
公开(公告)号：US11536196B2
公开(公告)日：2022-12-27
申请号：US17356106
申请日：2021-06-23
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Roberto Marrano , François Bisson
Abstract: An inertial particle separator (IPS) has: a main duct having an inlet fluidly connected to an environment outside of the aircraft engine, the main duct having a first segment and a second segment, the first segment extending longitudinally away from the inlet and vertically toward an elbow, the second segment extending vertically and longitudinally away from the elbow, the main duct having a concave side and a convex side; two inlet ducts extending from the concave side of the main duct, the two inlet ducts extending laterally away from one another and vertically away from the elbow; and a bypass duct communicating with the main duct, an intersection between the bypass duct and the main duct defining a splitter, the bypass duct extending along the longitudinal direction and laterally between the two inlet ducts, the two inlet ducts and the bypass duct extending vertically away from one another.
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公开(公告)号：US11066996B2
公开(公告)日：2021-07-20
申请号：US16202827
申请日：2018-11-28
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Roberto Marrano , Francois Bisson
Abstract: There is disclosed an inertial particle separator communicating with an engine inlet. The inertial particle separator has: a main duct body; a bypass duct; and a splitter defined by an intersection of the main duct and the bypass duct. The main duct and the bypass duct having particular geometric characteristics. A method of separating particles via inertia in an aircraft engine inlet is also provided.
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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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10.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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