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公开(公告)号：US20250067195A1
公开(公告)日：2025-02-27
申请号：US18238315
申请日：2023-08-25
Applicant: Pratt & Whitney Canada Corp.
Inventor： Dikran Mangardich , Paul Stone
IPC: F01D5/12
Abstract: A test rotor blade for an aircraft engine bladed rotor includes a blade body. The blade body extends between and to a leading edge and a trailing edge. The blade body forms a first side surface and a second side surface. The blade body forms a leading-edge pocket at the leading edge, a trailing-edge pocket at the trailing edge, and a hole extending through the blade body from the leading-edge pocket to the trailing edge pocket. The blade body includes a first side wall and a second side wall. The first side wall has a first wall thickness extending between and to the first side surface and the hole. The second side wall has a second wall thickness extending between and to the second side surface and the hole. The second wall thickness is 0.4 to 0.9 times the first wall thickness.
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公开(公告)号：US12234768B2
公开(公告)日：2025-02-25
申请号：US18346572
申请日：2023-07-03
Applicant: Pratt & Whitney Canada Corp.
Inventor： Daniel Alecu , Dave Menheere
Abstract: A gas turbine engine includes a turbine for driving a shaft to in turn drive a rotor. A combustor receives compressed air, and combusts the compressed air. The shaft is supported by at least one bearing. An oil delivery system is associated with the at least one bearing including an oil scoop rotating with the at least one shaft and a stationary oil jet provided with a source of lubricant. A mixed fluid chamber is within the shaft. The mixed fluid chamber is connected to an air exit. There further is an oil chamber radially outward of the mixed fluid chamber. The oil chamber is connected to the at least one bearing.
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公开(公告)号：US12228052B2
公开(公告)日：2025-02-18
申请号：US18354714
申请日：2023-07-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Dikran Mangardich , Krishna Prasad Balike
Abstract: An integrally bladed rotor for an aircraft engine includes a hub and a circumferential array of blades extending from the hub. Each blade has an airfoil extending from a gaspath side of a platform provided at a periphery of the hub. The platform has a radial thickness T. An edge of the airfoil is disposed at an axial distance L1 from an adjacent axial edge of the platform. A projection extends radially inwardly from an interior side of the platform opposite to the gaspath side. The projection has an axial thickness t, a radial height h from the interior side of the platform, and an axial distance L2 from the adjacent axial edge of the platform. T is a radial thickness of the platform at an axial location of the projection, and 0 . 2 ≤ T t ≤ 5 ; 1 ≤ h t ≤ 10 ; and 0 ≤ L 2 L 1 ≤ 1 0 .
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公开(公告)号：US12221971B1
公开(公告)日：2025-02-11
申请号：US18525046
申请日：2023-11-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere , Andrew Marshall
Abstract: A compressor has: a rotor and a shroud having a internal and external sides and an air outlet; an annular case mounted to the external side and enclosing a plenum, the annular case having inner and outer sides and defining an aperture; a valve mounted to the annular case at the aperture and having: a support secured to the annular case and defining a seat surrounding a bleed passage, the seat located on the outer side, the support defining a guiding aperture, and a valve member having a head and a stem slidably received within the guiding aperture, the valve member having a closed position and an open position, the head abutting the valve seat in the closed position and offset from the valve seat in the open position; and an actuator engaged to the valve member for moving the valve member between the closed position and the open position.
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公开(公告)号：US12221221B2
公开(公告)日：2025-02-11
申请号：US18441405
申请日：2024-02-14
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Mert Cevik , James Robert Jarvo , Keith Morgan , Elizabeth Gioia
Abstract: A method of operating a hybrid engine for an aircraft, the hybrid engine having a thermal engine and an electric motor. The method includes verifying, using an engine control unit of the hybrid engine, that a selected power level is under a predetermined threshold for operation of the hybrid engine in a sub-idle hybrid mode. The method further includes operating the hybrid engine in the sub-idle hybrid mode, using the engine control unit, by controlling the thermal engine to operate in a standby mode, and by controlling the electric motor to operate in an active mode wherein the electric motor provides a majority of a propulsive power to the aircraft, wherein in the standby mode the thermal engine operates in a sub-idle condition to provide at most minimal propulsive power to the aircraft.
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Patent Agency Ranking
公开(公告)号：US20250045908A1
公开(公告)日：2025-02-06
申请号：US18228441
申请日：2023-07-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Alireza Gharagozloo , Roja Tabar
Abstract: An assembly for recording rotor blade replacement data for a bladed rotor includes an imaging device and a processing system. The imaging device is configured to capture image data for the bladed rotor including a plurality of rotor blades. The processing system is configured to identify each of the plurality of rotor blades installed on the bladed rotor in pre-repair image data of the captured image data and store a pre-repair position of each of the identified plurality of rotor blades installed on the bladed rotor in the pre-repair image data, identify each of the plurality of rotor blades installed on the bladed rotor in post-repair image data and store a post-repair position of each of the identified plurality of rotor blades installed on the bladed rotor in the post-repair image data, and identify at least one replaced rotor blade installed on the bladed rotor in the post-repair image data using the pre-repair image data and the post-repair image data.
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公开(公告)号：US20250042559A1
公开(公告)日：2025-02-06
申请号：US18228986
申请日：2023-08-01
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Meisels , Richard Freer
Abstract: A method of and system for operating a hybrid-electric propulsion system is provided. The system has a thermal engine and an electrical propulsion subsystem having a plurality of components. The method includes providing a set of original engine ratings for operating the hybrid-electric propulsion system, the original engine ratings are based on one or more first performance/capability parameters of an original electrical propulsion subsystem component; replacing the original component with an alternative component, the alternative component having one or more second performance/capability parameters, wherein the second performance/capability parameters are different from the first performance/capability parameters; producing a set of alternative engine ratings based on the second performance/capability parameters; and operating the hybrid-electric propulsion system using the set of alternative engine ratings.
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公开(公告)号：US20250027523A1
公开(公告)日：2025-01-23
申请号：US18354800
申请日：2023-07-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Alexandre TASSE ROY
IPC: F16B31/02
Abstract: An adjustable torque limiting fastener has a shank extending along an axis from a proximal end to a distal end. The fastener has a head at the proximal end of the shank. A torque limiter is integrated between the head and the shank. The torque limiter is operable to rotatably decouple the head from the shank when a torque applied to the head exceed a maximum torque. The maximum torque is set by a spring plunger integrated to the head for friction engagement with the proximal end of the shank.
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公开(公告)号：US20250027456A1
公开(公告)日：2025-01-23
申请号：US18354918
申请日：2023-07-19
Applicant: Pratt & Whitney Canada Corp.
Inventor： Mehdi Abedinpour Fallah
Abstract: A disclosed method for controlling an aircraft propulsion system includes modeling dynamics of a propulsion system, formulating a problem for achieving the target output as system of linear equations constrained by physical limits of the propulsion system, and generating a solution to the system of linear equations with a singular value decomposition solver module that utilizes Jacobi's singular value decomposition. A control command is generated based on the solution that includes instructions for adjusting a propulsion system operating parameter toward a target output and the propulsion system us operated according to the control command.
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公开(公告)号：US12203410B1
公开(公告)日：2025-01-21
申请号：US18351653
申请日：2023-07-13
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Jeremie Barberger , Raphael Paquet , Vincent Savaria
Abstract: A housing assembly for a rotary engine, has: a rotor housing having a peripheral inner face, a first face and a second face; a first side housing secured to the first side and defining a first inner side face fac; and a second side housing secured to the second side and defining a second inner side face, the rotor cavity bounded axially between the first side housing and the second side housing, one or more of the rotor housing, the first side housing, and the second side housing having: a main body made of a base material; and an external layer made of an alloy including the base material, a wear-resistance of the alloy greater than that of the base material, the external layer defining one or more of the first face, the second face, the first inner side face, and the second inner side face.
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