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    AIR SYSTEM SWITCHING SYSTEM TO ALLOW AERO-ENGINES TO OPERATE IN STANDBY MODE
    1.
    发明公开
    AIR SYSTEM SWITCHING SYSTEM TO ALLOW AERO-ENGINES TO OPERATE IN STANDBY MODE 审中-公开

    公开(公告)号：EP3715248A1

    公开(公告)日：2020-09-30

    申请号：EP20165886.1

    申请日：2020-03-26

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： NG, Kevin ,  VINSKI, Johnny ,  LOGAN, Adam

    IPC: B64C27/08 ,  B64D15/04 ,  F02C6/02 ,  B64D13/06 ,  B64D31/06

    Abstract: A method of operating a multi-engine aircraft (1, Fig. 1a) having two or more gas turbine engines (10, Fig. 1b) includes operating a first engine in a powered mode to provide motive power to the aircraft (1), and, in flight, operating a second engine in either a powered mode to provide motive power to the aircraft (1) or in a standby mode to provide substantially no motive power to the aircraft (1). When operating the second engine in the powered mode, pressurized air is bled from a first bleed location (19) of a compressor (9) of the second engine. When operating the second engine in the standby mode, pressurized air is bled from a second bleed location (21) of the compressor (9) of the second engine and supplying the pressurized air to a bleed air system of the second engine. The second bleed location (21) is downstream of the first bleed location (19) within the compressor (9) of the second engine.

    ROTARY ENGINE HOUSING WITH A SEAL ASSEMBLY
    2.
    发明公开
    ROTARY ENGINE HOUSING WITH A SEAL ASSEMBLY 审中-公开

    公开(公告)号：EP4491846A2

    公开(公告)日：2025-01-15

    申请号：EP24188481.6

    申请日：2024-07-12

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： VINSKI, Johnny ,  BOUSQUET, Michel ,  SIMONEAU, Jean-Philippe ,  GAGNON-MARTIN, David ,  SAVARIA, Vincent ,  VILLENEUVE, Bruno ,  BERUBE, Stephane ,  ROY, Frederic ,  BOLDUC, Sebastien

    IPC: F01C1/10 ,  F01C1/22 ,  F01C19/00 ,  F01C21/06

    Abstract: An engine housing (46) for an aircraft rotary engine includes a rotor housing (52) and a side housing assembly (54). The rotor housing (52) includes a rotor housing body (56). The rotor housing body (56) extends about an axis (28) to form a rotor cavity (62) of the engine housing (46). The rotor housing body (56) extends between and to a first axial end (58) and a second axial end (60). The side housing assembly (54) includes a side housing body (82), a side plate (84), and a seal assembly (86). The side housing body (82) is disposed at the first axial end (58). The side plate (84) includes an inner side (106), an outer side (108), and a perimeter edge (110) extending from the inner side (106) to the outer side (108). The seal assembly includes a support ring (112) and a spacer (114). The support ring (112) and the spacer (114) extend about the axis (28). The support ring (112) is mounted to the perimeter edge (110) by a braze joint (144). The spacer (114) extends between and to a first axial spacer end (136) and a second axial spacer end. The first axial spacer end (136) is disposed at the support ring (112) and the outer side (108).

    MULTI-SOURCE AIR SYSTEM AND SWITCHING VALVE ASSEMBLY THEREFOR
    3.
    发明公开
    MULTI-SOURCE AIR SYSTEM AND SWITCHING VALVE ASSEMBLY THEREFOR 审中-公开

    公开(公告)号：EP3628840A1

    公开(公告)日：2020-04-01

    申请号：EP19199680.0

    申请日：2019-09-25

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： VINSKI, Johnny

    IPC: F02C3/08 ,  B64D13/00 ,  F01D17/14 ,  F02C6/08 ,  F02C9/18

    Abstract: A method of operating a gas turbine engine (10) having a high pressure compressor (42) and a secondary air system (50) includes, when the gas turbine engine (10) is operating in a first power range, providing a first bleed source for the secondary air system (50) by bleeding air from a first bleed location, providing bleed air at a first pressure, proximate to an outlet of the high pressure compressor (42). When the gas turbine engine (10) is operating in a second power range, higher than the first power range, the method includes providing a second bleed source by bleeding air from both a second bleed location and a third bleed location. The second and third bleed locations, respectively providing bleed air at second and third pressures, are both disposed upstream of the first bleed location within the gas turbine engine (10). The second and third pressures are different from the first pressure.

    INTERNAL COMBUSTION ENGINE WITH COATED IGNITION SYSTEM COMPONENT(S)
    5.
    发明公开
    INTERNAL COMBUSTION ENGINE WITH COATED IGNITION SYSTEM COMPONENT(S) 审中-公开

    公开(公告)号：EP4502351A2

    公开(公告)日：2025-02-05

    申请号：EP24192441.4

    申请日：2024-08-01

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： SAVARIA, Vincent ,  GAUVREAU, Jean-Gabriel ,  VINSKI, Johnny

    IPC: F02B19/10 ,  F02B19/12 ,  F02B53/12 ,  F02B55/14 ,  F02B77/02 ,  F02B77/04 ,  F02B19/00

    Abstract: During a manufacturing method, a protective coating (112) is applied to a first chamber surface (114) of a first component (102) to provide a coated first chamber surface (114') and to a second chamber surface (116) of a second component (104) to provide a coated second chamber surface (116'). The second component (104) is configured with the first component (102) to provide a pilot chamber structure (68). The pilot chamber structure (68) includes a pilot chamber (74), a pilot aperture (76), a fuel aperture (92) and an ignitor aperture (94). The pilot chamber (74) is formed by the coated first chamber surface (114') and the coated second chamber surface (116') within the pilot chamber structure (68). The pilot aperture (76) projects into the first component (102) from a distal end of the pilot chamber structure (68) to the pilot chamber (74). The fuel aperture (92) projects into the pilot chamber structure (68) to the pilot chamber (74). The ignitor aperture (94) projects into the pilot chamber structure (68) to the pilot chamber (74).

    ROTARY ENGINE WITH SEAL HAVING ELASTOMERIC MEMBER AND SHIELD
    6.
    发明公开
    ROTARY ENGINE WITH SEAL HAVING ELASTOMERIC MEMBER AND SHIELD 审中-公开

    公开(公告)号：EP4435229A1

    公开(公告)日：2024-09-25

    申请号：EP24165818.6

    申请日：2024-03-25

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： BOUSQUET, Michel ,  VINSKI, Johnny

    IPC: F01C1/22 ,  F01C19/00 ,  F01C21/06 ,  F01C21/10 ,  F16J15/02

    CPC classification number: F01C1/22 ,  F01C21/108 ,  F01C21/06 ,  F01C19/005 ,  F05C2251/0420130101 ,  F16J15/065 ,  F16J15/104 ,  F16J15/102

    Abstract: A housing assembly (12) for a rotary engine (10), has: a rotor housing (18) extending around an axis, the rotor housing (18) having an inner face facing a rotor cavity (20); side housings (11) secured to opposite sides of the rotor housing (18), the rotor cavity (20) bounded axially between the side housings (11); and a seal (70) received within a groove (16B) at an interface between the rotor housing (18) and a first side housing, the groove (16B) annularly extending around the axis, located outwardly of the inner face, and overlapping a peripheral section (14A) of the first side housing, the seal (70) having: an elastomeric member (71) compressed between the peripheral section (14A) and the rotor housing (18); and a shield (72) disposed inwardly of the elastomeric member (71), the shield (72) having a melting point above a temperature of combustion gases, the shield (72) in contact with both of the peripheral section (14A) of the first side housing and the rotor housing (18).

    ROTARY ENGINE HOUSING WITH A SEAL ASSEMBLY
    8.
    发明公开
    ROTARY ENGINE HOUSING WITH A SEAL ASSEMBLY 审中-公开

    公开(公告)号：EP4491847A2

    公开(公告)日：2025-01-15

    申请号：EP24188442.8

    申请日：2024-07-12

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： VINSKI, Johnny ,  SIMONEAU, Jean-Philippe ,  GAGNON-MARTIN, David ,  SAVARIA, Vincent ,  VILLENEUVE, Bruno ,  BERUBE, Stephane ,  ROY, Frederic ,  BOLDUC, Sebastien

    IPC: F01C1/22 ,  F01C21/10

    Abstract: An engine housing (46) includes a rotor housing and a side housing assembly (54). The rotor housing (52) includes a rotor housing body (56). The rotor housing body (56) extends about an axis (28) to form a rotor cavity (62) of the engine housing (46). The rotor housing body (56) extends between and to a first axial end (58) and a second axial end (60). The side housing assembly (54) includes a side housing body (82), a side plate (84), and a seal assembly (86). The side housing body (82) is disposed at the first axial end (58). The side plate is disposed axially between the rotor housing body (56) and the side housing body (82). The side plate (84) includes an inner side (106), an outer side (108), and a perimeter edge (110). The seal assembly (86) includes a support ring (112) and a sealing ring (114). The support ring (112) is disposed at the perimeter edge (110) and the first axial end (58). The support ring (112) circumscribes the side plate (84). The sealing ring (114) extends between and to a first axial sealing ring end (136) and a second axial sealing ring end (138). The first axial sealing ring end (136) is disposed at the support ring (112) and the outer side (108).

    INTERNAL COMBUSTION ENGINE WITH CERAMIC PILOT CHAMBER COMPONENT(S)
    9.
    发明公开
    INTERNAL COMBUSTION ENGINE WITH CERAMIC PILOT CHAMBER COMPONENT(S) 审中-公开

    公开(公告)号：EP4450784A1

    公开(公告)日：2024-10-23

    申请号：EP24170893.2

    申请日：2024-04-17

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： GAUVREAU, Jean-Gabriel ,  VINSKI, Johnny

    IPC: F02B19/10 ,  F02B19/16 ,  F02B53/12

    Abstract: An assembly for a powerplant includes a housing (34), a primary fuel injector (38) and an ignition system (40). The housing (34) forms a combustion volume (66) within the housing (34). The primary fuel injector (38) is configured to inject primary fuel into the combustion volume (66). The ignition system (40) is configured to ignite the primary fuel within the combustion volume (66). The ignition system (40) includes a pilot fuel injector (70), a pilot ignitor (72), a pilot chamber (74), a first component (78) and a second component (80). The pilot fuel injector (70) is configured to inject pilot fuel into the pilot chamber (74). The pilot ignitor (72) is configured to ignite the pilot fuel within the pilot chamber (74). The pilot chamber (74) is fluidly coupled with the combustion volume (66) through an aperture in the first component (78). The pilot chamber (74) is formed by and disposed between the first component (78) and the second component (80). The first component (78) is configured from or otherwise include a ceramic.

    ROTARY ENGINE WITH FLOATING SIDE PLATES
    10.
    发明公开
    ROTARY ENGINE WITH FLOATING SIDE PLATES 审中-公开

    公开(公告)号：EP4428336A1

    公开(公告)日：2024-09-11

    申请号：EP24162386.7

    申请日：2024-03-08

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： SIMONEAU, Jean-Philippe ,  VINSKI, Johnny ,  GAGNON-MARTIN, David ,  BOLDUC, Sebastien

    IPC: F01C1/22 ,  F01C21/10

    CPC classification number: F01C1/22 ,  F01C21/108

    Abstract: A rotary internal combustion engine (20) includes a rotor housing (22) having a peripheral wall (24) circumscribing a rotor cavity (28) and a rotor (26) disposed within the rotor cavity (28). A side housing (46) is secured to the rotor housing (22) and a plate (48) defines a seal running surface (45) for the rotor (26). The plate (48) is disposed between a portion of the side housing (46) and the rotor housing (22) and at least one shim (54) is disposed between the plate (48) and the side housing (46) for spacing the plate (48) apart from contact with the side housing (46).

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