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公开(公告)号：US12055058B2
公开(公告)日：2024-08-06
申请号：US17828652
申请日：2022-05-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Michael Fryer , Martin Dobson , Oleg Iskra , Marc Lavoie , Ivan Sidorovich Paradiso , Louis Duranleau-Hendrickx , Domenico Di Florio
IPC: F01D25/24
CPC classification number: F01D25/24 , F05D2220/32 , F05D2240/14
Abstract: An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a case, a housing, a component and a spring element. The case includes an aperture that extends axially along an axis through the case. The housing is attached to the case with a cavity formed by and axially between the housing and the case. The component includes a base and a projection. The base is disposed within the cavity and axially engages the case. The projection projects out from the base and axially through the aperture. The spring element is disposed within the cavity. The spring element is compressed axially between and engages the base and the housing.
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公开(公告)号：US11794914B2
公开(公告)日：2023-10-24
申请号：US17379285
申请日：2021-07-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ivan Sidorovich Paradiso , Daniel Alecu
CPC classification number: B64D27/24 , B64D27/023 , B60L2200/10 , B64D2027/026 , B64D2041/002 , B64D2221/00 , F01D13/02 , F01D15/10 , F02C3/30 , F05D2220/50 , F05D2220/76 , F05D2270/09 , H02J2310/44
Abstract: Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.
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公开(公告)号：US11965463B2
公开(公告)日：2024-04-23
申请号：US17176643
申请日：2021-02-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ivan Sidorovich Paradiso , Daniel Alecu
CPC classification number: F02C7/18 , F02C7/14 , F05D2260/213 , F05D2260/232 , F05D2260/31 , F05D2260/606 , F05D2260/98
Abstract: A fluid cooler for installation in a bypass duct of a turbofan gas turbine engine and associated methods are provided. The fluid cooler includes an inlet duct, a heat exchanger and an outlet duct. The inlet duct includes an inlet protruding into the bypass duct to receive a portion of the bypass air into the inlet duct. The heat exchanger is in fluid communication with the inlet duct. The heat exchanger facilitates heat transfer between a fluid and the portion of bypass air received into the inlet duct. The heat exchanger defines a general flow direction for the portion of bypass air that is different from the main flow direction of bypass air inside the bypass duct. The outlet duct conveys the portion of bypass air from the heat exchanger back to the bypass duct.
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公开(公告)号：US11802509B2
公开(公告)日：2023-10-31
申请号：US17358196
申请日：2021-06-25
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Martin Dobson , Oleg Iskra , Michael Fryer , Marc Lavoie , Ivan Sidorovich Paradiso , Louis Duranleau-Hendrickx , Domenico Di Florio
CPC classification number: F02C7/05 , F02C9/18 , F05D2220/323 , F05D2260/607
Abstract: Methods and systems for filtering pressurized air used to control a compressor bleed valve of a gas turbine engine are provided. One method comprises receiving the pressurized air in a conduit via an inlet of the conduit, releasing a first portion of the pressurized air out of the conduit via an outlet of the conduit, releasing a second portion of the pressurized air from the conduit via a port disposed between the inlet and the outlet of the conduit, directing the second portion of the pressurized air from the port to a filter along an upward flow path, filtering the second portion of the pressurized air using the filter, and directing the second portion of the pressurized air from the filter toward the compressor bleed valve.
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公开(公告)号：US12123305B2
公开(公告)日：2024-10-22
申请号：US17993517
申请日：2022-11-23
Applicant: Pratt & Whitney Canada Corp.
Inventor： Daniel Alecu , Ivan Sidorovich Paradiso
CPC classification number: F01D11/003 , F01D5/025 , F01D5/30 , F05D2220/32 , F05D2240/20 , F05D2240/55
Abstract: A gas turbine engine rotor assembly is provided that includes a shaft, a rotor, and a seal assembly. The seal assembly is configured to seal between a first and second rotor compartments on opposite sides of the seal assembly. The seal assembly includes a seal groove and a split piston ring seal. The split piston ring seal is configured such that air in the first rotor compartment at P1 produces a radial force acting on the split piston ring seal, and air in the second rotor compartment at P2 produces a second force acting on the split piston ring seal, wherein the second force is directed radially inward and the first force is directed radially outward, and the second force is greater than the first force.
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Patent Agency Ranking
公开(公告)号：US11852073B2
公开(公告)日：2023-12-26
申请号：US17389450
申请日：2021-07-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Martin Dobson , Oleg Iskra , Michael Fryer , Marc Lavoie , Ivan Sidorovich Paradiso , Louis Duranleau-Hendrickx , Domenico Di Florio , Tibor Urac
CPC classification number: F02C6/08 , B01D45/04 , F05D2260/605 , F05D2260/607
Abstract: An orifice pack is provided for delivering pressurized air to a compressor bleed valve of a gas turbine engine. The orifice pack has a diffusion chamber in serial flow communication with a tapering passage and a first outlet passage for venting a first portion of the pressurized air from the diffusion chamber. A second outlet passage branches off from the diffusion chamber at an axial location between the inlet and the tapering passage. The second outlet passage is fluidly connected to the compressor bleed valve for directing a second portion of the pressurized air from the diffusion chamber to the compressor bleed valve.
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公开(公告)号：US11300002B2
公开(公告)日：2022-04-12
申请号：US16707358
申请日：2019-12-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ivan Sidorovich Paradiso , Daniel Alecu
Abstract: A duct for a gas turbine engine, the duct has a wall defining a flow passage for an airflow, the wall defining a baseline surface, the duct comprising an off-take port for drawing a portion of the airflow out of the duct, the off-take port including a projected portion projecting away from the baseline surface into the flow passage, a conduit opening defined within the projected portion for receiving the portion of the airflow, and an off-take conduit communicating with the conduit opening for directing the portion of the airflow away from the duct, the projected portion having a hump upstream of the conduit opening relative to a direction of the airflow and a scoop downstream of the opening relative to the direction of the airflow.
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公开(公告)号：US10968827B2
公开(公告)日：2021-04-06
申请号：US15278477
申请日：2016-09-28
Applicant: Pratt & Whitney Canada Corp.
Inventor： Daniel Alecu , Ivan Sidorovich Paradiso
Abstract: A fan nose cone is disclosed for impeding icing and recovering momentum in a gas turbine engine. The fan nose cone comprises: an axially symmetric shell having a convex external surface and an internal surface, the shell having an opening in a forward end of the shell for communication with a source of heated pressurized air; and an axially symmetric deflector disposed forward of the opening, the deflector being configured to direct heated pressurized air exiting from the opening radially outwardly to flow in a downstream direction over the convex external surface of the shell during operation. The shell of the fan nose cone may have a rearward circumferential vent in communication with the source of heated pressurized air for directing heated pressurized from the vent in a radially outward and downstream direction toward the fan blade platforms.
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公开(公告)号：US20230407766A1
公开(公告)日：2023-12-21
申请号：US17828652
申请日：2022-05-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Michael Fryer , Martin Dobson , Oleg Iskra , Marc Lavoie , Ivan Sidorovich Paradiso , Louis Duranleau-Hendrickx , Domenico Di Florio
IPC: F01D25/24
CPC classification number: F01D25/24 , F05D2240/14 , F05D2220/32
Abstract: An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a case, a housing, a component and a spring element. The case includes an aperture that extends axially along an axis through the case. The housing is attached to the case with a cavity formed by and axially between the housing and the case. The component includes a base and a projection. The base is disposed within the cavity and axially engages the case. The projection projects out from the base and axially through the aperture. The spring element is disposed within the cavity. The spring element is compressed axially between and engages the base and the housing.
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公开(公告)号：US11639689B2
公开(公告)日：2023-05-02
申请号：US17478132
申请日：2021-09-17
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Martin Dobson , Oleg Iskra , Michael Fryer , Marc Lavoie , Ivan Sidorovich Paradiso , Louis Duranleau-Hendrickx , Domenico Di Florio , Tibor Urac
Abstract: The gas turbine engine can have a pneumatic actuator; an intake device secured to a gas path wall delimiting the gas path, the intake device having a tubular body protruding from the gas path wall into the gas path and an inlet aperture formed in the tubular body, the inlet aperture spaced-apart from the gas path wall and facing downstream relative a flow orientation of the gas path, the intake device having an internal conduit extending from the inlet aperture, along the tubular body, to an outlet across the gas path wall; and a fluid line fluidly connecting the outlet of the intake device to the pneumatic actuator.
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