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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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Patent Agency Ranking
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：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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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：US11719165B2
公开(公告)日：2023-08-08
申请号：US17453387
申请日：2021-11-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Damien Le Pape , Guorong Yan , Mark Cunningham , Philippe Beauchesne-Martel , Oleg Iskra , Richard Ivakitch
IPC: F02C7/32
CPC classification number: F02C7/32 , F05D2220/323
Abstract: An aircraft engine comprises an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine, to an outlet within the aircraft engine. At least one strut has a leading edge and a trailing edge and extends across at least part of the air inlet duct. The at least one strut has a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage.
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