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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：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：US11279465B2
公开(公告)日：2022-03-22
申请号：US16036917
申请日：2018-07-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Joseph Ernesto Marone , Olivier Basse , Martin Dobson , Martin Clermont , Marc Lavoie
Abstract: A blade angle feedback ring assembly for an aircraft engine propeller having adjustable angle blades is provided. The feedback ring assembly comprises a feedback ring coupled to rotate with the propeller, the engine configured such that a first electrically-conductive path is defined between the propeller and the engine via the feedback ring, and an electric current conduction element provided between the propeller and the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first path, the second electrically-conductive path configured with a lower electrical resistance to conduction between the propeller and the engine than the first electrically-conductive path.
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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：US11780561B2
公开(公告)日：2023-10-10
申请号：US17326993
申请日：2021-05-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Joseph Ernesto Marone , Ella Yakobov , Ian Farrell , Olivier Basse , Martin Dobson , Martin Clermont , Marc Lavoie
CPC classification number: B64C11/06 , B64C11/301 , B64C11/34 , B64D45/02
Abstract: There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.
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Patent Agency Ranking
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：US20210284322A1
公开(公告)日：2021-09-16
申请号：US17326993
申请日：2021-05-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Joseph Ernesto Marone , Ella Yakobov , Ian Farrell , Olivier Basse , Martin Dobson , Martin Clermont , Marc Lavoie
Abstract: There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.
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公开(公告)号：US11046422B2
公开(公告)日：2021-06-29
申请号：US16036930
申请日：2018-07-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Joseph Ernesto Marone , Ella Yakobov , Ian Farrell , Olivier Basse , Martin Dobson , Marc Lavoie
Abstract: A blade angle feedback ring assembly for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle is provided. A feedback ring is coupled to the propeller to rotate therewith and to move along a longitudinal axis with adjustment of the blade angle. A plurality of rods are coupled to the feedback ring and extending along a direction substantially parallel to the longitudinal axis, the rods configured to support the feedback ring for longitudinal sliding movement along the longitudinal axis with adjustment of the blade angle. At least one shielding element is provided between the feedback ring and the propeller for shielding the feedback ring from electromagnetism.
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公开(公告)号：US20200017234A1
公开(公告)日：2020-01-16
申请号：US16036930
申请日：2018-07-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Joseph Ernesto Marone , Ella Yakobov , Ian Farrell , Olivier Basse , Martin Dobson , Marc Lavoie
Abstract: A blade angle feedback ring assembly for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle is provided. A feedback ring is coupled to the propeller to rotate therewith and to move along a longitudinal axis with adjustment of the blade angle. A plurality of rods are coupled to the feedback ring and extending along a direction substantially parallel to the longitudinal axis, the rods configured to support the feedback ring for longitudinal sliding movement along the longitudinal axis with adjustment of the blade angle. At least one shielding element is provided between the feedback ring and the propeller for shielding the feedback ring from electromagnetism.
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