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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：US20250154869A1
公开(公告)日：2025-05-15
申请号：US18388285
申请日：2023-11-09
Applicant: Pratt & Whitney Canada Corp.
Inventor： Yashiva Dorsamy , Philippe Boyer , Jasrobin Grewal , Prakul Mittal , Domenico Di Florio
Abstract: An apparatus is provided for a gas turbine engine. This apparatus includes a bladed rotor rotatable about an axis. The bladed rotor includes a rotor disk and a plurality of rotor blades projecting radially out from the rotor disk. The bladed rotor are divided into a plurality of circumferential sectors about the axis. Each of the circumferential sectors have a common circumferential length about the axis. Each of the circumferential sectors includes a subset of two or more of the rotor blades. The circumferential sectors include a first sector and a second sector. The first sector has a first rotor configuration. The second sector has a second rotor configuration that is different than the first rotor configuration.
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公开(公告)号：US20250020069A1
公开(公告)日：2025-01-16
申请号：US18349524
申请日：2023-07-10
Applicant: Pratt & Whitney Canada Corp.
Inventor： Tomasz Olech , Morgan Demenois , Negin Abaeian , Domenico Di Florio , Raghavendra Pendyala
Abstract: A gas turbine engine includes a compressor section, a combustor and a turbine section. At least one case surrounds at least one of the compressor section and the turbine section. The case is formed from sheet metal and includes a case wall and at least one potential displacement location due to vibration. At least one retaining ring is assembled to the case and biased against the case wall at the at least one potential displacement location to dampen vibration.
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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：US12264593B1
公开(公告)日：2025-04-01
申请号：US18388305
申请日：2023-11-09
Applicant: Pratt & Whitney Canada Corp.
Inventor： Philippe Boyer , Prakul Mittal , Yashiva Dorsamy , Jasrobin Grewal , Domenico Di Florio
Abstract: An assembly is provided for a gas turbine engine. This assembly includes an integrally bladed rotor and a damper. The integrally bladed rotor is rotatable about an axis. The integrally bladed rotor includes a plurality of rotor blades and a rotor disk. The rotor blades are arranged circumferentially around and project radially out from the rotor disk. The rotor disk includes a flange, a groove and a plurality of slots. The groove extends circumferentially around the axis within the flange. The groove projects radially into the flange from an inner side of the flange. The slots are arranged circumferentially about the axis along the groove. Each of the slots projects radially into the flange from the inner side of the flange. The damper is mounted to the rotor disk and seated within the groove.
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Patent Agency Ranking
公开(公告)号：US20250012204A1
公开(公告)日：2025-01-09
申请号：US18799108
申请日：2024-08-09
Applicant: Pratt & Whitney Canada Corp.
Inventor： Morgan Demenois , Negin Abaeian , Tomasz Olech , Raghavendra Pendyala , Domenico Di Florio
Abstract: A gas turbine engine under this disclosure could be said to include a compressor section, a combustor and a turbine section. At least one casing surrounds at least one of the compressor and turbine section. The at least one casing is formed of sheet metal, and has at least one potential peak displacement point due to vibration across a speed range of the at least one of the compressor and turbine section. A stiffening element is fixed to a wall of the casing at the at least one potential peak displacement point. A method is also disclosed.
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公开(公告)号：US12158076B1
公开(公告)日：2024-12-03
申请号：US18348915
申请日：2023-07-07
Applicant: Pratt & Whitney Canada Corp.
Inventor： Morgan Demenois , Negin Abaeian , Tomasz Olech , Raghavendra Pendyala , Domenico Di Florio
Abstract: A gas turbine engine under this disclosure could be said to include a compressor section, a combustor and a turbine section. At least one casing surrounds at least one of the compressor and turbine section. The at least one casing is formed of sheet metal, and has at least one potential peak displacement point due to vibration across a speed range of the at least one of the compressor and turbine section. A stiffening element is fixed to a wall of the casing at the at least one potential peak displacement point. A method is also disclosed.
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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：US20250154871A1
公开(公告)日：2025-05-15
申请号：US18388259
申请日：2023-11-09
Applicant: Pratt & Whitney Canada Corp.
Inventor： Yashiva Dorsamy , Philippe Boyer , Jasrobin Grewal , Prakul Mittal , Domenico Di Florio
Abstract: An apparatus is provided for a gas turbine engine. This apparatus includes a bladed rotor rotatable about an axis. The bladed rotor includes a rotor disk and a plurality of rotor blades projecting radially out from the rotor disk. The rotor blades are arranged circumferentially around the rotor disk in an array. The array of the rotor blades are divided into a plurality of sectors including a first sector and a second sector. The rotor blades are disposed in the first sector including a plurality of first rotor blades. Each of the first rotor blades includes a first coating. The rotor blades are disposed in the second sector including a plurality of second rotor blades. Each of the second rotor blades includes a second coating that is different from the first coating.
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公开(公告)号：US12025053B1
公开(公告)日：2024-07-02
申请号：US18218683
申请日：2023-07-06
Applicant: Pratt & Whitney Canada Corp.
Inventor： Nicola Houle , Domenico Di Florio
CPC classification number: F02C3/04 , F01D9/041 , F01D25/04 , F05D2240/12 , F05D2260/96
Abstract: A stator vane assembly includes a support structure a support structure and a plurality of cantilever stator vanes Each cantilever stator vane of the plurality of cantilever stator vanes extends from the support structure to a distal end of that cantilever stator vane. At least one notch is formed in each of the distal ends. At least one damper is received within the at least one notch formed in each of the distal ends. A method is also disclosed.
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