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公开(公告)号：US20190085868A1
公开(公告)日：2019-03-21
申请号：US15706311
申请日：2017-09-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Karan ANAND , Farid ABRARI , Ernest ADIQUE , Paul AITCHISON , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Tibor URAC , Thomas VEITCH
Abstract: A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.
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公开(公告)号：US20190145431A1
公开(公告)日：2019-05-16
申请号：US16245516
申请日：2019-01-11
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ignatius THERATIL , Krishna Prasad BALIKE , Sean Michael KELLY , Richard IVAKITCH , Peter TOWNSEND , Ronald DUTTON , Paul STONE , Robert VENDITTI , Daniel FUDGE , Milica KOJOVIC , Aldo ABATE
Abstract: A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the compressor rotor.
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公开(公告)号：US20190078589A1
公开(公告)日：2019-03-14
申请号：US15703472
申请日：2017-09-13
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Ignatius THERATIL , Peter TOWNSEND , Tibor URAC
CPC classification number: F04D29/666 , F01D5/16 , F04D29/324 , F04D29/327 , F04D29/668 , F05D2220/36 , F05D2240/307 , F05D2260/961
Abstract: A rotor for a gas turbine engine comprises a rotor having a hub and blades around the hub, and extending from the hub to tips. The tips include first and second tip portions between their respective tip leading edge and tip trailing edge. Tips are spaced from a rotational axis of the rotor by spans. A mean span of a first tip portion of a first blade is greater than a mean span of a corresponding first tip portion of a second blade. A mean span of a second tip portion the first blade is less than a mean span of a corresponding second tip portion of the second blade.
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Patent Agency Ranking
公开(公告)号：US20190107123A1
公开(公告)日：2019-04-11
申请号：US15726819
申请日：2017-10-06
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Ignatius THERATIL , Peter TOWNSEND , Tibor URAC
Abstract: A fan for a gas turbine engine comprises blades distributed around a hub. The blades include first and second blades, having geometric parameters and/or material properties that differ from each other to frequency mistune the fan. The blades are distributed about the hub with at least one second blade between adjacent first blades. The leading edge of the airfoil of the second blades is disposed axially aft of the corresponding leading edge of the first blades in at least a portion of the blade span.
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公开(公告)号：US20190085708A1
公开(公告)日：2019-03-21
申请号：US15707133
申请日：2017-09-18
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Paul AITCHISON , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Tibor URAC
CPC classification number: F01D5/288 , F01D5/141 , F01D5/16 , F01D5/26 , F05D2220/3216 , F05D2230/90 , F05D2240/301 , F05D2260/961 , F05D2300/133 , F05D2300/143 , F05D2300/16
Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.
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公开(公告)号：US20230349297A1
公开(公告)日：2023-11-02
申请号：US17661454
申请日：2022-04-29
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Krishna Prasad BALIKE , Edwin WONG , Daniel FUDGE , Ignatius THERATIL , Paul STONE , Charles MASON , Karan ANAND , Pascal DORAN
CPC classification number: F01D5/16 , F01D5/141 , F05D2260/961 , F05D2240/305 , F05D2240/303 , F05D2240/304
Abstract: A method includes: obtaining a rotor having a hub and a plurality of blades protruding from the hub, the plurality of blades including first blades and second blades disposed in alternation around a central axis of the rotor, natural vibration frequencies of the first blades different from natural vibration frequencies of the second blades; determining that a difference between a first natural vibration frequency of a first blade of the first blades and a second natural vibration frequency of a second blade of the second blades is below a threshold; and modifying a shape of the first blade until the difference between the first natural vibration frequency and the second natural vibration frequency is at or above the threshold.
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公开(公告)号：US20200018176A1
公开(公告)日：2020-01-16
申请号：US16562701
申请日：2019-09-06
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Paul AITCHISON , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Tibor URAC
Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.
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公开(公告)号：US20190085704A1
公开(公告)日：2019-03-21
申请号：US15706247
申请日：2017-09-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Ignatius THERATIL , Peter TOWNSEND , Tibor URAC
Abstract: A rotor for a gas turbine engine. The rotor includes blades circumferentially distributed around a hub. The blades have airfoils with a span defined between a root and tip, a chord defined between a leading edge and a trailing edge, and a thickness defined between a pressure side surface and suction side surface. The blades include first blades and second blades. The airfoil of the first blades has a first thickness distribution defining a first natural vibration frequency of the airfoils of the first blades. The airfoil of the second blades has a second thickness distribution defining a second natural vibration frequency different than the first natural vibration frequency. The first thickness distribution is different than the second thickness distribution along a radially-inner half of the span, and the first thickness distribution matches the second thickness distribution along a radially-outer half of the span.
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