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公开(公告)号：US11725533B2
公开(公告)日：2023-08-15
申请号：US17093790
申请日：2020-11-10
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel Poick , Tibor Urac
CPC classification number: F01D17/162 , F01D9/041 , F02C9/20 , F04D29/563 , F05D2240/128 , F05D2240/54 , F05D2260/36
Abstract: A variable guide vane (VGV) assembly, has: vanes distributed about a central axis, each of the vanes having an airfoil extending between first and second stems, the vanes rotatable about vane axes extending between the first and second stems; and a bushing ring supporting the first stems of the vanes, the bushing ring defining circumferentially distributed pockets receiving the first stems of the vanes, the bushing ring having a first ring body extending circumferentially around the central axis, a second ring body extending circumferentially around the central axis and removably secured to the first ring body, the second ring body defining at least one tab projecting axially to axially overlap at least a portion of the first ring body and defining a contact plane therebetween, and at least one locking member extending radially through the contact plane to removably secure the first ring body and the second ring body together.
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公开(公告)号：US11092032B2
公开(公告)日：2021-08-17
申请号：US16543887
申请日：2019-08-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Tibor Urac , Esther Leung
Abstract: A variable guide vane (VGV) apparatus has a variable guide vane (VGV) rotatable about a vane rotation axis. An actuating arm is mounted to the VGV. The actuating arm has a fork defining a slot for receiving a drive pin. The slot is profiled to accommodate angular misalignment between the pin and the fork throughout a range of motion of the associated pin along the slot.
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公开(公告)号：US11060411B2
公开(公告)日：2021-07-13
申请号：US16672023
申请日：2019-11-01
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Tibor Urac , Barry Barnett , Matthew Meschino
IPC: F01D5/30
Abstract: A gas turbine engine assembly comprises a casing defining a gas path, the casing including a shroud having an annular body having a surface defining a portion of gas path, the shroud having slots configured for receiving inserted vanes. The slots are delimited substantially about their perimeter by respective flanges, the flanges radially offset from the shroud gas path surface so as to be disposed outside of said gas path, the flanges defined by opposed flange surfaces. Vanes received in the slots. Grommets engage the vanes at the slots. Inserts extend between the shroud and the grommets, the inserts having slots configured for engaging both of the opposed flanges, the inserts extending in a radial direction from at least the respective flange to an adjacent said shroud gas path surface to substantially matchingly mate with an inner surface the adjacent shroud gas path surface.
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公开(公告)号：US10408231B2
公开(公告)日：2019-09-10
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
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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公开(公告)号：US09657746B2
公开(公告)日：2017-05-23
申请号：US14472958
申请日：2014-08-29
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Tibor Urac
CPC classification number: F04D29/667 , F01D5/045 , F01D5/046 , F02C6/08 , F04D29/284 , F04D29/321
Abstract: A compressor rotor of a gas turbine engine includes a rotor body having a face adapted to face an adjacent rotor. The rotor body extends radially between an outer peripheral rim surface and an inner rim surface. The inner rim surface defines a bore of the rotor body. A plurality of blades extends radially from the outer peripheral rim surface. A plurality of anti-vortex fins extends axially from the face of the rotor body facing the adjacent rotor. The plurality of anti-vortex fins forms a plurality of open radial passageways. The plurality of anti-vortex fins extends axially to a predetermined thickness such that, when assembled with the second rotor, axial extremities of the plurality of anti-vortex fins being in close proximity with the adjacent rotor and the adjacent rotor closes the radial passageways. A method of providing a first rotor for assembly with a second facing rotor of a compressor rotor assembly is also presented.
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Patent Agency Ranking
公开(公告)号：US12297908B2
公开(公告)日：2025-05-13
申请号：US17806185
申请日：2022-06-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Tibor Urac , Sébastien Bergeron
Abstract: A seal for an aircraft engine includes an annular body receivable in interference fit in a radial spacing defined between inner and outer cylindrical components of the aircraft engine, the annular body defining a central axis coaxial with the inner and outer cylindrical components, the annular body including an inner portion defining an inner diameter, an outer portion defining an outer diameter, and an intermediate portion extending between the inner and outer portions. The outer portion is slidably engageable to the outer cylindrical component at an outer contact sealing portion of the annular body. One of the inner portion and the outer portion defines at least one cut extending from the one of the inner portion and the outer portion toward another one of the inner portion and the outer portion. A method for sealing a radial spacing between coaxial cylindrical components in an aircraft engine is also described.
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公开(公告)号：US11009039B2
公开(公告)日：2021-05-18
申请号：US16226694
申请日：2018-12-20
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas Veitch , Tibor Urac , Tyler Richardson
Abstract: A gas turbine engine casing apparatus includes annular first and second annular cases connected by a spigot joint. The spigot joint includes an annular projection of the first annular case fitted into an annular recess of the second annular case. A plurality of circumferentially spaced apart scallops are formed on one of surfaces of the annular projection or of the annular recess, and are located in selective circumferential locations adjacent respective enhanced stiff areas of the first and second annular cases.
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公开(公告)号：US10260636B2
公开(公告)日：2019-04-16
申请号：US15066463
申请日：2016-03-10
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Richard A. Kostka , Dean Carpenter , Tibor Urac , Adam Logan , Aaron Grey
Abstract: A controlled gap seal device is adapted to surround a shaft with an annular seal element. A ring is positioned on an outer surface of the seal element, the ring adapted to modify a diametrical dimension of the seal element by thermally expanding/contracting as a function of temperature variations. A housing assembly has an interior enclosing the seal element and the ring, with the seal configured to be generally stationary in the interior. The housing assembly has an air inlet and air outlet in fluid communication with a surrounding environment for directing a flow of gas from the surrounding environment onto the ring to controllably cool and shrink the ring. A method for modifying a diameter of a controlled gap seal relative to the shaft is also provided.
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公开(公告)号：US10190598B2
公开(公告)日：2019-01-29
申请号：US15046568
申请日：2016-02-18
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas Veitch , Tibor Urac , Tyler Richardson
Abstract: A gas turbine engine casing apparatus includes annular first and second annular cases connected by a spigot joint. The spigot joint includes an annular projection of the first annular case fitted into an annular recess of the second annular case. A plurality of circumferentially spaced apart scallops are formed on one of surfaces of the annular projection or of the annular recess, and are located in selective circumferential locations adjacent respective enhanced stiff areas of the first and second annular cases.
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公开(公告)号：US10012240B2
公开(公告)日：2018-07-03
申请号：US15492281
申请日：2017-04-20
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Tibor Urac
CPC classification number: F04D29/667 , F01D5/045 , F01D5/046 , F02C6/08 , F04D29/284 , F04D29/321
Abstract: A compressor rotor of a gas turbine engine includes a rotor body having a face adapted to face an adjacent rotor. The rotor body extends radially between an outer peripheral rim surface and an inner rim surface. The inner rim surface defines a bore of the rotor body. A plurality of blades extends radially from the outer peripheral rim surface. A plurality of anti-vortex fins extends axially from the face of the rotor body facing the adjacent rotor. The plurality of anti-vortex fins forms a plurality of open radial passageways. The plurality of anti-vortex fins extends axially to a predetermined thickness such that, when assembled with the second rotor, axial extremities of the plurality of anti-vortex fins being in close proximity with the adjacent rotor and the adjacent rotor closes the radial passageways. A method of providing a first rotor for assembly with a second facing rotor of a compressor rotor assembly is also presented.
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