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公开(公告)号：US20230399982A1
公开(公告)日：2023-12-14
申请号：US17806185
申请日：2022-06-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Tibor URAC , Sébastien BERGERON
CPC classification number: F02C7/28 , F01D11/003 , F05D2220/323 , F05D2240/55 , F05D2230/60 , F05D2260/60
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：US20230138438A1
公开(公告)日：2023-05-04
申请号：US17452927
申请日：2021-10-29
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Bernadette MASON , Gennadii DOROZHKIN , Jesse ALBUS , Tibor URAC
Abstract: A support plate for an engine casing includes an anti-rotation rib abutting an outer flange wall of the casing and a misalignment tab extending radially outwardly from the anti-rotation rib. The support plate has a support plate hole configured to be aligned with one flange hole of a flange of the casing.
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公开(公告)号：US20230129366A1
公开(公告)日：2023-04-27
申请号：US17509958
申请日：2021-10-25
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Matthew MESCHINO , Tibor URAC , Raghavendra PENDYALA
Abstract: A centrifugal compressor of an aircraft engine includes an impeller and a shroud extending circumferentially around the impeller. A bellmouth disposed upstream of the impeller extends circumferentially and includes: a conduit section extending from a first end to an upstream-most location of the bellmouth, the first end of the conduit section secured to the shroud, and a peripheral section extending from the upstream-most location to a second end located radially outwardly of the first end, the peripheral section located radially outwardly of the conduit section and axially overlapping the conduit section. A stiffening member is located on the peripheral section of the bellmouth proximate the second end. The stiffening member extends circumferentially and provides the bellmouth with a dynamic vibration mode outside a range of dynamic vibration modes of the aircraft engine during operation.
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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：US20230029960A1
公开(公告)日：2023-02-02
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
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：US20220145771A1
公开(公告)日：2022-05-12
申请号：US17093790
申请日：2020-11-10
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel POICK , Tibor URAC
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：US20180172026A1
公开(公告)日：2018-06-21
申请号：US15381420
申请日：2016-12-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Tibor URAC , Bernadette MASON
CPC classification number: F04D29/542 , F01D9/042 , F01D11/005 , F04D29/083 , F04D29/644 , F05D2220/32 , F05D2300/121 , F05D2300/43 , F05D2300/501
Abstract: A seal spacer for a gas turbine engine to provide sealing between a casing wall and a stator vane of the engine. The seal spacer comprises a circumferential body having a slot defined therethrough and configured to receive the stator vane therein. The circumferential body is configured to be disposed between and space apart the engine casing wall from a head of the stator vane when the vane is inserted in the slot and the vane is inserted in the opening in the casing wall. The circumferential body includes a support positioned to be engage and provide a gap between the casing wall and the head when the seal spacer is installed therebetween, and an elastomeric seal portion positioned to engage and compressingly provide sealing the casing wall and the head when the seal spacer is installed therebetween to seal the gap.
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公开(公告)号：US20170204876A1
公开(公告)日：2017-07-20
申请号：US15410060
申请日：2017-01-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Karan ANAND , Peter TOWNSEND , Tibor URAC , Terry BROWNRIDGE
CPC classification number: F04D29/526 , F04D29/164 , F04D29/324 , F04D29/644 , F04D29/685 , F05D2250/294 , F05D2250/61
Abstract: A gas turbine engine is described having a rotor with a plurality of rotor blades each extending radially between a blade root to a blade tip and axially between a leading edge and a trailing edge. An annular casing body housing the rotor blades includes an abradable segment of the inner surface facing the blade tips and having an abradable member. The abradable segment having one or more annular grooves, extending into the casing body from an inner surface thereof, and including an edge groove axially aligned with and facing the leading edge or the trailing edge of the rotor blades. The edge groove extends axially between a first position on the inner surface upstream of the leading edge or the trailing edge, and a second position on the inner surface downstream of the leading edge or the trailing edge.
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公开(公告)号：US20150096641A1
公开(公告)日：2015-04-09
申请号：US14046074
申请日：2013-10-04
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Bernard CHOW , Tibor URAC , Grigory RUKIN , Derek BAXTER
IPC: F15D1/02
CPC classification number: G05D7/012 , F02C7/00 , F05D2240/35 , F05D2250/311 , F05D2250/41 , F05D2260/60 , F16K7/06
Abstract: A flow regulating device in a fluid system according to one embodiment may include a housing defining a cavity receiving an orifice body. The orifice body defines a bore extending axially therethrough and includes a flexible end section, with axial slits in one example, to allow the end section to be radially compressed to change a cross-section of a flow passageway when the bore of the orifice body is included in the flow passageway.
Abstract translation: 根据一个实施例的流体系统中的流量调节装置可以包括限定容纳孔体的空腔的壳体。 孔本体限定了轴向延伸穿过其中的孔，并且包括柔性端部部分，在一个示例中具有轴向狭缝，以允许端部部分被径向压缩以改变流体通道的横截面， 包括在流通道中。
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公开(公告)号：US20230003141A1
公开(公告)日：2023-01-05
申请号：US17363384
申请日：2021-06-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Matthew EARNSHAW , Tibor URAC
Abstract: A component of an aircraft engine includes an annular flange disposed about a radially outer surface of the component. the annular flange includes an annular wall extending radially outwardly from the radially outer surface of the component. The annular wall includes radially-extending supports circumferentially spaced apart and extending radially between the radially outer surface of the component and a circumferentially uninterrupted radially outer rim of the annular wall. The annular wall includes one or more arcuate cutouts defined circumferentially between adjacent radially-extending supports and radially inwards of the radially outer rim of the annular wall. The radially-extending supports include fastener openings defined axially therethrough. A spigot extends axially from the radially outer rim of the annular wall and circumferentially about an entire circumference of the radially outer rim of the annular wall.
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