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公开(公告)号：US10753219B2
公开(公告)日：2020-08-25
申请号：US14746246
申请日：2015-06-22
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labbe
Abstract: The seal runner has an annular body secured to a rotating shaft of the gas turbine engine whereas ring segments are secured to a case of the gas turbine, with the seal runner having a radially-outer surface having a contacting portion adapted to rubbingly receive ring segments of the contact seal assembly during use, the seal runner having a radially-inner surface opposite to the radially-outer surface. The method includes rotating the seal runner relative to the ring segments and generating heat from the rubbing engagement therebetween; and feeding a flow of cooling fluid against the radially-inner surface to cool the seal runner from said generated heat including maintaining a pool of cooling fluid having a given depth against the radially-inner surface.
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公开(公告)号：US12264607B1
公开(公告)日：2025-04-01
申请号：US18516270
申请日：2023-11-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ahmad Cheikhzen , Victor Sa Melo , Penny Nicolaidis , Daniel Alecu , Michel Labbe
Abstract: An oil filler assembly, has: a filler tube extending from a bottom end to a top end; a non-return valve having a tube side and a tank side; a cap assembly including a cap removably secured to the filler tube and a dipstick projecting from the cap; a vent having an inlet connected to the tank side and an outlet connected to the tube side, the vent defining a flow path bypassing the non-return valve; and a safety valve connected to the vent and having an open configuration in which fluid flow is permitted and a closed configuration in which fluid flow is prevented, the safety valve being engageable by the cap assembly to bias the safety valve in the open configuration when the cap is secured to the top end, the safety valve being in the closed configuration when the cap assembly is detached from the top end.
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公开(公告)号：US12264594B1
公开(公告)日：2025-04-01
申请号：US18516209
申请日：2023-11-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ahmad Cheikhzen , Victor Sa Melo , Michel Labbe , Penny Nicolaidis , Daniel Alecu
Abstract: An oil filler assembly for an aircraft engine, has: a filler tube extending from a bottom end to a top end; a valve having a tube side fluidly connected to the filler tube and a tank side; a cap removably secured to the top end; a dipstick secured to the cap and extending into the filler tube; and a piston secured to the dipstick, the piston having: a sealing configuration in which the piston sealingly engages the filler tube to fluidly disconnect the top end from the valve, the piston being in the sealing configuration when the cap is secured to the top end of the filler tube; and a venting configuration in which the piston permits fluid communication between the top end and the valve, the piston being in the venting configuration when the cap is moved away from the top end of the filler tube.
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4.发明申请INTERNALLY COOLED SEAL RUNNER AND METHOD OF COOLING SEAL RUNNER OF A GAS TURBINE ENGINE 审中-公开内部冷却密封圈和冷却涡轮发动机密封圈的方法公开(公告)号：US20160348792A1
公开(公告)日：2016-12-01
申请号：US14746246
申请日：2015-06-22
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labbe
Abstract: The seal runner has an annular body secured to a rotating shaft of the gas turbine engine whereas ring segments are secured to a case of the gas turbine, with the seal runner having a radially-outer surface having a contacting portion adapted to rubbingly receive ring segments of the contact seal assembly during use, the seal runner having a radially-inner surface opposite to the radially-outer surface. The method includes rotating the seal runner relative to the ring segments and generating heat from the rubbing engagement therebetween; and feeding a flow of cooling fluid against the radially-inner surface to cool the seal runner from said generated heat including maintaining a pool of cooling fluid having a given depth against the radially-inner surface.
Abstract translation: 密封流道具有固定到燃气涡轮发动机的旋转轴的环形体，而环段固定到燃气轮机的壳体上，密封流道具有径向外表面，该径向外表面具有适于摩擦地接收环段的接触部分 在使用期间，密封流道具有与径向外表面相对的径向内表面。 该方法包括使密封流道相对于环形部分旋转，并从其间的摩擦接合产生热量; 并且将冷却流体流供给到径向内表面以从所述产生的热量冷却密封流道，包括保持具有给定深度的冷却流体池相对于径向内表面。
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公开(公告)号：US11698025B2
公开(公告)日：2023-07-11
申请号：US17175174
申请日：2021-02-12
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Darragh McGrath , Michel Labbe , Sean Powers , Pierre Gauvin
CPC classification number: F02C7/06 , F01M11/0004 , F01M11/12 , F05D2220/32 , F05D2260/98
Abstract: A method of monitoring a sealing component of a gas turbine engine, comprising: collecting oil leaked from the component; detecting a volume of the collected oil upstream of an oil return path of the gas turbine engine; and signalling for inspection of the component when the volume of the collected oil exceeds a threshold volume. Also disclosed is an oil leakage monitoring system for a gas turbine engine, comprising: one or more sealing components to be lubricated by oil; a valve downstream of the one or more components and fluidly connected to an oil system; a reservoir downstream of the one or more components to collect oil, the reservoir upstream of the valve; and a volume measurement device configured to detect the oil collected in the reservoir, and to signal for inspection of the one or more components when the oil collected in the reservoir exceeds a threshold volume.
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Patent Agency Ranking
公开(公告)号：US11203948B2
公开(公告)日：2021-12-21
申请号：US16563152
申请日：2019-09-06
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labbe , Steve Fett , Ho-Wing Edmund Leung
Abstract: The contact seal assembly for a shaft of a gas turbine engine includes a carbon seal mounted in a fixed position within a seal housing, and an annular seal runner adapted to be connected to the shaft of the gas turbine engine and rotatable relative to the carbon ring segments. The seal runner is disposed adjacent to and radially inwardly from the carbon ring segments to form a contact interface between the seal runner and the carbon ring segments which forms a substantially fluid tight seal. The seal runner includes a coolant scoop disposed in a cavity defined by the seal housing, a first slinger disposed between the coolant scoop and the contact interface, a second slinger disposed between the first slinger and the contact interface, and a coolant collector groove disposed between the first slinger and the second slinger.
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公开(公告)号：US09770978B2
公开(公告)日：2017-09-26
申请号：US14484938
申请日：2014-09-12
Applicant: Pratt & Whitney Canada Corp.
Inventor： Marcin Rejman , Michel Labbe
CPC classification number: B60K15/0406 , B60K2015/0438 , B60K2015/0451 , B64D37/005 , B64D37/06 , B64D37/16
Abstract: A tank defines an inner cavity and at least an opening. A filler tube device comprises a tube passing through the opening in the tank, the tube forming a joint with at least one degree of freedom with the tank such that the tube is displaceable relative to the tank. The tube has an open end in the inner cavity of the tank, and an opposite open end outside of the tank, whereby the tube defines a passage for filling the tank. A sealing component is in the inner cavity of the tank, the sealing component configured for collaborating with the open end of the tube when the tube is moved into engagement therewith to close the open end of the tube inside the tank in a protective position.
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公开(公告)号：US10851664B2
公开(公告)日：2020-12-01
申请号：US16053406
申请日：2018-08-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labbe , Stuart Hodgson , Daniel Poirier
Abstract: A controlled gap radial oil sealing assembly in a gas turbine engine having a centre rotational axis defining an axial direction, the controlled gap radial sealing assembly comprises a seal element located around a cooperating seal runner and sized to define a controlled sealing gap between them, the seal runner having an axial length extending beyond an axial width of the seal element into an oiled region of the engine. A first annular surface radially outwardly spaced from and extending substantially along the axial length of the seal runner, the first annular surface sealingly cooperating with a seal housing of the seal element, and a second annular surface axially extending to overlap at least a portion of the first annular surface, the second annular surface radially outwardly spaced from the first annular surface relative to the center axis.
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9.发明申请SEAL AND BEARING ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING SAME 有权用于气体涡轮发动机的密封和轴承组件及其组装方法公开(公告)号：US20160348522A1
公开(公告)日：2016-12-01
申请号：US14746241
申请日：2015-06-22
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labbe
CPC classification number: F16C17/02 , F01D11/003 , F01D25/125 , F02C7/06 , F02C7/28 , F05D2220/32 , F05D2230/60 , F05D2240/50 , F05D2240/55 , F05D2260/20 , F16C33/74 , F16C33/76 , F16C43/02 , F16C2360/23 , F16J15/162 , Y10S277/907 , Y10S277/93
Abstract: A seal and bearing assembly of a gas turbine engine having an engine case with a cooling fluid nozzle located between a bearing outer ring and ring segments, and a rotary shaft for rotation in the engine case around a main axis, the seal and bearing assembly can be assembled by positioning the engine case and the rotary shaft in axial alignment, and axially moving the engine case relative to the rotary shaft including moving the bearing outer ring across the axial location of the runner portion and into an assembled condition. The rotary shaft having mounted thereon a bearing inner ring and a runner assembly having a runner portion, a sleeve portion being concentric and radially internal to the runner portion, and a cooling fluid passage having a radial segment leading from an outgoing segment to a returning segment extending in a direction leading back toward the bearing inner ring.
Abstract translation: 一种燃气涡轮发动机的密封件和轴承组件，其具有发动机壳体，其具有位于轴承外圈和环段之间的冷却流体喷嘴，以及用于在发动机壳体中围绕主轴线旋转的旋转轴，所述密封件和轴承组件可以 通过将发动机壳体和旋转轴定位成轴向对准并且相对于旋转轴线轴向移动发动机壳体来组装，包括使轴承外圈横过流道部分的轴向位置并进入组装状态。 旋转轴上安装有轴承内圈和具有流道部分的流道组件，套筒部分同心且位于流道部分的径向内部，以及冷却流体通道，具有从输出段引导到返回段的径向段 沿着朝向轴承内圈的方向延伸。
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公开(公告)号：US10968834B2
公开(公告)日：2021-04-06
申请号：US16456573
申请日：2019-06-28
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labbe , Lukasz Pokrzywa
Abstract: There is disclosed an aircraft engine having: an engine shaft; a first transmission shaft in driving engagement with the engine shaft and a second transmission shaft concentric with the first transmission shaft and in driving engagement with the first transmission shaft, the second transmission shaft drivingly engageable to an engine accessory, the first and second transmission shafts rotatable about an axis; and at least two axially spaced apart annular ring seals disposed radially between the first and second transmission shafts, the at least two annular ring seals biased against both of the first and second transmission shafts.
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