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公开(公告)号：US20240141795A1
公开(公告)日：2024-05-02
申请号：US18488377
申请日：2023-10-17
申请人： ROLLS-ROYCE plc
发明人： Samuel P. LEE
IPC分类号： F01D9/04
CPC分类号： F01D9/04 , F05D2240/121 , F05D2250/73
摘要： Described herein is a flow splitter for a gas turbine engine, the flow splitter comprising a leading edge, wherein the radial and/or axial position of the leading edge varies circumferentially around the flow splitter, such that the leading edge is non-axisymmetric. Also described is a method of manufacture of a flow splitter and an engine comprising a flow splitter.
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公开(公告)号：US20230220786A1
公开(公告)日：2023-07-13
申请号：US17916333
申请日：2021-04-01
发明人： Paul Antoine FORESTO
CPC分类号： F01D25/26 , F01D9/065 , F01D5/143 , F05D2240/14 , F05D2250/10 , F05D2250/73
摘要： An intermediate casing includes an inner wall having an outer surface extending along a longitudinal axis, the outer surface having a first profile in a first plane, an outer wall having an inner surface a second profile in the first plane, and first through fourth arms each extending radially. The outer and inner surfaces and the first and second arms delimit a first cavity, the first cavity having a first area and the outer and inner surfaces being separated by a first distance. The outer and inner surfaces and the third and fourth arms delimit a second cavity, the second cavity having a second area and the outer and inner surfaces being separated by a second distance. The first and second profiles are such that the first area is substantially identical to the second area and the first distance is different from the second distance.
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公开(公告)号：US20180347587A1
公开(公告)日：2018-12-06
申请号：US16105336
申请日：2018-08-20
CPC分类号： F04D29/563 , F01D17/162 , F05D2250/14 , F05D2250/73
摘要： A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft.
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4.发明申请公开(公告)号：US20180266541A1
公开(公告)日：2018-09-20
申请号：US15921490
申请日：2018-03-14
申请人： GE Avio S.r.l.
CPC分类号： F16H57/082 , B60Y2200/50 , B60Y2400/73 , F02C3/107 , F05D2250/73 , F05D2260/40311 , F16H1/28 , F16H1/2809 , F16H2001/289 , F16H2057/085
摘要： A planet-carrier for an epicyclic gearing is provided with a ring having a plurality of plate sectors and a plurality of connection sectors, alternating with one another about a first axis; a connection structure connects in an angularly fixed manner the connection sectors to a rotating member or to a static member; the planet-carrier is also provided with a plurality of pins, which are fixed with respect to the plate sectors and protrude in opposite directions from the plate sectors along respective second axes, parallel and eccentric with respect to the first axis; each pin has two coaxial outer surfaces, adapted to support respective planet gears of the gearing and symmetrical to each other with respect to a symmetry plane orthogonal to the first axis; the plate sectors are asymmetrical with respect to this symmetry plane.
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公开(公告)号：US10036260B2
公开(公告)日：2018-07-31
申请号：US14765852
申请日：2014-03-07
CPC分类号： F01D5/26 , F01D5/02 , F01D5/12 , F01D5/22 , F01D5/3007 , F01D5/326 , F01D11/006 , F05D2220/32 , F05D2240/55 , F05D2250/71 , F05D2250/73 , F05D2260/96
摘要： A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.
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公开(公告)号：US20180156239A1
公开(公告)日：2018-06-07
申请号：US15831706
申请日：2017-12-05
发明人： Vincent Zielinger , Wiliam Riera
CPC分类号： F04D29/681 , F01D5/143 , F01D5/145 , F01D5/146 , F01D9/041 , F02K3/06 , F04D29/544 , F05D2220/323 , F05D2240/12 , F05D2240/127 , F05D2250/11 , F05D2250/73 , Y02T50/671 , Y02T50/673
摘要： A turbine engine part or set of parts including at least first and second obstacles each having a leading edge and a trailing edge, and a platform from which the obstacles extend; wherein the platform has, between the pressure side of the first obstacle and the suction side of the second obstacle a non-axisymmetric surface defining at least one fin with a substantially triangular cross-section, each fin being associated with a leading position and a trailing position on the surface between which the fin extends, such that the leading position is upstream of each of the leading edges; the trailing position is downstream of each of the leading edges.
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公开(公告)号：US09964118B2
公开(公告)日：2018-05-08
申请号：US14352263
申请日：2012-10-10
申请人： LG ELECTRONICS INC.
发明人： Byung Il Park , Byung Soon Kim , Sun Jong Noh , Kam Gyu Lee , Kyong Min Kwon
CPC分类号： F04D29/403 , F04D29/283 , F04D29/424 , F04D29/663 , F05D2250/711 , F05D2250/73 , F24F7/007 , F25D17/06
摘要： A sirocco fan is provided that may include an impeller, in which a plurality of first blades and a plurality of second blades are formed on a main plate, and a scroll housing that covers the impeller. The scroll housing may include air suction holes formed on both of first and second plates and a rounded portion formed to be convex in an opposite direction of the impeller on a scroll that connects both of the first and second plates. An interval from the main plate to the rounded portion in a direction perpendicular to a rotation central axis of the impeller may be the largest. A rapid change in direction of air flowing to the scroll from the impeller may be minimized, and collision of air with the scroll may be lessened, reducing a flow loss and enhancing efficiency.
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公开(公告)号：US09833869B2
公开(公告)日：2017-12-05
申请号：US14176669
申请日：2014-02-10
发明人： Paul M. Lutjen , Patrick D. Couture
CPC分类号： B24B1/00 , B24B19/26 , F01D11/12 , F05D2240/11 , F05D2250/15 , F05D2250/712 , F05D2250/73 , Y10T29/49982
摘要： A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile.
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公开(公告)号：US09732700B2
公开(公告)日：2017-08-15
申请号：US14496526
申请日：2014-09-25
申请人： The Boeing Company
发明人： David F. Cerra , Robert H. Willie , Alvaro Prieto
CPC分类号： F02K1/006 , B64C7/02 , B64D33/04 , F02K1/002 , F02K1/06 , F02K1/30 , F02K1/46 , F05D2250/323 , F05D2250/324 , F05D2250/71 , F05D2250/73 , F05D2260/96 , Y02T50/671
摘要： A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow.
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公开(公告)号：US20170218773A1
公开(公告)日：2017-08-03
申请号：US15489323
申请日：2017-04-17
申请人： MTU Aero Engines AG
IPC分类号： F01D5/14
CPC分类号： F01D5/143 , F01D5/145 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/60 , F05D2250/73 , F05D2260/961 , Y02T50/673
摘要： A blade cascade of a turbomachine having at least one shape variation of a blade situated on the blade side in the proximity of a side wall and extending downstream, and at least one side wall contouring of the side wall or at least one second shape variation of an adjacent blade near the side wall, as well as a turbomachine, are disclosed.
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