公开(公告)号：US20230392512A1

公开(公告)日：2023-12-07

申请号：US17805046

申请日：2022-06-02

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Ahmed ABDELRAHMAN

IPC分类号： F01D17/14

CPC分类号： F01D17/145 ,  F05D2220/323 ,  F05D2260/36 ,  F05D2260/31 ,  F05D2260/606 ,  F05D2250/182

摘要： A valve for an air system in an aircraft engine, comprising: a housing defining a chamber having a valve axis; a body within the chamber about a piston axis collinear with the valve axis, extending from a first surface to a second surface, defining a bore extending from the first to the second surface, having a mating connector defined by the second surface and located radially outward of the bore relative to the piston axis; and a sleeve extending from a first end matingly engaged with the mating connector to a second end along a sleeve axis collinear with the valve axis, the first end axially stacked on the body via the first surface to define a first distance between the first end and the first surface, and via the second surface to define a second distance between the first end and the second surface greater than the first distance.

公开(公告)号：US10072520B2

公开(公告)日：2018-09-11

申请号：US14760746

申请日：2014-02-12

申请人： United Technologies Corporation

发明人： Pellegrino J. Pisacreta ,  Christopher D. Ramsey ,  Mark W. Colebrook

IPC分类号： F01D25/14 ,  F02C7/12 ,  F02C7/18 ,  F02C7/16 ,  F01D11/24

CPC分类号： F01D25/14 ,  F01D11/24 ,  F02C7/12 ,  F02C7/16 ,  F02C7/18 ,  F05D2250/182 ,  F05D2250/184

摘要： A cooling manifold has a plurality of pieces. The pieces extend in a circumferential direction to abutting flanges. The flanges are secured together at circumferential ends of each piece. Cooling channels are formed in between inner and outer walls. Air inlets are formed in the pieces with the air inlets delivering air in the interior. There are fingers on an outer periphery. The fingers are aligned within an air outlet. The air can be delivered into the inlet, cool the interior, and leave through the outlet extending to a main conduit. The main conduit is secured directly to an outer periphery of the cooling manifold.

公开(公告)号：US10036349B2

公开(公告)日：2018-07-31

申请号：US14916467

申请日：2014-09-05

申请人： SNECMA ,  AIRCELLE

发明人： Irwin Kernemp ,  Jonathan Langridge ,  Sébastien Pascal ,  Denis Guillois ,  Gérard Clere ,  Loïc Chapelain

IPC分类号： F02K1/48 ,  F02K1/82 ,  F02K1/60 ,  F02K1/62 ,  F02K1/76

CPC分类号： F02K1/48 ,  F02K1/60 ,  F02K1/62 ,  F02K1/763 ,  F02K1/827 ,  F05D2250/182

摘要： An afterbody for a turbojet engine having a central axis, provided with a nozzle comprising two doors facing each other between two lateral beams. The doors pivot around axes defining a pivot direction, between a retracted position, in which a middle portion of the downstream edge of the doors forms the edge of the outlet section of the nozzle combined with the downstream edges of the two lateral beams, and a deployed position, in which the middle portions of the downstream edges of the pivoting doors come together so as to block the channel between the two lateral beams in order to reverse the thrust of the turbojet engine gases. The edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons alternating with indentations and the afterbody.

公开(公告)号：US10018066B2

公开(公告)日：2018-07-10

申请号：US14862342

申请日：2015-09-23

申请人： United Technologies Corporation

发明人： Philip Robert Rioux

IPC分类号： F01D5/22 ,  F01D11/00 ,  F01D9/04 ,  F01D5/02

CPC分类号： F01D11/008 ,  F01D5/02 ,  F01D5/225 ,  F01D9/041 ,  F01D11/005 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/71 ,  F05D2250/75 ,  Y02T50/672 ,  Y02T50/673

摘要： What is described is a partial platform. The partial platform includes a leading edge, a trailing edge, a first circumferential edge and a second circumferential edge. The first circumferential edge and the second circumferential edge are both swept such that a central circumferential axis forms a substantially rounded or squared S shape.

公开(公告)号：US10006303B2

公开(公告)日：2018-06-26

申请号：US15487844

申请日：2017-04-14

申请人： William P. Sanders ,  Anthony F. Mitola

发明人： William P. Sanders ,  Anthony F. Mitola

IPC分类号： F04D29/08 ,  F01D11/00 ,  F01D11/02 ,  F04D29/16

CPC分类号： F01D11/001 ,  F01D11/02 ,  F04D29/083 ,  F04D29/164 ,  F05D2250/182 ,  F05D2250/184 ,  F16J15/443

摘要： A contra-flow strip for inhibiting leakage of a fluid between a rotating member and a stationary member includes, for example, a base supportable by the stationary member coaxially around the rotating member, and means, extending from the base coaxially towards the rotating member between a low pressure region and a high pressure region, for generating a contra flow of a portion of a tangential flow of fluid in the low pressure region to the high pressure region between the stationary member and the rotating member.

公开(公告)号：US09945325B2

公开(公告)日：2018-04-17

申请号：US14646990

申请日：2013-11-06

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Gary D. Roberge

IPC分类号： F02K3/115 ,  F01D9/06 ,  F02K3/06 ,  F02C7/14 ,  F02C7/18 ,  F02K3/105 ,  F02C7/06

CPC分类号： F02K3/115 ,  F01D9/065 ,  F02C7/06 ,  F02C7/14 ,  F02C7/18 ,  F02K3/06 ,  F02K3/105 ,  F05D2210/12 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2250/182 ,  F05D2250/60 ,  F05D2260/20 ,  F05D2260/213 ,  F05D2260/4031 ,  F05D2260/98 ,  Y02T50/676

摘要： An oil cooling system and method are provided for use with respect to a lubricated mechanical system within a bypass configured gas turbine engine. A surface cooler is fluidly linked to the lubricated mechanical system to receive oil from the lubricated mechanical system for cooling and reuse. In an embodiment, the surface cooler is mounted on an existing surface within the bypass airflow path of the bypass configured gas turbine engine to provide effective cooling while avoiding the introduction of additional aerodynamic disturbances in the bypass path. In an embodiment, the surface cooler is mounted on the fan casing or on a fan exit guide vane.

公开(公告)号：US20180066521A1

公开(公告)日：2018-03-08

申请号：US15660067

申请日：2017-07-26

申请人： FUJITSU GENERAL LIMITED

发明人： Hirotaka SAWADA

IPC分类号： F01D5/14 ,  F24F1/00 ,  F24F13/24 ,  F01D5/16

CPC分类号： F01D5/141 ,  F01D5/16 ,  F04D29/384 ,  F04D29/681 ,  F05D2240/304 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2300/43 ,  F24F1/0029 ,  F24F13/24

摘要： An axial fan includes: a hub; a plurality of blades arranged in a circumferential direction of the hub; a cutout in a rear edge part of each of the plurality of blades, the cutout divides the rear edge part into an outer rear edge part and an inner rear edge part; a first groove part disposed in the outer rear edge part, the first groove part including a plurality of grooves extending toward the front edge part; and a second groove part disposed in the inner rear edge part, the second groove part including a plurality of grooves extending toward the front edge part, the plurality of grooves of the first groove part and the plurality of grooves of the second groove part having different shapes when viewed in a rotational axis direction of the hub.

公开(公告)号：US09879548B2

公开(公告)日：2018-01-30

申请号：US14823604

申请日：2015-08-11

申请人： General Electric Company

发明人： Srikeerthi Annaluri ,  Thangaraj Subbareddyar

IPC分类号： F01D5/10 ,  F01D5/22 ,  F01D5/16

CPC分类号： F01D5/22 ,  F01D5/16 ,  F05D2240/30 ,  F05D2240/80 ,  F05D2250/182 ,  F05D2250/294 ,  F05D2260/96 ,  Y02T50/67

摘要： A damper system for a turbine having adjacent turbine bucket platforms including opposing slash faces having opposing grooves is provided. The system includes a pin having a substantially cylindrical-shaped body configured for positioning in the opposing grooves. A set of slots are provided in an outer surface of the pin and at spaced axial locations therealong. The set of slots face in a radially outward direction relative to the turbine bucket platforms.

公开(公告)号：US20170334025A1

公开(公告)日：2017-11-23

申请号：US15520870

申请日：2015-10-23

申请人： GKN Aerospace Sweden AB

发明人： Robert Reimers

IPC分类号： B23K31/02 ,  F01D25/28 ,  B23K31/12 ,  B23K26/342 ,  B23K9/04 ,  B64C1/12 ,  B23K101/18 ,  B23K11/04 ,  B23K101/00 ,  B23P6/04

CPC分类号： B23K31/02 ,  B23K9/04 ,  B23K9/042 ,  B23K9/044 ,  B23K11/04 ,  B23K26/342 ,  B23K31/12 ,  B23K2101/006 ,  B23K2101/18 ,  B23P6/04 ,  B64C1/12 ,  F01D25/28 ,  F02K1/78 ,  F05D2230/232 ,  F05D2250/182 ,  F05D2250/183 ,  Y02T50/671

摘要： A method for joining two structural elements by welding, in particular by butt welding comprises forming a weld line joining the two structural elements; and adding material across the weld line, thereby forming one or more crack stoppers for limiting crack propagation along the weld line. The one or more crack stoppers each have a limited extension along the weld line as seen in relation to a length of the weld line. A structural system comprising two structural elements joined by the method is disclosed. The method may be applied, e.g., to components of aircraft engines.

公开(公告)号：US09709275B2

公开(公告)日：2017-07-18

申请号：US14314075

申请日：2014-06-25

申请人： General Electric Company

发明人： Peter de Diego ,  Herbert Chidsey Roberts, III ,  Frederic Woodrow Roberts, Jr.

IPC分类号： F23R3/02 ,  F23R3/00

CPC分类号： F23R3/02 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2260/607 ,  F23R3/002

摘要： A casing for a turbo-machine at least partially defines a flow path for a working fluid through or around one or more of a compressor section, a combustor assembly, or a turbine section. The casing defines an inner surface and the inner surface defines a plurality of debris routing channels. The plurality of debris routing channels are configured to route debris in a working fluid within the casing towards a debris collection mechanism.