公开(公告)号：US20240240574A1

公开(公告)日：2024-07-18

申请号：US18560212

申请日：2022-05-09

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Christelle MUTH-SENG ,  William DUARTE ,  Guillaume GAVA

IPC: F01D25/28 ,  B23P6/00 ,  B24C1/04 ,  C23C4/01 ,  C23C4/134

CPC classification number: F01D25/285 ,  B23P6/007 ,  B24C1/04 ,  C23C4/01 ,  C23C4/134 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2230/80 ,  F05D2240/90

Abstract: Equipment for treating an annular component of an aircraft turbomachine includes a support of elongate shape along an axis. The support includes, at one of its ends, a mount configured to receive the component, which is intended to extend about the axis. A cover is configured to be mounted on the component and to cover an upstream end of this component. The cover includes an orifice oriented along the axis (X). A clamping member passes through the orifice and is configured to cooperate with the support and to fix the cover to the support. An annular masking gasket extends about the axis and is configured to be interposed between the mount and a downstream end of the component. The gasket has an annular groove configured to be a counter-form of the downstream end.

公开(公告)号：US12012216B2

公开(公告)日：2024-06-18

申请号：US18061330

申请日：2022-12-02

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Stretton

IPC: B64D27/40 ,  B64D27/10 ,  F02C7/20

CPC classification number: B64D27/40 ,  B64D27/10 ,  B64D27/406 ,  F02C7/20 ,  F05D2220/323 ,  F05D2240/90

Abstract: A gas turbine engine includes a support structure for attaching the engine to an aircraft pylon. The support structure includes: an engine-side interface member, a pylon-side interface member interfacing to the engine-side interface member, and a top V-shaped connection formation above the engine core and pair of side V-shaped connection formations on opposite lateral sides of the engine core, each V-shaped connection formation being formed by a pair of connection members meeting at a vertex, the vertex of the top V-shaped connection formation joining to the top of the engine-side interface member, the vertices of the side V-shaped connection formations respectively joining to the bottom ends of the engine-side interface member, and the connection members extending forwardly from their respective vertices to join to front fixation points at the core casing.

公开(公告)号：US11643218B2

公开(公告)日：2023-05-09

申请号：US17395049

申请日：2021-08-05

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Bosko Blagojevic

IPC: B64D27/26 ,  F02C7/20 ,  F02K1/80 ,  F01D25/28

CPC classification number: B64D27/26 ,  F02C7/20 ,  B64D2027/262 ,  B64D2027/264 ,  F01D25/28 ,  F02K1/80 ,  F05D2220/323 ,  F05D2240/90

Abstract: An assembly for mounting an aircraft engine to an aircraft includes an engine casing flange having a first annular wall extending radially to terminate at an annular rim. A second flange of an additional engine component mounted aft of the engine casing includes a second annular wall. An aft mount bracket has an annular body extending uninterrupted about the center axis and a spigot extending axially from the annular body, the spigot extending circumferentially about an entire circumference of the annular body. The aft mount bracket is axially disposed between the engine casing flange and the additional engine component, with corresponding holes in the first annular wall, second annular wall and aft mount bracket being circumferentially aligned, and the spigot radially abutting the annular rim of the engine casing flange.

公开(公告)号：US20190249603A1

公开(公告)日：2019-08-15

申请号：US16202194

申请日：2018-11-28

Applicant: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.

Inventor： Seung Min Lee ,  Dong Hun Kim ,  Jong Hwa Lee

IPC: F02C7/20 ,  F23R3/28 ,  F02C3/06 ,  F02C9/16 ,  F02C7/22

CPC classification number: F02C7/20 ,  F02C3/06 ,  F02C7/22 ,  F02C9/16 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/90 ,  F23R3/283 ,  F23R2900/00005 ,  F23R2900/00017

Abstract: A combustor of a gas turbine includes a nozzle plate to accommodate an arrangement of fuel injection nozzles; an outer cap coupled with the nozzle plate while surrounding an outer circumferential periphery of the nozzle plate; a plurality of first protrusions radially protruding from the outer cap toward a center of the outer cap, the first protrusions arranged in a circumferential direction of the outer cap; and a plurality of first guide holes arranged at the outer circumferential periphery of the nozzle plate in a circumferential direction, to be respectively engaged with the first protrusions. Each first guide hole communicates with a linear recess and with a first fixing recess disposed at an end of the linear recess. The combustor, and a gas turbine including the combustor, evenly distribute stress to the nozzle plate and the outer cap, while minimizing thermal deformation of combustor components in a high-temperature operating environment.

公开(公告)号：US20180223726A1

公开(公告)日：2018-08-09

申请号：US15880291

申请日：2018-01-25

Applicant: Ford Global Technologies, LLC

Inventor： Daniel Meckenstock ,  Michael Spurling ,  Marius Sawatzki

IPC: F02B37/18 ,  F02B39/16

CPC classification number: F02B37/183 ,  F02B37/186 ,  F02B39/16 ,  F02B2039/166 ,  F05D2220/40 ,  F05D2240/90 ,  Y02T10/144

Abstract: Methods and systems are provided for an actuator connected to a turbocharger via a connecting arrangement. In one example, a system may include a connection arrangement which yields above a threshold force. The yielding of the connection arrangement may allow the movement of the actuator in a predetermined direction.

公开(公告)号：US20180216488A1

公开(公告)日：2018-08-02

申请号：US15755525

申请日：2016-08-25

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jacques Marcel Arthur BUNEL ,  Emeric D'HERBIGNY ,  Alain Paul MADEC ,  Pierre TINCELIN ,  Benjamin VILLENAVE

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F05D2220/3215 ,  F05D2240/90 ,  F05D2260/201

Abstract: The invention relates to a device (3) for attaching manifolds (1) for cooling the casing (2) of a preferably low-pressure turbine of a turbine engine by air jets, comprising a mounting (4) of said manifolds, shaped such as to keep said manifolds spaced apart from one another and a plurality of elements (5) for supporting said manifold mounting (4), each supporting element being attached to the casing, and connected to said manifold mounting (4) by connection means (6, 6′). Said device is characterised in that it comprises N cooling manifolds (1) and N−1 supporting elements (5), each supporting element (5) being arranged between two adjacent cooling manifolds.

公开(公告)号：US10006309B2

公开(公告)日：2018-06-26

申请号：US14498201

申请日：2014-09-26

Applicant: ANSALDO ENERGIA IP UK LIMITED

Inventor： Willy Heinz Hofmann ,  Philipp Schaefer

IPC: F01D25/30 ,  F02K1/04 ,  F01D9/02 ,  F01D25/28 ,  F02C7/20

CPC classification number: F01D25/30 ,  F01D9/02 ,  F01D25/28 ,  F02C7/20 ,  F02K1/04 ,  F05B2250/711 ,  F05B2250/712 ,  F05B2250/713 ,  F05D2240/90

Abstract: An exhaust diffuser for a gas turbine includes an annular duct. A row of struts is arranged in the duct. In a region downstream of the trailing edges of the struts, the cross-sectional area of the duct decreases to a local minimum and then increases again towards the outlet end of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions.

公开(公告)号：US09976746B2

公开(公告)日：2018-05-22

申请号：US14842872

申请日：2015-09-02

Applicant: General Electric Company

Inventor： Nicholas John Bloom ,  Daniel Kirtley ,  Adam Robert Kahn

IPC: F23R3/60 ,  F23R3/00 ,  F02C3/04 ,  F23R3/10

CPC classification number: F23R3/60 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/90 ,  F05D2260/941 ,  F23M2900/05002 ,  F23R3/002 ,  F23R3/007 ,  F23R3/10 ,  F23R2900/00017

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. Additionally, a heat shield is provided. The heat shield includes an end also received within the slot defined by the annular dome. A mounting assembly attaches the forward end of the liner and the end of the heat shield to the annular dome, such that the forward end of the liner and the end of the heat shield are co-mounted within the slot defined by the annular dome.

公开(公告)号：US09909458B2

公开(公告)日：2018-03-06

申请号：US14613755

申请日：2015-02-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Robertson, Jr. ,  Mark W. Costa ,  Steven Clarkson

IPC: F01B25/26 ,  F01D25/28 ,  F01D25/24 ,  G01D11/30

CPC classification number: F01D25/28 ,  F01D25/24 ,  F05D2230/60 ,  F05D2240/90 ,  F05D2300/121 ,  F05D2300/603 ,  G01D11/30 ,  Y02T50/672

Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.

公开(公告)号：US09863325B2

公开(公告)日：2018-01-09

申请号：US15306913

申请日：2015-04-27

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Kevin Morgane Lemarchand

IPC: F02C7/36 ,  F02C7/32 ,  F01D25/16 ,  F02C7/06 ,  F02C3/04 ,  F02K3/06

CPC classification number: F02C7/32 ,  F01D25/162 ,  F02C3/04 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2240/90 ,  F05D2250/75 ,  F05D2260/4031 ,  F05D2260/40311 ,  Y02T50/671

Abstract: An assembly for an aircraft turbine engine, including a rolling bearing bracket defining an inner space on either side thereof; a rotary assembly including a first gear; a housing for drawing mechanical power including a second gear mating with the first gear; a shaft for drawing mechanical power, inserted into the housing and rotated by the second gear, the shaft passing through a first opening of the bracket. The assembly includes a mounting device for mounting the housing on the bearing bracket, the mounting device passing through a second opening via the bracket, the mounting device passing through a second opening via the bracket, the second opening being configured so as to allow the housing to be inserted into the space.