公开(公告)号：US12129768B2

公开(公告)日：2024-10-29

申请号：US18228382

申请日：2023-07-31

Applicant: RTX Corporation

Inventor： Lawrence A. Binek ,  David W. Morganson ,  Jesse R. Boyer

IPC: F01D25/28 ,  F01D25/24

CPC classification number: F01D25/285 ,  F01D25/24 ,  F01D25/243 ,  F01D25/246 ,  F05D2230/60 ,  F05D2230/64 ,  F05D2230/68

Abstract: A unitized build assembly for a gas turbine engine includes an exhaust duct, a hot section with a locking structure and including a combustor and turbine section. The hot section at least partially circumferentially surrounds the exhaust duct. The build assembly includes a compressor section with an interface structure and is proximal to the hot section. The hot section at least partially circumferentially surrounds at least part of the compressor section and the locking structure is configured to engage the interface structure to limit movement of the hot section relative to the compressor section.

公开(公告)号：US20240352871A1

公开(公告)日：2024-10-24

申请号：US18761607

申请日：2024-07-02

Applicant: RTX Corporation

Inventor： David E. Bitter ,  William John Oldach ,  William C. Sheridan ,  Matthew Michael Massaro

IPC: F01D25/06 ,  F01D9/04

CPC classification number: F01D25/06 ,  F01D9/041 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2260/96

Abstract: A hollow vane assembly including an open body including an interior; a cover brazed to the open body to form at least one flow passage; and at least one surface feature on an interior surface of the cover.

公开(公告)号：US12116931B2

公开(公告)日：2024-10-15

申请号：US17510785

申请日：2021-10-26

Applicant: Safran Nacelles

Inventor： Denis Guillois ,  Fabienne Quenu ,  Anne Mounier ,  Franck Philippe Gérald Zaganelli

IPC: F02C7/045

CPC classification number: F02C7/045 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2230/60

Abstract: An air intake of a turbojet engine nacelle includes an air intake lip, an annular structure, a rear partition, and at least one acoustic attenuation structure. The annular structure includes at least a part of an outer fairing and an inner fairing joined to each other by the air intake lip. The rear partition is connected to the inner fairing. The acoustic attenuation structure is attached to the inner fairing of the annular structure. At least part of the outer fairing, the air intake lip and the inner fairing are integral with each other.

公开(公告)号：US12115623B2

公开(公告)日：2024-10-15

申请号：US17983815

申请日：2022-11-09

Applicant: Pratt & Whitney Canada Corp.

Inventor： Bernard Chow ,  Gerard Theriault

IPC: B25B13/48 ,  F02C7/20 ,  F16B43/00

CPC classification number: B25B13/48 ,  F02C7/20 ,  F16B43/00 ,  F05D2230/60 ,  F05D2260/31

Abstract: An assembly method is provided during which a first component is arranged with a second component. The first component is secured to the second component using a fastener assembly. The fastener assembly includes a fastener element and a washer. The fastener element includes a wrenching feature. The washer has a full-hoop annular body with a cylindrical outer surface. The securing includes: mating a socket device with the fastener element and the washer, the socket device engaging the wrenching feature and the cylindrical outer surface; and rotating the fastener element about an axis using the socket device to tighten the fastener assembly and clamp the washer axially between the first component and the fastener element. The socket device centers the washer to the fastener element during the rotating.

公开(公告)号：US12103694B2

公开(公告)日：2024-10-01

申请号：US17510626

申请日：2021-10-26

Applicant: Safran Nacelles

Inventor： Gina Ferrier ,  Patrick Boileau

IPC: B64D33/02 ,  B64D29/06 ,  F02C7/04

CPC classification number: B64D33/02 ,  B64D29/06 ,  F02C7/04 ,  B64D2033/0206 ,  B64D2033/0273 ,  B64D2033/0286 ,  F05D2230/60

Abstract: An air intake for a nacelle of an aircraft engine includes a substantially cylindrical outer wall, a substantially cylindrical inner wall, a front lip, a front mounting flange, and a support structure. The front lip connects the substantially cylindrical inner wall and the substantially cylindrical outer wall. The front mounting flange is configured to cooperate with a rear flange of a wall of the aircraft engine forming a fan casing. The support structure comprises a lower end configured to be secured to the fan casing, by the rear flange, and an upper end in contact at least with a downstream portion of the outer wall. The support structure includes access apertures configured to be crossed by maintenance tools during operations of maintenance of the air intake.

公开(公告)号：US12097972B2

公开(公告)日：2024-09-24

申请号：US17648971

申请日：2022-01-26

Applicant: Gulfstream Aerospace Corporation

Inventor： Andrew Martin ,  Kristin Medin ,  Scott Bohanan

IPC: B64F1/00 ,  A45B23/00 ,  F02C7/04

CPC classification number: B64F1/005 ,  F02C7/04 ,  A45B2023/0081 ,  F05D2220/323 ,  F05D2230/60

Abstract: An engine inlet cover and a method for covering an engine inlet are provided. A method for covering an engine inlet includes providing a collapsible cover comprising a connection pin defining an axis; a frame including interconnected arms; and a web. Further, the method includes storing the collapsible cover in a stowed configuration in which the arms are aligned. Also, the method includes rotating the arms from the stowed configuration to an operating configuration in which the arms are radially spaced about the axis, enclosing the frame in the operating configuration with the web to define an interior volume, and placing the cover over the engine inlet.

公开(公告)号：US20240309774A1

公开(公告)日：2024-09-19

申请号：US18600604

申请日：2024-03-08

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Daniel E. Molnar, JR. ,  Robert W. Heeter ,  Gregory J. Hebert

IPC: F01D17/16

CPC classification number: F01D17/162 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2260/60

Abstract: A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes an actuation assembly having a pass through actuation rod enabling the single actuation assembly to rotate both of the tip and hub segments.

公开(公告)号：US20240301827A1

公开(公告)日：2024-09-12

申请号：US18179660

申请日：2023-03-07

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Alan W. Smith ,  Sara Karaffa

IPC: F02C7/12 ,  F02C6/20

CPC classification number: F02C7/12 ,  F02C6/20 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2230/60 ,  F05D2260/20

Abstract: Gas turbine engines include an engine frame defining an inner radial surface, a shaft rotatably mounted in the engine frame along a longitudinal axis, and an electric machine that includes a rotor coupled to the shaft and a stator coupled to the engine frame and defining an outer radial surface. In some gas turbine engines, the engine frame includes inlet and outlet fluid passages, each extending to a portion of the inner radial surface. The portion of the inner radial surface of the engine frame is spaced from the outer radial surface of the stator to form an annular fluid passage around the stator of an electric machine. The annular fluid passage is configured to direct a cooling fluid around the stator to remove heat from the stator. Some gas turbine engines include two or more positioning keys configured to fix the stator relative to the engine frame.

公开(公告)号：US12084979B2

公开(公告)日：2024-09-10

申请号：US18326782

申请日：2023-05-31

Applicant: MTU Aero Engines AG

Inventor： Alexander Rauschmeier

IPC: F01D17/16

CPC classification number: F01D17/16 ,  F05D2230/60 ,  F05D2230/70

Abstract: The invention is directed to a guide vane device for a guide vane adjustment of a turbomachine, comprising a guide vane, which has a shaft extending along an adjustment axis of the guide vane, as well as an adjusting lever, which forms a connecting element for connection to an outer end of the shaft, wherein, at its outer end, the shaft has a three-dimensional front surface with at least one beveled region, the connecting element surrounds, at least in sections, the outer end of the shaft in a sleeve-like manner and is joined to the outer end in a form-fitting manner, and the guide vane device forms an interference fit between the connecting element and the outer end of the shaft.

公开(公告)号：US12071859B2

公开(公告)日：2024-08-27

申请号：US17908111

申请日：2020-12-04

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Satoshi Kumagai ,  Shunsuke Mizumi ,  Koji Ishibashi ,  Juichi Kodera

IPC: F01D25/24 ,  G01B11/24 ,  G06F30/17

CPC classification number: F01D25/24 ,  G01B11/24 ,  G06F30/17 ,  F05D2230/60 ,  F05D2260/81

Abstract: In an assembly method for a turbine, measured shape data is acquired by measuring a shape for each of a plurality of casing components in a state in which the plurality of casing components are not fastened to each other. self-weighted state shape data, which is shape data when self-weight is applied, is created for each of the plurality of casing components. A reference shape model is corrected based on a difference between the measured shape data of a target measurement part and the self-weighted state shape data of the target measurement part. By using the corrected shape model, fastened state shape data, which is shape data in a state in which the plurality of casing components are fastened to each other, is estimated for each of the plurality of casing components.