公开(公告)号：US20240247595A1

公开(公告)日：2024-07-25

申请号：US18444100

申请日：2024-02-16

Applicant: General Electric Company

Inventor： Nicholas R. Overman

IPC: F01D11/00

CPC classification number: F01D11/005 ,  F05D2240/57 ,  F05D2260/38

Abstract: A sealing system for sealing between components. The sealing system includes a first component, a second component, and a seal assembly including a seal member. The first component includes a first component surface, and the second component includes a second component surface. The second component surface is oriented in a direction transverse to the first contact surface. The seal member has a plurality of contact surfaces including a first contact surface and a second contact surface. The first contact surface is configured to contact the first component surface and to slide relative to the first component surface. The second contact surface is configured to contact the second component surface and to slide relative to the second component surface. The second contact surface is oriented in a direction transverse to the first contact surface.

公开(公告)号：US20240229667A1

公开(公告)日：2024-07-11

申请号：US18150664

申请日：2023-01-05

Applicant: General Electric Company

Inventor： Rodolfo Mena Dominguez

IPC: F01D11/00 ,  F01D25/16

CPC classification number: F01D11/003 ,  F01D11/005 ,  F01D25/164 ,  F05D2240/55

Abstract: Separators for use with gas turbine engines are disclosed herein. An example apparatus disclosed herein includes a rod and a joint to be disposed within a scaling wall, the joint including a bushing portion, the rod extending through the bushing portion and a disk portion including a slot, the disk portion concentric with the bushing portion.

公开(公告)号：US12018567B2

公开(公告)日：2024-06-25

申请号：US17828670

申请日：2022-05-31

Applicant: Pratt & Whitney Canada Corp.

Inventor： Philippe Savard ,  Guy Lefebvre

IPC: F01D11/00

CPC classification number: F01D11/003 ,  F01D11/005 ,  F05D2240/55 ,  F05D2260/30

Abstract: An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a seal carrier, a seal land, a seal ring, a plate and a fastener. The seal carrier has an annular groove and extends between a first side and a second side. The seal land is opposite the annular groove. The seal ring seals a gap between the seal carrier and the seal land. The seal ring is seated in the annular groove. The plate is at the second side of the seal carrier. The fastener includes a head and an elongated member connected to the head. The head is at the first side of the seal carrier. The elongated member projects out from the head through the seal carrier, the seal ring and the plate. The elongated member is bonded to the plate.

公开(公告)号：US20240191631A1

公开(公告)日：2024-06-13

申请号：US18528300

申请日：2023-12-04

Applicant: DOOSAN ENERBILITY CO., LTD

Inventor： Hyuk Hee LEE

IPC: F01D11/00

CPC classification number: F01D11/005 ,  F05D2240/80

Abstract: Proposed is a turbine vane platform sealing assembly in which compressed air is prevented from leaking to a turbine vane to improve power generation efficiency. The turbine vane platform sealing assembly includes a first sealing member inserted into a first groove formed in a turbine vane platform in a first direction, the first sealing member extending in the first direction, a second sealing member inserted into a second groove formed in a second direction intersecting the first direction of the turbine vane platform, with an end part of the second sealing member being in contact with an upper surface of the first sealing member, and the third sealing member having a portion formed by extending in the first direction and a remaining portion formed by bending in the second direction at a bend line at which the first sealing member and the second sealing member contact.

公开(公告)号：US12000288B2

公开(公告)日：2024-06-04

申请号：US17246912

申请日：2021-05-03

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III ,  Bryan P. Dube ,  Wojciech Lipka

IPC: F01D5/00 ,  F01D11/00 ,  F01D25/00 ,  F01D25/24

CPC classification number: F01D11/005 ,  F01D11/003 ,  F01D25/005 ,  F01D25/246 ,  F05D2230/90 ,  F05D2240/11

Abstract: A flow path component assembly includes a flow path component that has a platform that extends from a first circumferential side to a second circumferential side. The platform has a first radius of curvature between the first circumferential side and the second circumferential side. A coating is arranged on a portion of the platform near the first circumferential side. The coating has a second radius of curvature. The second radius of curvature is larger than the first radius of curvature.

公开(公告)号：US11994039B2

公开(公告)日：2024-05-28

申请号：US17711405

申请日：2022-04-01

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Kirk Douglas Gallier ,  Charles William Craig, III

IPC: F01D9/04 ,  F01D11/00 ,  F01D25/24

CPC classification number: F01D25/246 ,  F01D9/042 ,  F01D11/005 ,  F05D2300/6033 ,  Y02T50/60

Abstract: A gas turbine engine having a rotor blade stage with a plurality of circumferentially spaced rotors, a nozzle stage adjacent the rotor blade stage and including an outer nozzle end, at least one stop, and a shroud. The shroud having a forward end positioned radially outward from the circumferentially spaced rotor blades, and an aft end axially aft of the forward end. The at least one stop confronting at least a portion of the outer nozzle end.

公开(公告)号：US20240117747A1

公开(公告)日：2024-04-11

申请号：US18263943

申请日：2022-01-31

Applicant: SAFRAN AERO BOOSTERS

Inventor： Théo Robin Thomas BOUR ,  Matthieu Edouard Henri DROELLER ,  Christophe Joseph Richard Gillain REMY

IPC: F01D9/04 ,  F01D11/00

CPC classification number: F01D9/042 ,  F01D9/041 ,  F01D11/005

Abstract: A stator vane assembly for a compressor of an aircraft turbine engine includes an inner shroud, an outer shroud and stator vanes. The stator vanes are attached only to the inner shroud and are in non-immobilizing mechanical contact with the outer shroud.

公开(公告)号：US11920487B1

公开(公告)日：2024-03-05

申请号：US17956877

申请日：2022-09-30

Applicant: Raytheon Technologies Corporation

Inventor： Thomas E. Clark ,  Andrew E. Breault

IPC: F01D25/14 ,  F01D11/00 ,  F02C7/18 ,  F02C7/28

CPC classification number: F01D25/14 ,  F01D11/005 ,  F02C7/18 ,  F02C7/28 ,  F05D2250/75 ,  F05D2260/232 ,  F05D2260/31 ,  F05D2260/37

Abstract: A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is positioned radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features. A bifurcation feature is positioned downstream of the first seal. The bifurcation feature is configured to direct a portion of an airflow through the first seal into a cooling air passage. A second seal contacts the bifurcation and the first seal, such that fluid radially inward of the bifurcation feature.

公开(公告)号：US20240011406A1

公开(公告)日：2024-01-11

申请号：US18474410

申请日：2023-09-26

Applicant: Hamilton Sundstrand Corporation

Inventor： Brent J. Merritt ,  Craig M. Beers

IPC: F01D11/00 ,  F01D25/28

CPC classification number: F01D11/005 ,  F01D25/28 ,  F05D2220/34 ,  F05D2240/55 ,  F05D2250/18 ,  F05D2250/90 ,  F05D2260/31

Abstract: A seal plate for a rotary machine includes a hub centered on a central axis of the rotary machine, a disk portion extending radially outwards from the hub, and a variable lattice structure in an interior of the seal plate. The variable lattice structure includes a first region of the seal plate having a first lattice structure, and a second region of the seal plate having a second lattice structure. The second lattice structure of the second region is denser than the first lattice structure of the first region. The second region is a deflection region, a stress region, or an energy containment region of the seal plate.

公开(公告)号：US11828183B2

公开(公告)日：2023-11-28

申请号：US17783629

申请日：2020-12-01

Applicant: Safran Aircraft Engines

Inventor： Paul Ghislain Albert Levisse ,  Olivier Belmonte ,  Fabien Roger Gaston Caty ,  Amelie Argie Antoinette Chassagne

IPC: F01D1/24 ,  F01D11/00 ,  F01D25/00

CPC classification number: F01D1/24 ,  F01D11/005 ,  F01D25/00 ,  F05D2260/40311 ,  F05D2260/98

Abstract: Disclosed is a turbomachine (10) with counter-rotating turbine for an aircraft, comprising: —a high-pressure body, —a low-pressure counter-rotating turbine (22), —a planetary-type mechanical epicyclic reduction gear (42), —a guide bearings (56-62) for the turbine shafts (36, 38), characterised in that said reduction gear (42) and certain of the bearings (60, 62) are housed in a lubrication chamber (86) supplied with oil and comprising dynamic seals (86a-86d), and in that the turbomachine comprises circuits (C1, C2) for pressurising these seals.