公开(公告)号：US12129765B2

公开(公告)日：2024-10-29

申请号：US18388567

申请日：2023-11-10

Applicant: General Electric Company

Inventor： Krzysztof Andrzej Woszczak ,  William Patrick Rusch ,  Samuel Nathan Merrill ,  Ejiro Anthony Oruaga ,  David John Nelmes ,  Justyna Ludwika Wojdyło ,  John Francis Nolan

IPC: F01D25/24 ,  F01D21/00 ,  F01D25/02 ,  F01D25/28

CPC classification number: F01D25/243 ,  F01D21/003 ,  F01D25/02 ,  F01D25/28 ,  F05D2230/644 ,  F05D2240/14 ,  F05D2250/11 ,  F05D2260/30

Abstract: A method and system for aligning a component within a turbine casing, and a related turbine casing, are disclosed. In a top-on position, a location of a reference point and another, vertically spaced reference point on the lower casing are measured. After removing at least the upper casing, the reference points' locations are measured again, and the locations of a reference point on an upper surface of the HJ flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a HJ flange surface distortion adjustment. The component support position is adjusted by the prediction offset value to improve alignment.

公开(公告)号：US12044181B1

公开(公告)日：2024-07-23

申请号：US18297589

申请日：2023-04-07

Applicant: Raytheon Technologies Corporation

Inventor： Steven Michael Danley ,  Ahmad Sajad Delawar ,  Ryan K. Snyder

IPC: F02C7/32 ,  F16M13/02

CPC classification number: F02C7/32 ,  F16M13/02 ,  F05D2260/30

Abstract: An assembly for mounting an auxiliary component to an engine case for a gas turbine engine includes a support bracket and a locator. The locator includes a fusible guide pin extending at least partially into a first aperture disposed in the support bracket, and a catcher pin extending at least partially into a second aperture disposed in the support bracket. The fusible guide pin is configured to fracture to absorb energy while the catcher pin limits system displacement during and post an overload event, thus reducing the energy transmitted to the auxiliary component (e.g., a gearbox housing). The locator can further include an anti-rotation pin extending from the plate member and configured to be received by the auxiliary component. The anti-rotation pin prevents rotation of the locator, about a third pin of the locator, with respect to the auxiliary component when the fusible guide pin is broken.

公开(公告)号：US20240218834A1

公开(公告)日：2024-07-04

申请号：US18603036

申请日：2024-03-12

Applicant: GE Infrastructure Technology LLC

Inventor： Robert Jamiolkowski ,  Damian Wolff ,  Adam Wisniewski

IPC: F02C7/24 ,  F01D25/14

CPC classification number: F02C7/24 ,  F01D25/145 ,  F05D2220/32 ,  F05D2230/642 ,  F05D2240/128 ,  F05D2260/231 ,  F05D2260/30

Abstract: A system may include an insulation mount assembly configured to mount insulation within a component of an exhaust diffuser of a combustion system. The insulation mount assembly includes an insulation cover plate configured to cover the insulation over a wall of the component, and a plurality of mounting clips configured to extend partially over the insulation plate and couple to the wall of the component. Each clip of the plurality of mounting clips is configured to enable movement of the insulation cover plate in a first direction along a surface of the wall and block movement of the insulation cover plate in a second direction crosswise to the surface of the wall.

公开(公告)号：US12024474B2

公开(公告)日：2024-07-02

申请号：US17850430

申请日：2022-06-27

Applicant: RTX CORPORATION

Inventor： David C. Jarmon

IPC: C04B35/80 ,  B28B1/00 ,  B28B11/12 ,  C04B35/01 ,  C04B35/565 ,  C04B35/571 ,  C04B35/573 ,  C04B35/622 ,  C04B35/634 ,  C04B35/638 ,  C04B35/64 ,  C04B35/76 ,  C04B35/83 ,  C04B37/00 ,  D03D25/00 ,  F01D5/00 ,  F01D9/00 ,  F01D11/00 ,  F01D25/00 ,  F01D25/24 ,  F01D25/28 ,  F01D25/30 ,  F02C7/28 ,  F02K1/82 ,  F23R3/00 ,  F23R3/28 ,  F23R3/60

CPC classification number: C04B35/80 ,  B28B1/001 ,  B28B1/002 ,  B28B11/12 ,  C04B35/01 ,  C04B35/565 ,  C04B35/571 ,  C04B35/573 ,  C04B35/62227 ,  C04B35/634 ,  C04B35/638 ,  C04B35/64 ,  C04B35/76 ,  C04B35/83 ,  C04B37/001 ,  D03D25/005 ,  F01D5/00 ,  F01D9/00 ,  F01D11/00 ,  F01D25/00 ,  F01D25/005 ,  F01D25/243 ,  F01D25/246 ,  F01D25/28 ,  F01D25/30 ,  F02C7/28 ,  F02K1/822 ,  F23R3/002 ,  F23R3/007 ,  F23R3/283 ,  F23R3/60 ,  C04B2235/48 ,  C04B2235/5208 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/5252 ,  C04B2235/5256 ,  C04B2235/612 ,  C04B2235/614 ,  C04B2235/616 ,  C04B2237/38 ,  C04B2237/385 ,  C04B2237/60 ,  C04B2237/61 ,  C04B2237/80 ,  C04B2237/84 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2230/314 ,  F05D2240/91 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2300/6033 ,  F23M2900/05004 ,  Y02T50/60

Abstract: A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

公开(公告)号：US11927101B1

公开(公告)日：2024-03-12

申请号：US17901769

申请日：2022-09-01

Applicant: Solar Turbines Incorporated

Inventor： Megan K. Waller ,  Jeffrey B. Stewart ,  George Prater ,  James Maleski ,  Victor Antonio Chagala Galicia ,  Antonio Fajardo Celis ,  Marius Dumitrascu ,  Jeffrey Tarczy

IPC: F01D11/08 ,  F02C7/28

CPC classification number: F01D11/08 ,  F02C7/28 ,  F05D2260/30

Abstract: Tip shrouds or other shrouds with multi-slope geometries are generally implemented using segments, since performing the necessary cut for an alternative split-ring design is difficult given conventional cutting processes. However, a segmented design generally results in more leakage, relative to a split-ring design. Accordingly, a split-ring multi-slope design is disclosed that can be more easily manufactured. In particular, a continuous ring may be cut along a linear path to produce a split ring, and then the ends of the split ring may be machined to form complementary shiplap portions. The split ring may then be compressed for installation by overlapping the shiplap portions, to form a seal against leakage through the shroud.

公开(公告)号：US11913357B2

公开(公告)日：2024-02-27

申请号：US16623560

申请日：2017-07-05

Applicant: Siemens Energy, Inc.

Inventor： Charalambos Polyzopoulos

IPC: F01D9/02 ,  F01D11/00 ,  F02C7/28

CPC classification number: F01D9/023 ,  F01D11/005 ,  F02C7/28 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/30

Abstract: A gas turbine sealing interface to seal a gap between a transition duct and a turbine section component is provided. The transition duct includes an outlet exit frame including at least one fastener hole. The turbine section component includes a first stage vane structure including an upstream lip. A seal couples the outlet exit frame to the first stage turbine vane structure. An L-shaped rail including a flat portion and a lipped portion disposed perpendicularly to the flat portion. The seal is secured to the outlet exit frame via the L-shaped rail. An upstream portion of the seal includes a U-shaped cross section forming a first groove. A downstream portion of the seal comprises a groove which engages the upstream lip of the first stage turbine vane structure. A gas turbine engine including a radially inner sealing interface and a radially outer sealing interface is also provided.

公开(公告)号：US11873727B2

公开(公告)日：2024-01-16

申请号：US17231817

申请日：2021-04-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Jorge Mario Rochin Machado ,  David Garza Maldonado ,  Gerardo Plata Contreras ,  Maria Isabel Romero Contreras ,  Claudia Priscila Sandoval Camacho

IPC: F01D25/28 ,  B66F7/26 ,  F02C7/20

CPC classification number: F01D25/285 ,  B66F7/26 ,  F02C7/20 ,  F05D2220/32 ,  F05D2260/02 ,  F05D2260/30

Abstract: A hoist for lifting at least a portion of a gas engine assembly includes a support member including an upper portion, a lower portion, and a connecting portion extending therebetween. The hoist also includes an elongate member coupled to the lower portion of the support member and extending substantially orthogonally to the lower portion, and at least one bracket slidably engaged with the elongate member and axially translatable along a length of the elongate member. In addition, the hoist includes a plurality of linkage members coupled to the at least one bracket, where each linkage member of the plurality of linkage members is configured to attach to at least a portion of the gas engine assembly.

公开(公告)号：US20240003267A1

公开(公告)日：2024-01-04

申请号：US18251930

申请日：2021-11-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Clément Emile André CAZIN ,  Pascal Cédric TABARIN ,  Sébastien Serge Francis CONGRATEL ,  Nicolas Paul TABLEAU

IPC: F01D25/24 ,  F01D9/04

CPC classification number: F01D25/246 ,  F01D9/04 ,  F05D2240/14 ,  F05D2260/96 ,  F05D2260/30

Abstract: A turbine ring assembly extending around a longitudinal axis and comprises:



a plurality of ring angular sectors made of CMC material circumferentially arranged in such a way as to form a turbine ring, each sector comprising a base from which an upstream leg and a downstream leg extend radially,
a ring support structure comprising:
a spacer extending around the sectors and comprising a downstream flange in such a way that the downstream leg of each sector is held against the downstream flange,
a upstream force-absorbing plate extending circumferentially around the longitudinal axis in such a way as to be in contact with the upstream leg of each sector and fixed to an upstream area of the spacer which extends in extension of the upstream leg.

公开(公告)号：US20230399956A1

公开(公告)日：2023-12-14

申请号：US18456126

申请日：2023-08-25

Applicant: RTX CORPORATION

Inventor： Jason Husband ,  James Glaspey ,  Aaron John Pepin

IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28 ,  F01D11/00 ,  F01D5/02

CPC classification number: F01D5/3053 ,  F01D5/147 ,  F01D5/282 ,  F01D11/008 ,  F01D5/02 ,  F01D5/3038 ,  F05D2240/301 ,  F05D2240/80 ,  F05D2260/30 ,  F05D2300/603 ,  F05D2300/702 ,  F05D2260/31

Abstract: A rotor assembly for a gas turbine engine includes a rotatable hub that has a main body and an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels. An array of airfoils are circumferentially distributed about the outer periphery. Each one of the airfoils includes an airfoil section extending from a root section received in the annular channels. Retention pins extend through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach each root section to the hub.

公开(公告)号：US11821321B2

公开(公告)日：2023-11-21

申请号：US17880074

申请日：2022-08-03

Applicant: Raytheon Technologies Corporation

Inventor： Timothy R. Dyer ,  Abhijeet Shrestha

IPC: F01D11/00 ,  F02C7/28 ,  F01D5/02

CPC classification number: F01D11/003 ,  F01D5/027 ,  F02C7/28 ,  F05D2230/60 ,  F05D2240/55 ,  F05D2260/15 ,  F05D2260/30 ,  F05D2300/226 ,  F05D2300/611

Abstract: A machine has: an outer member; an inner member mounted for rotation about an axis relative to the outer member; and a seal system. The seal system has: a seal housing mounted to the outer member; one or more seal rings held by the seal housing and having an inner diameter surface; and a seal runner mounted to the inner member and having a first outer diameter surface portion contacting or facing the inner diameter surface of the one or more seal rings. The seal runner has a circumferential array of mounting features. One or more weights are mounted to one or more of the mounting features.