公开(公告)号：US12065947B2

公开(公告)日：2024-08-20

申请号：US18090197

申请日：2022-12-28

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Sam J. Stoughton ,  Kevin Lee Kirkeng ,  Jacob P. Miller ,  Reddi Hari Prasad Reddy Mylapalli ,  Paul Trimby ,  Jaeyong Kim

IPC: F01D5/22 ,  F02C7/28

CPC classification number: F01D5/225 ,  F02C7/28 ,  F05D2240/55 ,  F05D2250/283 ,  F05D2260/31 ,  F05D2260/96

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An inner shroud damper for a gas turbine engine includes: at least one carrier including a joint to couple to an inner shroud, the at least one carrier having a first side and a second side, and at least one mass damper coupled to the at least one carrier.

公开(公告)号：US12044172B2

公开(公告)日：2024-07-23

申请号：US18148559

申请日：2022-12-30

Applicant: General Electric Company

Inventor： Vaishnav Raghuvaran ,  Sesha Subramanian ,  Hari Krishna Meka ,  Vishnu Vardhan Venkata Tatiparthi ,  Raghuveer Chinta ,  Daniel O'Brien ,  Sai Raju Ippili ,  Michael Thomas Hogan

IPC: F01D25/12 ,  F01D25/14 ,  F02C7/18 ,  F02C7/28

CPC classification number: F02C7/18 ,  F01D25/12 ,  F01D25/14 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/201

Abstract: A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.

公开(公告)号：US11898494B2

公开(公告)日：2024-02-13

申请号：US17502502

申请日：2021-10-15

Applicant: General Electric Company

Inventor： Nicholas John Bloom ,  Michael Alan Stieg ,  Brian Christopher Towle

IPC: F02C7/20 ,  F02C7/28 ,  F23R3/60 ,  F23R3/50 ,  F23R3/00

CPC classification number: F02C7/20 ,  F02C7/28 ,  F23R3/007 ,  F23R3/50 ,  F23R3/60 ,  F05B2280/2004

Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.

公开(公告)号：US11879396B2

公开(公告)日：2024-01-23

申请号：US17992019

申请日：2022-11-22

Applicant: Raytheon Technologies Corporation

Inventor： Michael A Beinor ,  Timothy J. Castaldo ,  Christopher M. Valva ,  Nasr A. Shuaib ,  Mitchell D. Panton

IPC: F02C7/28 ,  F01D25/18 ,  F02C7/06

CPC classification number: F02C7/28 ,  F01D25/183 ,  F02C7/06 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2260/232 ,  F05D2260/98

Abstract: A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward.

公开(公告)号：US20240003301A1

公开(公告)日：2024-01-04

申请号：US18130270

申请日：2023-04-03

Applicant: Raytheon Technologies Corporation

Inventor： Caroline Karanian ,  Steven D. Porter ,  John T. Ols

IPC: F02C7/28 ,  F02C7/12

CPC classification number: F02C7/28 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/56 ,  F05D2260/20

Abstract: A brush seal system includes a component including a first mating surface. The brush seal system further includes a brush seal including a brush seal backing plate, a retaining ring, and a plurality of bristles retained between the brush seal backing plate and the retaining ring. The brush seal backing plate includes a second mating surface mounted to the first mating surface. The brush seal system further includes at least one cooling channel extending from an exterior side of the component to an interior side of the component so as to bypass the brush seal.

公开(公告)号：US11846207B2

公开(公告)日：2023-12-19

申请号：US17685523

申请日：2022-03-03

Applicant: General Electric Company

Inventor： David Alan Frey ,  Jeffrey Douglas Rambo ,  Alexander Martin Sener ,  Kirk Douglas Gallier

IPC: F01D9/04 ,  F01D25/24 ,  F02C7/28 ,  F01D5/18 ,  F01D5/28

CPC classification number: F01D9/042 ,  F01D5/18 ,  F01D25/246 ,  F02C7/28 ,  F01D5/282 ,  F01D5/284 ,  F05D2230/60 ,  F05D2300/6033

Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.

公开(公告)号：US20230399982A1

公开(公告)日：2023-12-14

申请号：US17806185

申请日：2022-06-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Tibor URAC ,  Sébastien BERGERON

IPC: F02C7/28 ,  F01D11/00

CPC classification number: F02C7/28 ,  F01D11/003 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2230/60 ,  F05D2260/60

Abstract: A seal for an aircraft engine includes an annular body receivable in interference fit in a radial spacing defined between inner and outer cylindrical components of the aircraft engine, the annular body defining a central axis coaxial with the inner and outer cylindrical components, the annular body including an inner portion defining an inner diameter, an outer portion defining an outer diameter, and an intermediate portion extending between the inner and outer portions. The outer portion is slidably engageable to the outer cylindrical component at an outer contact sealing portion of the annular body. One of the inner portion and the outer portion defines at least one cut extending from the one of the inner portion and the outer portion toward another one of the inner portion and the outer portion. A method for sealing a radial spacing between coaxial cylindrical components in an aircraft engine is also described.

公开(公告)号：US11815017B2

公开(公告)日：2023-11-14

申请号：US16850848

申请日：2020-04-16

Applicant: Raytheon Technologies Corporation

Inventor： Arun K. Theertham

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

CPC classification number: F02C7/00 ,  F01D11/005 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2260/606

Abstract: A fan blade platform assembly includes a pressure side platform half that includes a first attachment wall, a first gas path wall, and a first connecting wall attached to both the first attachment wall and the first gas path wall. A suction side platform half includes a second attachment wall, a second gas path wall, and a second connecting wall attached to both the second attachment wall and the second gas path wall. A seal engages the pressure side platform half and the suction side platform half.

公开(公告)号：US20230353009A1

公开(公告)日：2023-11-02

申请号：US17661062

申请日：2022-04-28

Applicant: Garrett Transportation I Inc

Inventor： Milan Nejedly ,  Petr Koplik ,  Vit Houst

IPC: H02K5/22 ,  H02K7/14 ,  H02K7/18 ,  H02K11/33 ,  H02K15/00 ,  F02C7/36 ,  F02C7/28

CPC classification number: H02K5/225 ,  H02K7/14 ,  H02K7/1823 ,  H02K11/33 ,  H02K15/0062 ,  F02C7/36 ,  F02C7/28 ,  F05D2240/11

Abstract: An electrical connector arrangement for a turbomachine includes a support structure and a terminal with a terminal post projecting from the support structure along an axis. The electrical connector arrangement includes a connection stack that is supported by the terminal and arranged along the axis of the terminal post. The connection stack includes a bus bar that is electrically connected to the terminal post and that extends from the terminal post and the support structure. The connection stack includes a first deformable seal member and a second deformable seal member. The first deformable seal member is deformed against the terminal post to define an inner radial seal within the connection stack. The second deformable seal member is deformed against the support structure to define an outer radial seal within the connection stack.

公开(公告)号：US20230265762A1

公开(公告)日：2023-08-24

申请号：US18072921

申请日：2022-12-01

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Thomas Joseph Lipinski

IPC: F01D11/02 ,  F02C7/28

CPC classification number: F01D11/025 ,  F02C7/28 ,  F05D2240/55 ,  F05D2220/32

Abstract: A turbine engine comprising an engine core, a plurality of circumferentially arranged vanes, and a floating seal. The plurality of circumferentially arranged vanes forming an upper band and a lower band. The floating seal being carried by at least one respective vane of the plurality of circumferentially arranged vanes. The floating seal having a ring and at least one dynamic seal.