公开(公告)号：US20170248028A1

公开(公告)日：2017-08-31

申请号：US15053276

申请日：2016-02-25

Applicant: General Electric Company

Inventor： Jan Christopher Schilling

IPC: F01D11/24

CPC classification number: F01D11/24

Abstract: A gas turbine engine clearance control system includes a cooling air passage extending from a cooling air inlet port to a cooling air outlet port. The cooling air inlet port and outlet port are formed within an external surface of a compressor casing of a compressor and are also axially spaced on the external surface of the compressor casing. The cooling air passage extends from the cooling air inlet port radially inwardly to at least one of a flange joint, a radially outer surface of a compressor casing ring, and a radially outer surface of a connector case. The cooling air passage further extends aftward along the radially outer surfaces of the connector case and the compressor casing ring. The cooling air passage further extends radially outward to the cooling air outlet port. Selectively supplying cooling air to the cooling air passage controls a rotor tip clearance between a rotor tip of a rotor blade of the compressor and an inner surface of the compressor casing ring and further controls an interstage seal clearance between an inner band and a rotor spool of the compressor.

公开(公告)号：US20240141804A1

公开(公告)日：2024-05-02

申请号：US18398597

申请日：2023-12-28

Applicant: General Electric Company

Inventor： Jan Christopher Schilling ,  Andrew John Breslin ,  Bryce Loring Heitman

IPC: F01D25/24

CPC classification number: F01D25/246 ,  F01D9/04

Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

公开(公告)号：US11879349B2

公开(公告)日：2024-01-23

申请号：US17565528

申请日：2021-12-30

Applicant: General Electric Company

Inventor： Jan Christopher Schilling ,  Andrew John Breslin ,  Bryce Loring Heitman

IPC: F01D25/24 ,  F01D9/04 ,  F01D11/12

CPC classification number: F01D25/246 ,  F01D9/04 ,  F01D11/12 ,  Y02T50/60

Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

公开(公告)号：US20190284958A1

公开(公告)日：2019-09-19

申请号：US16462355

申请日：2015-05-06

Applicant: General Electric Company

Inventor： Jan Christopher Schilling ,  Andrew John Breslin ,  Bryce Loring Heitman

IPC: F01D25/24

Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud, which is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

公开(公告)号：US20170191493A1

公开(公告)日：2017-07-06

申请号：US14985169

申请日：2015-12-30

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Jan Christopher Schilling ,  Nitesh Jain ,  Abhijit Roy

IPC: F04D29/32 ,  F04D29/02

CPC classification number: F04D29/324 ,  F01D5/147 ,  F01D5/282 ,  F01D5/30 ,  F01D11/008 ,  F04D29/023 ,  F04D29/322 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2230/23 ,  F05D2230/60 ,  F05D2240/30 ,  F05D2240/80 ,  F05D2260/30 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

Abstract: A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.