公开(公告)号：EP2971564A4

公开(公告)日：2016-03-16

申请号：EP13877597

申请日：2013-12-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G

IPC: F01D5/30 ,  F01D5/18 ,  F01D5/28 ,  F01D9/02 ,  F01D25/08 ,  F02C7/24

CPC classification number: F01D5/282 ,  B28B1/24 ,  F01D5/147 ,  F01D5/225 ,  F01D5/28 ,  F01D5/284 ,  F01D5/3007 ,  F01D5/3092 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2230/51 ,  F05D2260/231 ,  F05D2300/2261 ,  F05D2300/2283 ,  F05D2300/6033

Abstract: A co-formed element includes a core structure which has a root portion and is formed from a high thermal conductivity ceramic matrix composite material, and a low thermal conductivity layer co-formed with the core structure and surrounding the root portion of the core structure.

公开(公告)号：EP2946081A4

公开(公告)日：2016-03-09

申请号：EP13871926

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  SURACE RAYMOND ,  PROPHETER-HINCKLEY TRACY A

IPC: F01D17/16 ,  F01D5/14 ,  F01D5/18

CPC classification number: F01D17/162 ,  F01D5/145 ,  F01D5/187

公开(公告)号：EP2920428A4

公开(公告)日：2016-01-06

申请号：EP13872958

申请日：2013-11-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  ROUSE BRANDON T

IPC: F01D11/08 ,  F01D9/04 ,  F02C7/28

CPC classification number: F01D11/08 ,  F01D9/04

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an engine case, a rotor stage including a plurality of rotor blades, a plurality of carriers for supporting a plurality of blade outer air seals and an interlock formed between circumferential ends of a first adjacent carrier and a second adjacent carrier of the plurality of carriers.

公开(公告)号：EP2815082A4

公开(公告)日：2015-11-11

申请号：EP13749712

申请日：2013-02-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G

IPC: F01D11/14 ,  F01D11/10 ,  F02C7/28

CPC classification number: F01D11/20 ,  F01D11/22 ,  F01D25/24 ,  F02C3/04 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2240/55 ,  Y10T29/49318

Abstract: An adjustable blade outer air seal apparatus includes a case structure that extends circumferentially, a support ring structure mounted radially inwards of the case structure and at least one blade outer air seal segment radially adjustably mounted relative to the support ring structure.

公开(公告)号：EP2875224A4

公开(公告)日：2015-10-28

申请号：EP13820536

申请日：2013-06-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G

IPC: F02C7/00 ,  F01D11/16 ,  F01D11/18 ,  F02C7/20 ,  F02C7/32

CPC classification number: F01D11/16 ,  F01D11/18 ,  Y02T50/672

Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. The supported structure includes a hook providing an annular recess. A support ring is received in the recess. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure.