公开(公告)号：US20200025105A1

公开(公告)日：2020-01-23

申请号：US16374995

申请日：2019-04-04

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Michael G. McCaffrey

IPC: F02C9/18 ,  F01D17/10 ,  F01D25/12 ,  F02C7/36 ,  F04D29/28 ,  F02C7/143 ,  F02C7/32 ,  F02C7/18

Abstract: A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

公开(公告)号：US10443616B2

公开(公告)日：2019-10-15

申请号：US15071263

申请日：2016-03-16

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D11/12 ,  F04D29/52 ,  F04D29/32 ,  F04D29/08 ,  F01D25/24

Abstract: A seal system includes a segmented annular seal support that has carriage arc segments arranged circumferentially in circumferential carriage joints, and a segmented annular seal that includes seal arc segments arranged end-to-end in circumferential seal joints. The circumferential seal joints are circumferentially offset from the circumferential carriage joints.

公开(公告)号：US10344612B2

公开(公告)日：2019-07-09

申请号：US15405778

申请日：2017-01-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Eric A. Hudson ,  Michael G. McCaffrey ,  Stanley J. Funk ,  Scott D. Virkler

IPC: F01D11/18 ,  F01D11/02 ,  F01D5/20 ,  F01D25/24 ,  F02C3/04 ,  F04D29/32 ,  F04D29/52 ,  F04D29/08 ,  F04D29/64

Abstract: A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. The section also includes a control ring being annular, positioned radially inward from the case and designed to move radially relative to the case. The section also includes a segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and designed to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine.

公开(公告)号：US20190195087A1

公开(公告)日：2019-06-27

申请号：US15850379

申请日：2017-12-21

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Scott D. Virkler ,  Tuan David Vo

IPC: F01D25/16 ,  F01D25/00 ,  F01D25/24

CPC classification number: F01D25/162 ,  F01D9/065 ,  F01D25/005 ,  F01D25/243 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/237 ,  F05D2300/177

Abstract: The present disclosure provides an assembly for a gas turbine engine. The assembly may comprise a tierod, a bearing mounting ring, and a joint coupling the tierod to the bearing mounting ring. The joint may be configured to increase a volume of a bearing compartment on an inner surface of the bearing mounting ring. A coefficient of thermal expansion of the bearing mounting ring may be substantially the same as the coefficient of thermal expansion of the tierod.

公开(公告)号：US10280784B2

公开(公告)日：2019-05-07

申请号：US14749695

申请日：2015-06-25

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D11/20 ,  F01D11/22 ,  F01D25/24 ,  F02C3/04 ,  F02C7/28

Abstract: An adjustable blade outer air seal apparatus includes a case that extends circumferentially around an axis, a support ring non-rigidly mounted to the case on spring connections radially inwards of the case, whereby the support ring floats with respect to the case, and at least one blade outer air seal segment that is radially adjustable relative to the support ring.

公开(公告)号：US10196918B2

公开(公告)日：2019-02-05

申请号：US15176035

申请日：2016-06-07

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D11/08 ,  F01D25/24 ,  F01D25/28

Abstract: A blade outer air seal (BOAS) segment has a transversely concave inner diameter (ID) surface along a main body portion and extending from a first circumferential end to a second circumferential end. A first mounting ear extends outward from the main body portion and cooperates with a first end portion of the main body portion to define a first circumferentially outwardly open mounting recess. A second mounting ear extends outward from the main body portion and cooperates with a second end portion of the main body portion to define a second circumferentially outwardly open mounting recess. An outwardly open well is between the first mounting ear and the second mounting ear; a plurality of layers are formed of a ceramic matrix composite (CMC) material and include: a first plurality extending along the first circumferentially outwardly open mounting recess; a second plurality extending along the second circumferentially outwardly open mounting recess; and a third plurality extending along from the first mounting ear to the second mounting ear. One or more first wedges are between layers along the first mounting ear to circumferentially flare the layers along the first mounting ear. One or more second wedges are between layers along the second mounting ear to circumferentially flare the layers along the second mounting ear.

公开(公告)号：US20190024526A1

公开(公告)日：2019-01-24

申请号：US16143589

申请日：2018-09-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G. McCaffrey

IPC: F01D11/08 ,  F01D25/24 ,  F01D11/12 ,  F01D9/04 ,  F01D5/28 ,  F16J15/34

CPC classification number: F01D11/08 ,  F01D5/284 ,  F01D9/04 ,  F01D11/12 ,  F01D11/122 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/30 ,  F05D2300/2261 ,  F05D2300/2283 ,  F16J15/3464 ,  Y02T50/672

Abstract: A seal assembly includes a seal arc segment defining first and second seal supports. A carriage defines first and second support members with the first support member supporting the seal arc segment in a first ramped interface and the second support member supporting the seal arc segment in a second ramped interface such that the seal arc segment is circumferentially moveable with respect to the carriage. The seal assembly includes an anti-rotation interface in which the seal arc segment and the carriage are engaged. The anti-rotation interface restricts circumferential movement of the seal arc segment.

公开(公告)号：US10161258B2

公开(公告)日：2018-12-25

申请号：US15071485

申请日：2016-03-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G. McCaffrey ,  Benjamin F. Hagan ,  David Richard Griffin ,  Peter Balawajder ,  Christopher Corcoran

IPC: F01D11/08 ,  F01D5/02 ,  F01D25/24 ,  F01D9/04

Abstract: A seal assembly includes a seal arc segment that defines radially inner and outer sides with the radially outer side including radially-extending sidewalls. A radially inner surface joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A rail shield has radially-extending walls lines the radially-extending sidewalls.

公开(公告)号：US10036281B2

公开(公告)日：2018-07-31

申请号：US14847363

申请日：2015-09-08

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D25/24 ,  F01D9/04 ,  F01D25/16

CPC classification number: F01D25/246 ,  F01D9/041 ,  F01D25/162 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2300/20 ,  F05D2300/6033 ,  Y10T29/49337

Abstract: A mid-turbine frame for a gas turbine engine includes a CMC outer ring, a CMC inner ring, and a multiple of CMC airfoils between the CMC outer ring and the CMC inner ring. Each of the CMC airfoils includes at least one hollow tube and a shell of a multiple of CMC plies surrounding the hollow tube. The hollow tube reinforces the shell. A spring biased tie-rod assembly is mounted through at least one of the multiple of CMC airfoils.

公开(公告)号：US09988921B2

公开(公告)日：2018-06-05

申请号：US14882672

申请日：2015-10-14

Applicant: United Technologies Corporation

Inventor： Ross Wilson ,  Michael G. McCaffrey

IPC: F01D11/02 ,  F01D11/00 ,  F01D25/04 ,  F16J15/16 ,  F16J15/44

CPC classification number: F01D11/025 ,  F01D11/00 ,  F01D11/001 ,  F01D11/003 ,  F01D11/02 ,  F01D25/04 ,  F05D2220/32 ,  F05D2240/55 ,  F16J15/16 ,  F16J15/445

Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a circumferential seal for a gas turbine engine includes a first beam, a second beam, a seal shoe and at least one feature between the first beam and second beam configured to retain a beam spacer, wherein the at least one feature is configured to dampen at least one of beam and shoe vibration of the circumferential seal. Another embodiment is directed to a circumferential seal including a beam spacer.