公开(公告)号：US20200149423A1

公开(公告)日：2020-05-14

申请号：US16184701

申请日：2018-11-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Bryan H. Farrar ,  Howard J. Liles ,  Michael G. McCaffrey ,  Andrew J. Lazur

IPC: F01D9/04 ,  F01D5/14 ,  F01D5/28 ,  B29C70/24

Abstract: A stator vane may comprise an airfoil extending between a first platform and a second platform, a first shear tube may extend through the airfoil and relatively orthogonal to the first platform and the second platform, wherein the first shear tube extends through the first platform and the second platform. In various embodiments, a second shear tube may extend through the airfoil into the first platform and the second platform parallel the first shear tube.

公开(公告)号：US20200149417A1

公开(公告)日：2020-05-14

申请号：US16189233

申请日：2018-11-13

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D5/20 ,  F01D11/08

Abstract: A blade outer air seal (BOAS) for a gas turbine engine includes a seal ring body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a segmented spline that extends from the radially outer face of the seal ring body, the seal secured to the radially inner face of the seal ring body

公开(公告)号：US10590780B2

公开(公告)日：2020-03-17

申请号：US14782014

申请日：2014-04-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G. McCaffrey

IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28 ,  C04B37/00 ,  B28B1/30 ,  F01D5/02 ,  F01D9/04 ,  F02C3/04

Abstract: Disclosed is a gas turbine engine component, and a method for forming the component. The component includes a first portion, a second portion formed separately from the first portion, and an intermediate layer provided between the first portion and the second portion.

公开(公告)号：US10563531B2

公开(公告)日：2020-02-18

申请号：US15071317

申请日：2016-03-16

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D11/00 ,  F01D11/08

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal including a sealing portion and an engagement portion. A support includes an interface portion and a mounting portion. The interface portion defines a retention slot spaced apart from opposing mate faces. The mounting portion is configured to be fixedly attached to an engine static structure. The engagement portion is dimensioned to be slideably received within the retention slot.

公开(公告)号：US20200025014A1

公开(公告)日：2020-01-23

申请号：US16388219

申请日：2019-04-18

Applicant: United Technologies Corporation

Inventor： John R. Farris ,  Michael G. McCaffrey

IPC: F01D11/12 ,  B05D3/00 ,  F01D25/00 ,  C23C4/01 ,  C23C28/04 ,  C23C4/18 ,  C23C4/11

Abstract: A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event.

公开(公告)号：US20190323430A1

公开(公告)日：2019-10-24

申请号：US15956884

申请日：2018-04-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael G. McCaffrey

IPC: F02C7/18 ,  F01D25/12 ,  F01D5/18 ,  F01D5/08

Abstract: A method of modulating cooling of gas turbine engine components includes the steps of identifying an input indicative of a usage rate for at least a first gas turbine engine component of a plurality of gas turbine engine components. A cooling system is operated for at least the first gas turbine engine component. The cooling system is moved between a higher cooling potential mode and a lower cooling potential mode based on the identified rate. A gas turbine engine is also disclosed.

公开(公告)号：US10443450B2

公开(公告)日：2019-10-15

申请号：US14921533

申请日：2015-10-23

Applicant: United Technologies Corporation

Inventor： Ross Wilson ,  Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John J. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  John E. Paul ,  Alan W. Stoner ,  Edwin Otero

IPC: F01D25/28 ,  F16J15/16 ,  F01D5/22 ,  F01D5/24 ,  F01D5/26 ,  F01D5/28 ,  F01D9/02 ,  F01D9/04 ,  F01D11/00 ,  F01D11/12 ,  F01D25/24

Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.

公开(公告)号：US10436053B2

公开(公告)日：2019-10-08

申请号：US16143589

申请日：2018-09-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G. McCaffrey

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

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：US10436051B2

公开(公告)日：2019-10-08

申请号：US14921503

申请日：2015-10-23

Applicant: United Technologies Corporation

Inventor： Ross Wilson ,  Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John J. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  John E. Paul ,  Alan W. Stoner ,  Edwin Otero

IPC: F01D11/00 ,  F16J15/16 ,  F01D9/04 ,  F01D11/02 ,  F01D11/12

Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.

公开(公告)号：US10415417B2

公开(公告)日：2019-09-17

申请号：US15221061

申请日：2016-07-27

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D11/22 ,  F01D11/20 ,  F01D25/24

Abstract: A gas turbine engine includes a blade having a tip, a blade outer air seal operatively connected to a case assembly, and an active clearance control system disposed on the case assembly. The active control system includes an actuator assembly. The actuator assembly includes a motor assembly and a shaft. The shaft has a shaft body that extends between a first end that is operatively connected to the motor assembly and a second end that is operatively connected to the blade outer air seal.