公开(公告)号：US11306619B2

公开(公告)日：2022-04-19

申请号：US16455093

申请日：2019-06-27

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

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：US11261744B2

公开(公告)日：2022-03-01

申请号：US16441676

申请日：2019-06-14

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D5/30 ,  F01D5/02 ,  F01D5/08 ,  F01D5/28

Abstract: A rotor disk assembly for a gas turbine engine. A multiple of blade attachments each received within a slot in a rotor disk. The rotor blade attachment manufactured of a metal alloy and a rotor blade retained between each two of the multiple of blade attachments, the rotor blade manufactured of non-metal alloy.

公开(公告)号：US11136995B2

公开(公告)日：2021-10-05

申请号：US16376445

申请日：2019-04-05

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Pedro Rivero ,  Matthew Andrew Hough

IPC: F04D29/54 ,  F23R3/04

Abstract: A pre-diffuser for a gas turbine engine includes an exit guide vane ring having a multiple of exit guide vanes defined around an engine longitudinal axis; a hot fairing structure adjacent to the exit guide vane ring to define a multiple of diffusion passages around the engine longitudinal axis; an outer radial interface between a radial outer surface of the hot fairing structure and the exit guide vane ring, the outer radial interface being a full hoop structure; and an anti-rotation feature between the hot fairing structure and the exit guide vane ring, the anti-rotation features inboard of the multiple of diffusion passages.

公开(公告)号：US20210246790A1

公开(公告)日：2021-08-12

申请号：US16785999

申请日：2020-02-10

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D5/10

Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis; and a damper pivot support that extends from a rim of the rotor disk, the damper pivot support comprising an aperture that defines a pivot axis parallel to the axis. A method to dampen a rotor blade of a gas turbine engine, includes independently pivoting a first damper and a second damper of a damper assembly about the pivot axis to respectively contact a first blade and a second blade in response to centrifugal force below a platform of the respective first blade and second blade.

公开(公告)号：US11041397B1

公开(公告)日：2021-06-22

申请号：US16713284

申请日：2019-12-13

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D5/30 ,  F01D11/00

Abstract: A side plate seal assembly for a gas turbine engine includes a multiple of non-metallic side plate seals that are arranged about an axis of the gas turbine engine to form a full hoop seal, each of the multiple of side plate seals comprise a retention surface and a knife edge seal surface that extends at an angle therefrom.

公开(公告)号：US11021971B2

公开(公告)日：2021-06-01

申请号：US15025949

申请日：2014-09-17

Applicant: United Technologies Corporation

Inventor： John E. Holowczak ,  Michael G. McCaffrey

IPC: F01D5/28 ,  F01D5/30 ,  F01D5/14 ,  F01D11/00

Abstract: A blade for a gas turbine engine includes a fiber reinforced ceramic matrix composite structure that provides an airfoil with an exposed exterior airfoil surface and a refractory structure that provides at least an outer portion of a root secured relative to the airfoil.

公开(公告)号：US20210115804A1

公开(公告)日：2021-04-22

申请号：US16659737

申请日：2019-10-22

Applicant: United Technologies Corporation

Inventor： Bryan P. Dube ,  Michael G. McCaffrey

IPC: F01D11/00

Abstract: A vane includes a ceramic vane piece that defines first and second vane platforms and a hollow airfoil section that joins the first and second vane platforms. A structural platform adjacent the first platform defines a radial seal slot. A seal has a radial leg and an axial leg. The radial leg extends in the radial seal slot and the axial leg extends in an interface between the structural platform and the first vane platform.

公开(公告)号：US10822989B2

公开(公告)日：2020-11-03

申请号：US16166279

申请日：2018-10-22

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D11/22 ,  F01D11/20

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：US10801348B2

公开(公告)日：2020-10-13

申请号：US14852838

申请日：2015-09-14

Applicant: United Technologies Corporation

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

IPC: F16J15/44 ,  F01D11/02 ,  F16F15/06 ,  F01D25/04

Abstract: Non-contacting dynamic seals having wave springs are disclosed herein. A non-contacting dynamic seal may have a shoe coupled to an outer ring by an inner beam and an outer beam. A wave spring may be located between the inner beam and the outer beam, between the shoe and the inner beam, or between the outer beam and the outer ring. The wave spring may damp vibrations in the inner beam and the outer beam.

公开(公告)号：US10787914B2

公开(公告)日：2020-09-29

申请号：US14912317

申请日：2014-08-19

Applicant: United Technologies Corporation

Inventor： Michael G. Abbott ,  Michael G. McCaffrey ,  Grant O. Cook, III

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/18

Abstract: An airfoil includes a core having a first surface, a skin having a second surface disposed over at least a portion of the first surface of the core, and at least one of a transient liquid phase (TLP) bond and a partial transient liquid phase (PTLP) bond. The bond(s) are disposed between the first surface and the second surface, joining the skin to the core.