公开(公告)号：US11314227B2

公开(公告)日：2022-04-26

申请号：US16575751

申请日：2019-09-19

Applicant: United Technologies Corporation

Inventor： John P. Rizzo, Jr. ,  Adam Z. Doherty ,  Jesse R. Boyer

IPC: B29C64/386 ,  G05B19/408 ,  G05B19/4099 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/02

Abstract: An exemplary method for determining a set of additive manufacturing parameters includes, a) determining a nominal parameter of at least one surface of a component, b) determining at least a second order variation in the nominal parameter, c) predicting an actual resultant dimension based at least in part on the nominal parameter and the second order variation, and d) adjusting at least one additive manufacturing process parameter in response to the predicted actual resultant dimension.

公开(公告)号：US11306919B2

公开(公告)日：2022-04-19

申请号：US16224012

申请日：2018-12-18

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis

IPC: F23R3/06 ,  F23R3/50

Abstract: A cooling hole arrangement for a combustor panel including a first group of cooling holes, each of the first cooling holes extending from a first inlet to a first outlet. Also included is a second group of cooling holes, each of the second cooling holes extending from a second inlet to a second outlet, each of the first cooling holes and the second cooling holes spaced from an edge of the combustor panel in an axial direction to be arranged substantially parallel to the edge of the combustor panel. At least a portion of the first inlet of each first cooling holes is axially overlapped with a portion of the second inlet of the second cooling holes. The first outlet of each of the first cooling holes is closer to the edge of the combustor panel than the second outlet of the second cooling holes is to the edge.

公开(公告)号：US11306657B2

公开(公告)日：2022-04-19

申请号：US16736281

申请日：2020-01-07

Applicant: United Technologies Corporation

Inventor： Armando Amador ,  Ernest Boratgis

IPC: F02C7/06 ,  F01D9/06 ,  F01D25/16 ,  F01D25/18 ,  F01D25/20 ,  F01D25/22 ,  F16C27/04 ,  F16F15/023

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft configured to rotate during operation of the gas turbine engine, and a squeeze film damper radially outside the shaft. The squeeze film damper includes a cavity including a film of lubricant axially between first and second cavity seals, and further includes a reservoir fluidly coupled to the cavity. A method is also disclosed.

公开(公告)号：US11306601B2

公开(公告)日：2022-04-19

申请号：US16163610

申请日：2018-10-18

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  James Glaspey

IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction, and the airfoil section defines a pressure side and a suction side separated in a thickness direction. The airfoil section includes a metallic sheath that receives a composite core, and the core includes first and second ligaments received in respective internal channels defined by the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction. The first and second ligaments define respective sets of bores, and the respective sets of bores are aligned to receive a common set of retention pins.

公开(公告)号：US11300209B2

公开(公告)日：2022-04-12

申请号：US16598168

申请日：2019-10-10

Applicant: United Technologies Corporation

Inventor： Jeremy Drake ,  Raymond Surace

IPC: F16J15/3288 ,  F01D11/00 ,  F01D11/12 ,  F04D29/08

Abstract: Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.

公开(公告)号：US11300057B2

公开(公告)日：2022-04-12

申请号：US15981559

申请日：2018-05-16

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F02K3/04 ,  F16D41/069 ,  F16H1/20

Abstract: A gas turbine engine including a fan and an oil pump operatively connected to the fan by a main input drive gear, the drive gear rotating when the fan rotor rotates in either a first or second direction of the fan. Further included is a gear train intermediate the main input drive gear and the oil pump, the gear train including a first and second pinion gear, the first and second pinion gear each driven by the main input drive gear, the first pinion gear driving a first gear through a first clutch, the second pinion gear driving a second gear through a second clutch. Only one of the clutches transmits rotation from the respective pinion gear to the respective gear when the fan is rotating in the first direction, with the only the other clutch transmitting rotation when the fan is rotating in the second direction.

公开(公告)号：US11293638B2

公开(公告)日：2022-04-05

申请号：US16549722

申请日：2019-08-23

Applicant: United Technologies Corporation

Inventor： Fumitaka Ichihashi ,  Timothy S. Snyder ,  Jeffrey J. Lienau ,  Baris A. Sen

IPC: F23R3/08 ,  F01D25/12 ,  F01D25/26

Abstract: A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.

公开(公告)号：US11293301B2

公开(公告)日：2022-04-05

申请号：US16812644

申请日：2020-03-09

Applicant: United Technologies Corporation

Inventor： Sheridon Everette Haye

IPC: G01M15/14 ,  F01D21/00 ,  F02K3/06 ,  F02C7/00 ,  F01D5/06 ,  G01H1/10 ,  F02C7/36 ,  G01H1/00 ,  F02C3/04

Abstract: A drive system of a gas turbine engine includes a first drive shaft and a second drive shaft operable to rotate within the gas turbine engine, a first sensor operable to detect rotation of the first drive shaft, a second sensor operable to detect rotation of the second drive shaft, and a processing system coupled to the first sensor and the second sensor. The processing system is operable to determine a timing variation based on output of the first sensor and output of the second sensor, determine a torsional deflection between the first drive shaft and the second drive shaft based on the timing variation, and detect a health status of the drive system based on the torsional deflection.

公开(公告)号：US11286801B2

公开(公告)日：2022-03-29

申请号：US16158397

申请日：2018-10-12

Applicant: United Technologies Corporation

Inventor： Dean W. Johnson ,  Thomas E. Clark

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

Abstract: A turbine section for a gas turbine engine includes a turbine blade that extends radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal has a plurality of segments arranged circumferentially about the axis of rotation and mounted in a support structure radially outward of the outer tip. Each of the segments have a radially inner surface and a radially outer surface and four hooks protruding radially outward from the radially outer surface and extending along the segment in an axial direction.

公开(公告)号：US11286796B2

公开(公告)日：2022-03-29

申请号：US16406294

申请日：2019-05-08

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D5/30 ,  F01D11/00 ,  B33Y80/00

Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk with a multiple of blade slots, the rotor disk defined about an axis; a sleeve received within each of the multiple of blade slots; and a ceramic matrix composite rotor blade received within each of the multiple of sleeves.