公开(公告)号：US11268530B2

公开(公告)日：2022-03-08

申请号：US16831955

申请日：2020-03-27

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F04D19/02 ,  F04D25/16 ,  F04D27/00 ,  F04D29/58 ,  F16H3/72 ,  F02C7/32 ,  F02C7/18 ,  F02C9/18

Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.

公开(公告)号：US11174798B2

公开(公告)日：2021-11-16

申请号：US16359010

申请日：2019-03-20

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C9/18 ,  F01D11/24 ,  F01D19/00 ,  F01D17/20 ,  F01D11/22 ,  F01D11/12

Abstract: A compressor case for a gas turbine engine includes an annular body that extends circumferentially around a center axis and extends axially along the center axis. A first bleed manifold is formed on an outer surface of the annular body and encloses a first plenum. A second bleed manifold is formed on the outer surface of the annular body and is axially aft of the first bleed manifold. The second bleed manifold encloses a second plenum. A bleed inlet extends through the annular body and into the first bleed manifold. Cooling passages are formed in the annular body, and each of the cooling passages extends from the first plenum to the second plenum and fluidically connects the first plenum to the second plenum.

公开(公告)号：US20210222567A1

公开(公告)日：2021-07-22

申请号：US16796227

申请日：2020-02-20

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D5/18

Abstract: An apparatus is provided for a rotor assembly with a rotational axis. This apparatus includes a rotor blade including an airfoil, a neck and an attachment. The neck radially connects the airfoil and the attachment. The attachment extends axially between an attachment first axial side and an attachment second axial side. A first end portion of the attachment projects axially out from the neck to the attachment first axial side. A second end portion of the attachment projects axially out from the neck to the attachment second axial side.

公开(公告)号：US20210222557A1

公开(公告)日：2021-07-22

申请号：US16746321

申请日：2020-01-17

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D5/02

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. Each of the disk mounts connects the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount that further supports the first rotor blade.

公开(公告)号：US10982597B2

公开(公告)日：2021-04-20

申请号：US16431962

申请日：2019-06-05

Applicant: United Technologies Corporation

Inventor： Brandon T. Slaney ,  Michael Joseph Murphy ,  Gary D. Roberge

IPC: F02C7/28 ,  F01D11/00 ,  F01D25/14

Abstract: Isolation seals for gas turbine engines are described. The isolation seals include an elastomer body configured to be attached to a first case structure at a first end and a second case structure at a second end and a seal shield configured to be attached to the first case structure, the seal shield having a shielding member configured to define a protected space between the shielding member and the elastomer body.

公开(公告)号：US10968760B2

公开(公告)日：2021-04-06

申请号：US15951289

申请日：2018-04-12

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D9/02 ,  F01D11/00

Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor having a hub carrying a plurality of blades, the hub rotatable about a longitudinal axis, and a seal extending outwardly from the hub to establish a sealing relationship with a plurality of vanes distributed about the longitudinal axis. A flow guide assembly is secured to an engine static structure such that a flow path is defined between the hub and the flow guide assembly. The flow path has an inlet portion defined along the seal and an outlet portion, and the flow guide assembly includes an acoustic liner that extends along the flow path.

公开(公告)号：US10801413B2

公开(公告)日：2020-10-13

申请号：US15089891

申请日：2016-04-04

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D15/10 ,  F02C7/26 ,  F01D21/00 ,  F02K3/06 ,  F01D25/28 ,  F02C3/107 ,  F02C6/14 ,  F02C7/06 ,  F02C7/36 ,  F04D19/00 ,  F04D25/02

Abstract: A gas turbine engine including a compressor has a first compressor section and a second compressor section, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. The turbine includes a first turbine section and a second turbine section. A first shaft connects the first compressor section and the first turbine section. A second shaft connects the second compressor section and the second turbine section. A fan is connected to the first shaft via a geared architecture. The first shaft includes at least one magnetic section. An electromagnet is disposed radially outward of the first shaft at an axial location of the at least one magnetic section, relative to an axis defined by the gas turbine engine.

公开(公告)号：US20200300714A1

公开(公告)日：2020-09-24

申请号：US16355959

申请日：2019-03-18

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: G01K11/12 ,  F16L23/16

Abstract: A gas turbine engine includes a joint and a flexible strip wrapped circumferentially around the joint. The flexible strip includes a lock operable to fasten the flexible strip about the joint. A thermochromatic layer is attached to a surface of the flexible strip and is operable to change color responsive to a change in temperature.

公开(公告)号：US20200283910A1

公开(公告)日：2020-09-10

申请号：US16776231

申请日：2020-01-29

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge ,  William J. Brindley

IPC: C23C24/04 ,  C23C24/08 ,  B33Y10/00 ,  C25D7/00 ,  F01D25/00

Abstract: A method for forming a sheet structure includes providing a tool having a formation surface corresponding to a shape of the sheet structure. The method also includes depositing at least one layer of material on the formation surface using a cold-spray deposition technique. The method also includes removing the at least one layer of material from the formation surface to create the sheet structure.

公开(公告)号：US20200182157A1

公开(公告)日：2020-06-11

申请号：US16212010

申请日：2018-12-06

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/32 ,  F01D25/16 ,  F01D25/24

Abstract: A gas turbine engine includes an engine case along an engine axis, a conformal accessory drive gearbox housing mounted to the engine case, and at least one accessory mounted to the conformal housing