公开(公告)号：US10302017B2

公开(公告)日：2019-05-28

申请号：US15096619

申请日：2016-04-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: B23H9/14 ,  B32B1/00 ,  B32B3/26 ,  B32B3/30 ,  B32B5/00 ,  B32B5/22 ,  C23C4/00 ,  C23C4/06 ,  C25D5/36 ,  C25D5/38 ,  C25D5/40 ,  C25D7/00 ,  F02C7/24 ,  F02K1/04 ,  B21D22/02 ,  B23K26/36 ,  B32B15/00 ,  B32B15/01 ,  B32B15/04 ,  B32B15/18 ,  C23C4/134 ,  C23C4/129 ,  C23C24/04 ,  C23C14/16 ,  C23C14/30 ,  C23C16/06 ,  B32B15/20 ,  B32B37/24 ,  B32B38/04

Abstract: A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration; and attenuating the component to a desired frequency by forming a plurality of openings in the external metallic shell.

公开(公告)号：US10287976B2

公开(公告)日：2019-05-14

申请号：US14797250

申请日：2015-07-13

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C3/107 ,  F02K3/06 ,  F02C3/113 ,  F02C7/36 ,  F01D5/06 ,  F01D25/24 ,  F04D29/32 ,  F02K3/04

Abstract: A gas turbine engine includes a fan section, a compressor section aft of the fan section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor. The turbine section includes at least a first turbine and a second turbine. The second turbine operates at a higher pressure than the first turbine. A shaft is connected to the first turbine section such that the first turbine section is operable to drive rotation of the shaft. The shaft is a rotational input for a split gear and the split gear is connected to the fan and at least one of the multiple compressors.

公开(公告)号：US20190078453A1

公开(公告)日：2019-03-14

申请号：US15703164

申请日：2017-09-13

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D11/00 ,  F02C7/28 ,  F16J15/08

CPC classification number: F01D11/003 ,  F01D11/005 ,  F01D25/30 ,  F02C7/28 ,  F02K1/805 ,  F02K3/077 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2250/61 ,  F05D2300/175 ,  F16J15/0887

Abstract: Aspects of the disclosure are directed an engine having a central longitudinal axis, comprising: a first case that at least partially defines a first flow path, a second case located radially outward of the first case, where the second case and the first case at least partially define a second flowpath, and an assembly that includes a first duct wall, a second duct wall, a finger seal disposed in a gap defined between the first duct wall and the second duct wall such that a first flow in the first flow path is isolated from a second flow in the second flowpath, a stop that projects from the first duct wall towards the second duct wall, and a diaphragm coupled to the second duct wall.

公开(公告)号：US20190072040A1

公开(公告)日：2019-03-07

申请号：US16180548

申请日：2018-11-05

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge ,  Michael E. McCune ,  William G. Sheridan

IPC: F02C7/36 ,  F01D25/16

Abstract: A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. The speed change mechanism is an epicyclic gear train. A torque frame surrounds the speed change mechanism and includes a plurality of fingers. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted on the bearing support aft of the speed change mechanism. The second fan section bearing is a fan thrust bearing.

公开(公告)号：US20180195463A1

公开(公告)日：2018-07-12

申请号：US15864297

申请日：2018-01-08

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02K1/38 ,  F02K3/105 ,  F02K3/077 ,  F02K3/075

CPC classification number: F02K1/386 ,  F02K3/075 ,  F02K3/077 ,  F02K3/105 ,  F05D2240/122 ,  F05D2240/129

Abstract: A method of communicating flow through a gas turbine engine having multiple flow paths according to an exemplary embodiment of the present disclosure includes moving core flow along a core flow path from a compressor section to an exhaust section, selectively communicating a first amount of bypass flow from a bypass flow path defined by a bypass duct to the exhaust section or a second amount of bypass flow from the bypass flow path to the exhaust section, the first amount different than the second amount.

公开(公告)号：US09964069B2

公开(公告)日：2018-05-08

申请号：US14753637

申请日：2015-06-29

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02K1/00 ,  F02K1/12 ,  F02K1/15 ,  F02K1/08 ,  F02K1/42 ,  F02K1/58 ,  F02K1/76 ,  F02K3/02

CPC classification number: F02K1/08 ,  F02K1/002 ,  F02K1/15 ,  F02K1/42 ,  F02K1/58 ,  F02K1/763 ,  F02K3/02

Abstract: An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

公开(公告)号：US09915164B2

公开(公告)日：2018-03-13

申请号：US14688080

申请日：2015-04-16

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D15/10 ,  F01D25/02 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107

CPC classification number: F01D15/10 ,  F01D25/02 ,  F02C3/107 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/76 ,  F05D2230/72 ,  F05D2260/40311 ,  F05D2260/60 ,  Y02T50/671

Abstract: A gas turbine engine comprises a fan rotor, a lower speed compressor rotor and a higher speed compressor rotor, and a lower speed turbine rotor and a higher speed turbine rotor. The lower speed turbine rotor rotates the lower speed compressor rotor, and rotates a gear reduction to, in turn, rotate the fan rotor. The higher speed turbine rotor rotates the higher speed compressor rotor. An electrical generator is driven to rotate with one of the lower speed turbine rotor and the fan rotor.

公开(公告)号：US09909529B2

公开(公告)日：2018-03-06

申请号：US14489777

申请日：2014-09-18

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C1/00 ,  F02K1/38 ,  F02K3/075 ,  F02K3/077 ,  F02K3/105

CPC classification number: F02K1/386 ,  F02K3/075 ,  F02K3/077 ,  F02K3/105 ,  F05D2240/122 ,  F05D2240/129

Abstract: An example gas turbine engine with multiple flow paths includes, among other things, a core flow path extending from a compressor section to an exhaust section, a bypass duct providing a bypass flow path radially outside the core flow path, and a flow injection device to selectively communicate a first amount of flow or a second amount of flow from the bypass flow path to the exhaust section, the first amount of flow different than the second amount of flow.

公开(公告)号：US20180051935A1

公开(公告)日：2018-02-22

申请号：US15243249

申请日：2016-08-22

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F28D9/00 ,  B23P15/26

CPC classification number: F01D25/12 ,  F05D2260/213 ,  F28D9/0018 ,  F28D2021/0021 ,  F28F3/086 ,  Y02T50/675

Abstract: A heat exchanger includes a heat exchanger body having a plurality of stacked panels defining an internal manifold and an external manifold. Each of the stacked panels includes an internal structure partially defining an internal manifold, an external structure partially defining the external manifold, and a plurality of ribs connecting the internal structure to the external structure. Each of the ribs further comprises a channel protruding into the rib and being paired with a corresponding rib of an adjacent panel, such that each of the ribs and the corresponding rib defining a cooling passage fluidly connecting the internal manifold to the external manifold. Each of the stacked panels is bonded to at least one adjacent stacked panel.

公开(公告)号：US20170320178A1

公开(公告)日：2017-11-09

申请号：US15149543

申请日：2016-05-09

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: B23Q3/08 ,  B23Q11/12 ,  B23Q17/22 ,  F01D5/14 ,  F04D29/34 ,  B23Q3/06 ,  F04D29/32 ,  F01D5/30 ,  F04D29/38

CPC classification number: B23Q3/086 ,  B23Q3/063 ,  B23Q11/126 ,  B23Q17/2233 ,  F01D5/147 ,  F01D5/30 ,  F04D29/322 ,  F04D29/324 ,  F04D29/34 ,  F04D29/38 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/30

Abstract: Disclosed is a method for machining a component, comprising: installing the component on a fixture, causing a medium of the fixture to solidify to encase a first portion of the component, applying a toolset to a second portion of the component that is outside of the solidified medium, and subsequent to applying the toolset, extracting the component from the fixture when the medium is in one of a liquid state or a semi-liquid state, where the medium has a melting-point temperature that is less than 500 degrees Fahrenheit. Disclosed is a fixture for machining a component, comprising: a medium configured to encase a first portion of the component when the medium is in a solidified state, and a toolset configured to be applied to a second portion of the component that is outside of the solidified medium, the medium having a melting-point temperature that is less than 500 degrees Fahrenheit.