公开(公告)号：US10138809B2

公开(公告)日：2018-11-27

申请号：US14592991

申请日：2015-01-09

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C1/00 ,  F02C3/107 ,  F01D25/16 ,  F02K3/06 ,  F02C7/36

Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.

公开(公告)号：US10125693B2

公开(公告)日：2018-11-13

申请号：US14593056

申请日：2015-01-09

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F01D1/26 ,  F01D15/12

Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction.

公开(公告)号：US10054059B2

公开(公告)日：2018-08-21

申请号：US14824292

申请日：2015-08-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Robert E. Malecki

IPC: F02C1/00 ,  F02C9/18 ,  F02K3/06 ,  F02C7/05 ,  F01D25/24 ,  F02C3/04 ,  F02C7/36 ,  B64D33/02

CPC classification number: F02C9/18 ,  B64D2033/022 ,  F01D25/24 ,  F02C3/04 ,  F02C7/05 ,  F02C7/36 ,  F02K3/06 ,  F05D2250/14 ,  F05D2250/232 ,  F05D2250/24

Abstract: A gas turbine engine includes a nacelle defining a centerline axis and an annular splitter radially inward from the nacelle. A spinner is radially inward of the nacelle forward of a compressor section. A fan blade extends from a fan blade platform. A distance X is the axial distance from a first point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defined on a leading edge of the fan blade where the fan blade meets the fan blade platform. A distance H is the radial distance from the first point to the second point. The relative position of the first point and the second point is governed by the ratio of X H ≥ 1.5 for reducing foreign object debris (FOD) intake into the compressor section.

公开(公告)号：US10018120B2

公开(公告)日：2018-07-10

申请号：US14598252

申请日：2015-01-16

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Paul W. Duesler

IPC: F02C9/16 ,  F01D5/08 ,  F01D25/10 ,  F02C9/18 ,  F02C3/04

CPC classification number: F02C9/16 ,  F01D5/08 ,  F01D25/10 ,  F02C3/04 ,  F02C9/18 ,  F05D2260/232 ,  F05D2260/941 ,  F05D2270/303 ,  Y02T50/676

Abstract: A gas turbine engine comprises a compressor rotor including blades and a disk, with a bore defined radially inwardly of the disk, and a combustor. A tap directs the products of combustion first to a valve and then into the bore of the disk. At least two temperature sensors sense a temperature of the products of combustion downstream of the valve. A control compares sensed temperatures from the at least two temperature sensors to ensure the at least two temperature sensors are functioning properly. The sensed temperatures are utilized to control the valve. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US09995222B2

公开(公告)日：2018-06-12

申请号：US14754325

申请日：2015-06-29

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Matthew P. Forcier

IPC: F02C9/18 ,  F01D5/08 ,  F01D11/24 ,  F02C3/34 ,  F02C7/12 ,  F01D25/10 ,  F01D9/06

CPC classification number: F02C9/18 ,  F01D5/08 ,  F01D5/082 ,  F01D9/065 ,  F01D11/24 ,  F01D25/10 ,  F02C3/34 ,  F02C7/125 ,  F05D2260/20 ,  F05D2260/941 ,  Y02T50/676

Abstract: A gas-circulation system for conditioning a disk of an aircraft may comprise a first takeoff port configured to extract a combusted gas and a second takeoff port configured to extract an uncombusted gas. A first valve may comprise an inlet in fluid communication with the first and second takeoff ports and an outlet of the first valve in fluid communication with the disk.

公开(公告)号：US20180128178A1

公开(公告)日：2018-05-10

申请号：US15806992

申请日：2017-11-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nathan Snape ,  Joseph Brent Staubach ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F02C9/18 ,  B64D13/08

CPC classification number: F02C7/18 ,  B64D13/08 ,  B64D2013/0644 ,  F02C6/08 ,  F02C9/18 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/676

Abstract: A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increases a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A valve is downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.

公开(公告)号：US09915165B2

公开(公告)日：2018-03-13

申请号：US14751299

申请日：2015-06-26

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C9/18 ,  F01D17/00 ,  F02C6/08 ,  F02C7/32 ,  F01D25/28 ,  F02C3/04 ,  F02C3/14 ,  F02C7/20 ,  F02C7/36

CPC classification number: F01D17/00 ,  F01D25/28 ,  F02C3/04 ,  F02C3/14 ,  F02C6/08 ,  F02C7/20 ,  F02C7/32 ,  F02C7/36 ,  F02C9/18

Abstract: An environmental control system includes a higher pressure tap at a higher pressure location in the main compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A pylon includes a lowermost surface and the higher pressure tap does not extend above a plane including the lowermost surface. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use.

公开(公告)号：US20180051630A1

公开(公告)日：2018-02-22

申请号：US15242973

申请日：2016-08-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F01D25/12

CPC classification number: F02C7/18 ,  F01D25/12 ,  F02C6/12 ,  F02C7/20 ,  F05D2260/213 ,  F05D2260/30 ,  F05D2260/96 ,  Y02T50/676

Abstract: A gas turbine engine has a core engine with a compressor section and a turbine section. The compressor section includes a low pressure compressor and a high pressure compressor. A cooling air system taps compressed air and passes the compressed air through a heat exchanger. Cooling air passes over the heat exchanger to cool the compressed air, which is returned to the core engine to provide a cooling function. The heat exchanger is mounted through a flexible mount allowing movement between a static structure and the heat exchanger.

公开(公告)号：US09897001B2

公开(公告)日：2018-02-20

申请号：US14620395

申请日：2015-02-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Stephen G. Pixton

IPC: F02C3/107 ,  F02C3/067 ,  F02C7/36

CPC classification number: F02C3/107 ,  F02C3/067 ,  F02C7/36 ,  F05D2250/44 ,  F05D2260/4031

Abstract: A gas turbine engine comprises a high pressure turbine rotor, an intermediate pressure turbine rotor and a fan drive turbine rotor. The fan drive turbine rotor drives a fan rotor through a gear reduction. The intermediate pressure rotor drives a low pressure compressor rotor and the high pressure turbine rotor drives a high pressure compressor rotor. A first flow cross-sectional area is between an outer periphery of a hub in the low pressure compressor rotor, and an outer tip of an upstream most blade row of the low pressure compressor rotor. A second flow cross-sectional area is between an outer periphery of a hub in the high pressure compressor rotor, and an outer tip of an upstream most blade row of the high pressure compressor rotor. A ratio of the first and second flow cross-sectional areas is greater than or equal to about 0.12 and less than or equal to about 0.33.

公开(公告)号：US20180023413A1

公开(公告)日：2018-01-25

申请号：US15656444

申请日：2017-07-21

Applicant: United Technologies Corporation

Inventor： Subhradeep Chowdhury ,  David M. Bostwick ,  David Gelwan ,  Frederick M. Schwarz

IPC: F01D19/02 ,  F02C6/20 ,  B64D41/00 ,  F01D25/34 ,  B64D27/12 ,  B64F1/36 ,  F02C3/04 ,  F02C7/277

CPC classification number: F01D19/02 ,  B64D27/12 ,  B64D41/00 ,  B64D2041/002 ,  B64F1/364 ,  F01D25/34 ,  F02C3/04 ,  F02C6/20 ,  F02C7/277 ,  F02C9/00 ,  F05D2220/323 ,  F05D2220/50 ,  F05D2260/85 ,  F05D2270/303

Abstract: A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.