公开(公告)号：US10794290B2

公开(公告)日：2020-10-06

申请号：US15806992

申请日：2017-11-08

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02C6/08 ,  F02C7/18 ,  B64D13/08 ,  F02C9/18 ,  B64D13/06

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：US10794216B2

公开(公告)日：2020-10-06

申请号：US16012059

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D15/10 ,  F02C7/36 ,  F02K3/06 ,  H02K11/00 ,  H02K7/18

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other things, a fan driven by a fan shaft rotatable about an engine axis; a fan drive electric motor providing a supplemental drive input to the fan; a turbine section driving an input shaft; a geared architecture driven by the input shaft of the turbine section and coupled to the fan shaft to provide a main drive input for driving the fan; and a generator including a rotor supported on the input shaft and a stator disposed on a static structure relative to the rotor, wherein the generator communicates electric power to power the fan drive electric motor.

公开(公告)号：US10794208B2

公开(公告)日：2020-10-06

申请号：US14794516

申请日：2015-07-08

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William K. Ackermann

IPC: F01D11/08 ,  F01D11/04 ,  F01D11/00 ,  F16J15/44 ,  F16J15/3284 ,  B64D27/10 ,  F04D29/32 ,  F04D29/54

Abstract: An assembly is provided for rotational equipment such as a gas turbine engine for an aircraft propulsion system. This assembly includes a stator, a rotor and a seal assembly. The rotor extends axially along a centerline. The rotor includes a linkage, a first rotor disk, and a second rotor disk. The linkage extends axially from the first rotor disk to the second rotor disk. The linkage is removably attached to the second rotor disk. The seal assembly is configured for sealing a gap radially between the stator and the linkage. The seal assembly includes a hydrostatic non-contact seal.

公开(公告)号：US10787933B2

公开(公告)日：2020-09-29

申请号：US15186839

申请日：2016-06-20

Applicant: United Technologies Corporation

Inventor： Jesse W. Clauson ,  Frederick M. Schwarz

IPC: F01D25/36 ,  F01D1/14 ,  F01D25/12 ,  F02C7/275 ,  F01D21/00 ,  F01D21/06 ,  F01D25/34 ,  F02C9/00 ,  F01D21/14

Abstract: A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes a full authority digital engine control (FADEC) that controls operation of the gas turbine engine in a full-power mode and controls operation of the core turning motor to drive rotation of the engine core using a reduced power draw when the FADEC is partially depowered in a low-power bowed rotor prevention mode.

公开(公告)号：US20200291860A1

公开(公告)日：2020-09-17

申请号：US16745921

申请日：2020-01-17

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Amy R. Grace

IPC: F02C7/27 ,  F02C7/268 ,  F01D19/02 ,  F01D25/34 ,  F01D25/24 ,  F02C3/107 ,  F02C7/06 ,  F02K3/04 ,  G05B15/02

Abstract: A bowed rotor start mitigation system for a gas turbine engine of an aircraft is provided. The bowed rotor start mitigation system includes a motoring system and a controller coupled to the motoring system and an aircraft communication bus. The controller is configured to determine at least one inferred engine operating thermal parameter based on at least one aircraft-based parameter received on the aircraft communication bus, where the at least one inferred engine operating thermal parameter is based on data describing a history of the aircraft before an engine shutdown. The motoring system is controlled to drive rotation of a starting spool of the gas turbine engine below an engine idle speed based on determining that the at least one inferred engine operating thermal parameter is within a preselected range.

公开(公告)号：US10759545B2

公开(公告)日：2020-09-01

申请号：US16012040

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Zubair Ahmed Baig

IPC: B64D31/06 ,  B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  B64D31/14 ,  H02K7/18 ,  H02K11/00 ,  F02C6/20 ,  F02C6/14 ,  H02K7/20

Abstract: A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

公开(公告)号：US20200248625A1

公开(公告)日：2020-08-06

申请号：US16781424

申请日：2020-02-04

Applicant: United Technologies Corporation

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F28D1/053 ,  F28F13/06 ,  F28D1/04 ,  F28F13/08 ,  F02K3/115 ,  F02C7/14

Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.

公开(公告)号：US10731661B2

公开(公告)日：2020-08-04

申请号：US14974138

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  David A. Welch

IPC: F04D29/52 ,  F02C7/04 ,  F02C7/36 ,  F04D29/32 ,  F04D29/64 ,  F02C3/04 ,  F02K3/06 ,  F04D19/00 ,  F04D25/02 ,  F04D29/66

Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. At least a portion of the nacelle inner surface extends radially inwardly to be radially inward of an outer diameter of the fan blades. The inner surface of the nacelle is formed with a trench, which extends into the inner surface to a radially outer extent that is spaced radially outward of the outer diameter of the fan blades.

公开(公告)号：US10669888B2

公开(公告)日：2020-06-02

申请号：US16107270

申请日：2018-08-21

Applicant: United Technologies Corporation

Inventor： William K. Ackermann ,  Clifton J. Crawley, Jr. ,  Frederick M. Schwarz

IPC: F01D25/12 ,  F01D5/08 ,  F01D5/30 ,  F01D11/00 ,  F16J15/44 ,  F01D5/02 ,  F01D9/04 ,  F01D11/04 ,  F01D11/08 ,  F02C3/14 ,  F02C7/18

Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a bladed rotor assembly, a stator vane assembly, a fixed stator structure and a seal assembly. The bladed rotor assembly includes a rotor disk structure. The stator vane assembly is disposed adjacent the bladed rotor assembly. The fixed stator structure is connected to and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.

公开(公告)号：US10662880B2

公开(公告)日：2020-05-26

申请号：US14692090

申请日：2015-04-21

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C9/18 ,  F02C3/04 ,  F02C7/20 ,  F01D1/02 ,  F01D5/02 ,  F01D9/04 ,  F01D25/24 ,  F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F02C3/113 ,  F02K3/02 ,  F02K3/075 ,  F02K7/06

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.