公开(公告)号：US11542016B2

公开(公告)日：2023-01-03

申请号：US16360280

申请日：2019-03-21

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Winter ,  Charles E. Lents ,  Nathan Snape ,  Alan H. Epstein

IPC: F25B9/14 ,  B64D33/08 ,  B64D13/06 ,  F25J1/00 ,  B64D13/08 ,  F02C7/141 ,  F02C7/16 ,  F02C9/18 ,  F25J3/04 ,  B01D45/08 ,  B01D53/00 ,  B03C1/28 ,  B64D27/12 ,  F01D15/00 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C7/18 ,  F02K3/06 ,  F17C7/02 ,  F17C7/04 ,  B64D37/32

Abstract: A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.

公开(公告)号：US20200095939A1

公开(公告)日：2020-03-26

申请号：US16142317

申请日：2018-09-26

Applicant: United Technologies Corporation

Inventor： Alan H. Epstein

IPC: F02C7/275 ,  F02C7/12 ,  F02C7/27 ,  B64D27/10 ,  B64D31/02 ,  B64D33/08

Abstract: An engine system for an aircraft includes a first gas turbine engine, a first core turning system, a second gas turbine engine, and a second core turning system. The engine system also includes a controller operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.

公开(公告)号：US09909504B2

公开(公告)日：2018-03-06

申请号：US14440953

申请日：2013-02-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Jesse M. Chandler

IPC: F02C7/052 ,  F02C7/36 ,  B64D33/02 ,  B64D33/10

CPC classification number: F02C7/36 ,  B64D33/02 ,  B64D33/10 ,  B64D2033/022 ,  F02C7/052 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2250/44 ,  F05D2260/20 ,  Y02T50/675

Abstract: A gas turbine engine comprises an outer nacelle. A nose cone is spaced radially inward of the outer nacelle. The nose cone defines a particle separator for directing an outer air flow and an inner airflow. The inner airflow is directed through a core inlet to a compressor. The engine further comprises a drive gear system for driving at least one propeller. A variable pitch control system may alter a pitch angle of the at least one propeller. Some of the outer air flow is directed to at least one of the drive gear system and the pitch control system.

公开(公告)号：US09752510B2

公开(公告)日：2017-09-05

申请号：US15000077

申请日：2016-01-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Michael E. McCune ,  Brian D. Merry

IPC: F02C7/16 ,  F02C7/36 ,  F01D15/12 ,  F02C3/107 ,  F02C3/06

CPC classification number: F02C7/36 ,  F01D15/12 ,  F02C3/06 ,  F02C3/107 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/40 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.

公开(公告)号：US11199137B2

公开(公告)日：2021-12-14

申请号：US16142317

申请日：2018-09-26

Applicant: United Technologies Corporation

Inventor： Alan H. Epstein

IPC: F02C7/275 ,  B64D27/10 ,  B64D31/02 ,  B64D33/08 ,  F02C7/12 ,  F02C7/27 ,  F01D25/36

Abstract: An engine system for an aircraft includes a first gas turbine engine, a first core turning system, a second gas turbine engine, and a second core turning system. The engine system also includes a controller operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.

公开(公告)号：US10549845B2

公开(公告)日：2020-02-04

申请号：US15606051

申请日：2017-05-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alan H. Epstein ,  Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64C21/06 ,  B64C23/02 ,  B64C1/00 ,  B64D33/02

Abstract: A propulsion system for an aircraft including at least two main gas turbine engines and a plurality of dedicated boundary layer ingestion fans. The propulsion system is arranged such that a combined thrust produced by the boundary layer ingestion fans is less than 20 percent of a total thrust of the main engines and the boundary layer ingestion fans. The boundary layer ingestion fans are controllable and selectively turned off at lower speeds.

公开(公告)号：US20180342904A1

公开(公告)日：2018-11-29

申请号：US15605446

申请日：2017-05-25

Applicant: United Technologies Corporation

Inventor： Joseph V. Mantese ,  Alan H. Epstein ,  Kurt J. Sobanski

IPC: H02J50/20 ,  H01L35/28 ,  F25B21/04

Abstract: A thermoelectric conditioning arrangement may comprise a first antenna/splitter configured to transmit a power & control signal, a second antenna/splitter configured to receive the power & control signal, a waveguide coupled between the first antenna/splitter and the second antenna/splitter, wherein the power & control signal is guided from the first antenna/splitter to the second antenna/splitter via the waveguide, a power converter configured to receive the power & control signal from the second antenna/splitter and generate a direct current (DC) signal, and a thermoelectric cooler (TEC) configured to receive the DC signal from the power converter.

公开(公告)号：US09771863B2

公开(公告)日：2017-09-26

申请号：US14600304

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Jesse M. Chandler ,  Stephen G. Pixton

IPC: B64D27/12 ,  F02C3/10 ,  F02K1/54 ,  F02C6/20 ,  F02C7/36 ,  B64D35/04

CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C6/206 ,  F02C7/36 ,  F02K1/54

Abstract: An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed.

公开(公告)号：US20160131044A1

公开(公告)日：2016-05-12

申请号：US15000077

申请日：2016-01-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Michael E. McCune ,  Brian D. Merry

IPC: F02C7/36 ,  F02C3/06

CPC classification number: F02C7/36 ,  F01D15/12 ,  F02C3/06 ,  F02C3/107 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/40 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.

公开(公告)号：US11319963B2

公开(公告)日：2022-05-03

申请号：US15992747

申请日：2018-05-30

Applicant: United Technologies Corporation

Inventor： Alan H. Epstein

IPC: F04D27/02 ,  F02C9/50 ,  F04D25/04 ,  F04D25/06 ,  H02P23/04

Abstract: A compressor surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The compressor surge control system also includes one or more rotor system sensors configured to collect a plurality of sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to monitor the one or more rotor system sensors while the rotor system is rotating. The controller determines whether the plurality of sensor data from the one or more rotor system sensors is indicative of an early-stage compressor surge oscillation. A surge control torque is determined to diminish the early-stage compressor surge oscillation of the rotor system. The electric motor is commanded to apply the surge control torque to the rotor system.