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：US20170363098A1

公开(公告)日：2017-12-21

申请号：US15186729

申请日：2016-06-20

Applicant: United Technologies Corporation

Inventor： Stephen H. Taylor ,  Charles E. Lents ,  Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler

IPC: F04D27/00 ,  F01D15/12 ,  F01D5/02 ,  F01D17/14 ,  F01D15/08 ,  F04D29/32

CPC classification number: F04D27/009 ,  F01D5/02 ,  F01D15/08 ,  F01D15/12 ,  F01D17/145 ,  F02C6/08 ,  F02C7/32 ,  F04D25/02 ,  F04D27/004 ,  F04D27/023 ,  F04D29/321 ,  F05D2220/32 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine includes a main engine compressor section. A booster compressor changing a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system. The booster compressor operates at airflow conditions greater than a demand by the pneumatic system. A speed change system driving the booster compressor at speeds corresponding to a demand of the pneumatic system. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.

公开(公告)号：US10533501B2

公开(公告)日：2020-01-14

申请号：US15186722

申请日：2016-06-20

Applicant: United Technologies Corporation

Inventor： Stephen H. Taylor ,  Charles E. Lents ,  Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler

IPC: F02C9/24 ,  F02C3/13 ,  F02C6/08 ,  F02C9/18 ,  F02K3/06

Abstract: A gas turbine engine includes a main compressor section. A booster compressor includes an inlet and an outlet. The inlet receives airflow from the main compressor section and the outlet provides airflow to a pneumatic system. A recirculation passage is between the inlet and the outlet. A flow splitter valve controls airflow between the outlet and the inlet through the recirculation passage for controlling airflow to the pneumatic system based on airflow output from the booster compressor. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.

公开(公告)号：US10519963B2

公开(公告)日：2019-12-31

申请号：US15186739

申请日：2016-06-20

Applicant: United Technologies Corporation

Inventor： Stephen H. Taylor ,  Charles E. Lents ,  Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler

IPC: F02C6/08 ,  F04D27/02 ,  F01D5/02 ,  F01D15/08 ,  F01D15/12 ,  F01D17/14 ,  F04D29/32 ,  F04D27/00 ,  F04D25/06 ,  F02C9/18

Abstract: A gas turbine engine includes a main engine compressor section. A booster compressor changes a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system. The booster compressor is configured to operate at airflow conditions greater than a demand of the pneumatic system. An exhaust valve controls airflow between an exhaust outlet and an outlet passage to the pneumatic system. The exhaust valve is operable to exhaust airflow from the booster compressor in excess of the demand of the pneumatic system. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.

公开(公告)号：US20190162121A1

公开(公告)日：2019-05-30

申请号：US15823639

申请日：2017-11-28

Applicant: United Technologies Corporation

Inventor： Joseph Brent Staubach ,  Nathan Snape ,  Frederick M. Schwarz ,  Charles E. Lents ,  Michael K. Ikeda

IPC: F02C9/18 ,  F02C7/18 ,  B64D33/02 ,  B64D13/00

Abstract: A lower pressure tap is connected to a first heat exchanger to be cooled by cooling air, and then to a selection valve. The selection valve selectively delivers the lower pressure tap air to a boost compressor. The lower pressure tap air downstream of the boost compressor is connected to cool the at least one turbine. The selection valve also selectively delivers a portion of the lower pressure tap air across a first cooling turbine, and to a line associated with an air delivery system for a cabin on an associated aircraft. A portion of the air downstream of the first cooling turbine is connected to a second cooling turbine, and air downstream of the second cooling turbine is connected for use in a cold loop A method of operating an air supply system is also disclosed.

公开(公告)号：US20180003071A1

公开(公告)日：2018-01-04

申请号：US15200128

申请日：2016-07-01

Applicant: United Technologies Corporation

Inventor： Charles E. Lents ,  Christopher J. Hanlon ,  Larry W. Hardin ,  Jonathan Rheaume

IPC: F01D15/10 ,  F02C6/14 ,  F02K3/06 ,  B64D27/10 ,  F02C7/36 ,  F02C3/04

CPC classification number: F01D15/10 ,  B64D27/10 ,  B64D27/24 ,  B64D41/00 ,  F02C6/14 ,  F02C7/36 ,  F05D2220/76 ,  F05D2240/60

Abstract: A gas turbine engine includes a compressor section having a first compressor and a second compressor, the second compressor having a higher pressure than the first compressor, and a turbine section having a first turbine and a second turbine, the second turbine having a higher pressure than the first turbine. The first compressor is connected to the first turbine via a first shaft. The second compressor is connected to the second turbine via a second shaft. An electric motor is connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft. A fan is connected to the first shaft via a gear system. The gas turbine engine includes at least a takeoff mode of operations, a top of climb mode of operations and a maximum cruise mode of operations. The gas turbine engine is sized to operate at peak efficiency in the maximum cruise mode of operations.

公开(公告)号：US11428170B2

公开(公告)日：2022-08-30

申请号：US15200149

申请日：2016-07-01

Applicant: United Technologies Corporation

Inventor： Charles E. Lents ,  Larry W. Hardin ,  Jonathan Rheaume ,  Joseph B. Staubach

IPC: F02C7/36 ,  F01D15/10 ,  B64D31/06 ,  F02C6/14 ,  F02C9/50 ,  B64D27/24 ,  B64D27/10 ,  B64D27/02

Abstract: A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.

公开(公告)号：US11130580B2

公开(公告)日：2021-09-28

申请号：US15809244

申请日：2017-11-10

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Stephen H. Taylor ,  Charles E. Lents

IPC: F02C6/08 ,  B64D13/08 ,  F02C9/18 ,  F02K3/115 ,  B64D27/10 ,  F01D15/10 ,  F02C3/04 ,  F02K3/06 ,  H02K7/18 ,  F02C7/18 ,  F02K3/04 ,  B64D13/06

Abstract: An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

公开(公告)号：US20180162537A1

公开(公告)日：2018-06-14

申请号：US15665860

申请日：2017-08-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  Brian Merry ,  Charles E. Lents ,  Stephen H. Taylor

IPC: B64D13/08 ,  F02C6/08 ,  F02K3/06 ,  F02C3/04 ,  F02C9/18 ,  F01D15/10 ,  H02K7/18 ,  B64D27/10

Abstract: An aircraft has a gas turbine engine including a compressor section that includes at least one compressor bleed. An environmental control system has an air input configured to receive pressurized cabin air. An intercooler has an input and an output. A selection valve is configured to selectively connect the bleeds to an intercooler input. At least one auxiliary compressor is connected to the intercooler output. An output of at least one auxiliary compressors is connected to an ECS air input. A controller is configured to receive contemporaneous operational data, calculate minimum configuration requirements to satisfy environmental demands, and transmit calculated configuration requirements to at least the selection valve to achieve a desired pressure and temperature for the air downstream of the auxiliary compressor. A method for supplying engine air to an environmental control system and a system for use on a turbine engine powered aircraft are also disclosed.

公开(公告)号：US10914242B2

公开(公告)日：2021-02-09

申请号：US15823639

申请日：2017-11-28

Applicant: United Technologies Corporation

Inventor： Joseph Brent Staubach ,  Nathan Snape ,  Frederick M. Schwarz ,  Charles E. Lents ,  Michael K. Ikeda

IPC: F02C9/18 ,  F02C7/18 ,  B64D33/02 ,  B64D13/00 ,  F02C7/14 ,  F02C7/32 ,  F02C7/224 ,  F02C3/04 ,  F02C7/22 ,  B64D13/06

Abstract: A lower pressure tap is connected to a first heat exchanger to be cooled by cooling air, and then to a selection valve. The selection valve selectively delivers the lower pressure tap air to a boost compressor. The lower pressure tap air downstream of the boost compressor is connected to cool the at least one turbine. The selection valve also selectively delivers a portion of the lower pressure tap air across a first cooling turbine, and to a line associated with an air delivery system for a cabin on an associated aircraft. A portion of the air downstream of the first cooling turbine is connected to a second cooling turbine, and air downstream of the second cooling turbine is connected for use in a cold loop A method of operating an air supply system is also disclosed.