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公开(公告)号：US20190291877A1
公开(公告)日：2019-09-26
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
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.
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公开(公告)号：US20180163627A1
公开(公告)日：2018-06-14
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
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.
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Patent Agency Ranking
公开(公告)号：US20180003109A1
公开(公告)日：2018-01-04
申请号：US15200240
申请日：2016-07-01
Applicant: United Technologies Corporation
Inventor： Charles E. Lents , Jonathan Rheaume
CPC classification number: F02C6/14 , B64D27/10 , B64D27/24 , B64D41/00 , B64D2221/00 , F01D15/10 , F02C3/22 , F02C3/24 , F02C7/32 , F05D2220/76 , F05D2260/42 , F05D2260/85
Abstract: A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor.
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14.发明申请公开(公告)号：US20180003072A1
公开(公告)日：2018-01-04
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: F01D15/10 , B64D27/16 , B64D27/24 , F02C6/14 , F02C7/36 , F02C9/50 , F02C3/04 , B64D31/06 , B64D27/02
CPC classification number: F01D15/10 , B64D27/10 , B64D27/24 , B64D31/06 , B64D2027/026 , F02C6/14 , F02C7/36 , F02C9/50 , F05D2220/76 , Y10S903/905 , Y10S903/906
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.
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公开(公告)号：US20180002025A1
公开(公告)日：2018-01-04
申请号：US15200192
申请日：2016-07-01
Applicant: United Technologies Corporation
Inventor： Charles E. Lents , Larry W. Hardin , Jonathan Rheaume
CPC classification number: B64D27/10 , B64C25/405 , B64D27/16 , B64D27/24 , B64D41/00 , B64D2027/026 , B64D2205/00 , B64D2221/00 , F01D15/10 , F02C3/04 , F02C3/13 , F02C6/14 , F02K3/06 , F05D2220/323 , F05D2220/76 , Y10S903/905 , Y10S903/906
Abstract: A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, and a turbine section with a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and 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. An electric energy storage component is electrically connected to the electric motor, and electrically connected to at least one aircraft taxiing system. The gas turbine engine is configured such that the gas turbine engine requires supplemental power from the electric motor during at least one mode of operations.
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公开(公告)号：US20170363099A1
公开(公告)日：2017-12-21
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
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.
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公开(公告)号：US20170363014A1
公开(公告)日：2017-12-21
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
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.
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