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公开(公告)号：US10718272B2
公开(公告)日：2020-07-21
申请号：US15490155
申请日：2017-04-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wesley K. Lord , Matthew R Feulner , Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine comprises a housing having an inlet leading to a fan rotor. A bypass door is mounted upstream of the inlet to the fan rotor, and is moveable away from a non-bypass position to a bypass position to selectively bypass boundary layer air vertically beneath the engine. An aircraft is also disclosed.
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公开(公告)号：US10718268B2
公开(公告)日：2020-07-21
申请号：US15807911
申请日：2017-11-09
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry , Wesley K. Lord
Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses cooling air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.
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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
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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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.
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公开(公告)号：US10421553B2
公开(公告)日：2019-09-24
申请号：US14600946
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Wesley K. Lord , Jesse M. Chandler
Abstract: An aircraft is provided that includes a wing and a pusher fan engine. The pusher fan engine is configured in the wing.
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Patent Agency Ranking
公开(公告)号：US10330010B2
公开(公告)日：2019-06-25
申请号：US14967518
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
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公开(公告)号：US10247097B2
公开(公告)日：2019-04-02
申请号：US14443078
申请日：2013-06-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.
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公开(公告)号：US10221862B2
公开(公告)日：2019-03-05
申请号：US14695534
申请日：2015-04-24
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：US20180354637A1
公开(公告)日：2018-12-13
申请号：US15619893
申请日：2017-06-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Wesley K. Lord
Abstract: An exemplary boundary layer ingestion engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan mechanically linked to the turbine via at least one shaft. The linkage is configured such that rotation of the turbine is translated to the fan. The boundary layer ingestion engine further includes an exhaust duct fluidly connected to an outlet of the turbine. The exhaust duct is positioned radially inward of the fan.
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公开(公告)号：US10094393B2
公开(公告)日：2018-10-09
申请号：US15023289
申请日：2014-08-01
Applicant: United Technologies Corporation
Inventor： James D. Hill , Gabriel L. Suciu , Jesse M. Chandler
Abstract: A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades. The inlet frame connects to an inlet end of the compressor case. The outlet frame connects to an outlet end of the compressor case portion at an end opposite the compressor case inlet end. An axially fore mounting structure of the mounting structure connects to the inlet frame. An axially aft mounting structure of the mounting structure connects to the outlet frame. A bridging structure of the mounting structure is offset from the compressor case and connects the fore and aft mounting structures, thereby bridging engine loads across the inlet and outlet frames to reduce load induced distortion of the compressor case portion.
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