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公开(公告)号：US20200025071A1
公开(公告)日：2020-01-23
申请号：US16570923
申请日：2019-09-13
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , James D. Hill
Abstract: A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.
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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：US10508562B2
公开(公告)日：2019-12-17
申请号：US14935673
申请日：2015-12-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , William G. Sheridan , Michael E. McCune , Gabriel L. Suciu
Abstract: A gas turbine engine has a fan rotor, a turbine rotor driving the fan rotor, and an epicyclic gear reduction positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and no more than four intermediate gears that engage the sun gear and the ring gear. The fan drive turbine is configured to drive the sun gear to, in turn, drive the ring gears to, in turn, drive the fan rotor.
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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：US10352247B2
公开(公告)日：2019-07-16
申请号：US14767477
申请日：2014-02-27
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Gabriel L. Suciu , Brian D. Merry
Abstract: A gas turbine engine comprises a first compressor, a second compressor, a starter generator and a clutch. The starter generator is coupled to the first compressor. The clutch selectively couples the second compressor and the first compressor. The clutch is disposed between a first shaft and a second shaft to engage the first shaft with the second shaft at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft relative to the second shaft when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine comprises engaging a low pressure compressor with a high pressure compressor utilizing a clutch, rotating the low pressure compressor and the high pressure compressor utilizing a starter generator coupled to the low pressure compressor, igniting the gas turbine engine, and disengaging the clutch at an operational speed of the gas turbine engine.
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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：US20190055889A1
公开(公告)日：2019-02-21
申请号：US15679808
申请日：2017-08-17
Applicant: United Technologies Corporation
Inventor： Eric J. Heims , Gabriel L. Suciu , Brian Merry
Abstract: An air bleed system for a gas turbine engine includes a compressor case, fan panel, compartment, bleed port, bleed valve, and duct. The compressor case extends circumferentially around a core of the gas turbine engine. The fan panel is disposed radially outward from the compressor case. The compartment is disposed between the compressor case and fan panel. The bleed port extends from the compressor case into the compartment. The bleed valve is disposed on an outward end of the bleed port and is configured to selectively occupy an open or a closed position so as to regulate flow of a fluid. The duct extends between the bleed valve and the fan panel and is fluidly connected to the bleed port and to the opening of the fan panel. The duct is configured to transport the fluid from the engine core to the fan panel and through the opening.
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