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公开(公告)号：US10669938B2
公开(公告)日：2020-06-02
申请号：US14771074
申请日：2014-02-28
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , William K. Ackermann
IPC: F02C7/00 , F02C7/18 , F01D17/10 , F02C6/08 , F01D9/04 , F01D9/06 , F02C7/06 , F02C7/14 , F01D5/02 , F02C3/04 , F02C7/04 , F01D25/24 , F04D29/54 , F01D25/12
Abstract: A diffuser for a gas turbine engine is provided that includes an outer shroud, an inner shroud, a multiple of struts between said outer shroud and said inner shroud to define an annular flow path, and a mid-span pre-diffuser inlet in communication with said annular flow path.
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公开(公告)号：US10662880B2
公开(公告)日：2020-05-26
申请号：US14692090
申请日：2015-04-21
Applicant: United Technologies Corporation
Inventor： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
IPC: F02C9/18 , F02C3/04 , F02C7/20 , F01D1/02 , F01D5/02 , F01D9/04 , F01D25/24 , F02C7/36 , F02C3/107 , F02K3/06 , F02C3/113 , F02K3/02 , F02K3/075 , F02K7/06
Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
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公开(公告)号：US20200025105A1
公开(公告)日：2020-01-23
申请号：US16374995
申请日：2019-04-04
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Michael G. McCaffrey
Abstract: A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.
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公开(公告)号：US10526976B2
公开(公告)日：2020-01-07
申请号：US15498764
申请日：2017-04-27
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Hung Duong , Jonathan F. Zimmitti , William G. Sheridan , Michael E. McCune , Brian Merry
IPC: F02C7/36
Abstract: A gas turbine engine comprises a high speed spool and a low speed spool. A low speed power takeoff is driven by the low speed spool and a high speed power takeoff is driven by the high speed spool. The low speed power takeoff drives a plurality of low speed driven accessories about low speed spool drive axes and the high speed power takeoff drives a plurality of high speed driven accessories about high speed spool drive axes. The low speed spool drive axes are generally tangential to an envelope defined about a center axis of the engine, and the high speed spool drive axes are generally tangential to an envelope defined about the center.
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公开(公告)号：US10526910B2
公开(公告)日：2020-01-07
申请号：US16059377
申请日：2018-08-09
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Federico Papa
Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.
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Patent Agency Ranking
公开(公告)号：US10480419B2
公开(公告)日：2019-11-19
申请号：US14745567
申请日：2015-06-22
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, passing the tapped air through a first heat exchanger and then to a cooling compressor. A second tap taps air from a location closer to the downstream most end than the location of the first tap, and the first and second taps mix together and are delivered into the high pressure turbine. The cooling compressor is positioned downstream of the first heat exchanger, and upstream of a location where air from the first and second taps mix together.
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公开(公告)号：US10450957B2
公开(公告)日：2019-10-22
申请号：US15412203
申请日：2017-01-23
Applicant: United Technologies Corporation
Inventor： Matthew Robert Pearson , Gabriel L. Suciu , Justin R. Urban
IPC: F01D25/12 , F02C7/04 , F02C7/12 , F02C7/14 , F02C3/04 , F28D15/02 , F01D5/08 , F01D21/00 , F01D25/10 , F28D15/04 , F28D21/00
Abstract: A gas turbine engine includes a rotor section proximate to a combustor section, where the rotor section is subject to bowing effects due to thermal differences and heat transfer at engine shutdown. The gas turbine engine also includes a heat pipe system. The heat pipe system includes one or more heat pipes installed between an upper portion of the rotor section and a lower portion of the rotor section. The heat pipe system is operable to accept heat at a hot side of the heat pipe system at the upper portion, flow heat from the hot side to a cold side of the heat pipe system, and reject heat from the cold side of the heat pipe system at the lower portion to reduce a thermal differential between the upper portion and the lower portion at engine shutdown.
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公开(公告)号：US10385774B2
公开(公告)日：2019-08-20
申请号：US15268713
申请日：2016-09-19
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Tania Bhatia Kashyap , Mark F. Zelesky , Arthur W. Utay , Gabriel L. Suciu , Thomas N. Slavens , Kevin L. Rugg , Brian Merry
Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.
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公开(公告)号：US10378453B2
公开(公告)日：2019-08-13
申请号：US14844097
申请日：2015-09-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Julian Partyka , David R. Pack , James D. Hill
Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.
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公开(公告)号：US10352241B2
公开(公告)日：2019-07-16
申请号：US15970516
申请日：2018-05-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nathan Snape , Gabriel L. Suciu , Brian D. Merry , James D. Hill , William K. Ackermann
IPC: F02C7/12
Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.
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