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公开(公告)号：US20180171815A1
公开(公告)日：2018-06-21
申请号：US15827132
申请日：2017-11-30
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian Merry , William G. Sheridan , Michael E. McCune
CPC classification number: F01D15/12 , F01D5/06 , F01D15/08 , F01D15/10 , F01D25/16 , F01D25/18 , F02C7/32 , F02C7/36 , F05D2220/32 , F05D2240/60 , F05D2260/402 , F05D2260/4031 , F05D2270/024 , F16H1/222 , F16H15/04 , F16H37/021
Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, an accessory drive gearbox a first towershaft interconnecting the accessory drive gearbox and the first or second turbine shaft, and a multispeed transmission interconnecting the accessory drive gearbox and at least one accessory component.
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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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公开(公告)号：US09988935B2
公开(公告)日：2018-06-05
申请号：US14788089
申请日：2015-06-30
Applicant: United Technologies Corporation
Inventor： James Hill , Brian Merry , Gabriel Suciu
CPC classification number: F01D25/14 , F01D5/084 , F02C7/12 , F02C7/18 , F04D29/321 , F04D29/584 , Y02T50/673 , Y02T50/676
Abstract: A gas turbine engine may include an axial high pressure compressor having an air flow pathway positioned between the inner and outer rim of the rotor section. The air flow pathway includes an inlet port, a transition segment, an axial segment, and an outlet port. The pathway may be a tube having an ovoid cross sectional shape and is substantially co-planar to the outer surface of the outer rim. The pathway may traverse the rotor section from the first rotor segment to the rear hub.
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公开(公告)号：US09897098B2
公开(公告)日：2018-02-20
申请号：US14793503
申请日：2015-07-07
Applicant: United Technologies Corporation
Inventor： James Hill , Brian Merry , Gabriel Suciu
CPC classification number: F04D29/083 , F01D11/005 , F01D11/006 , F04D17/08 , F04D17/122 , F04D29/284 , F04D29/286 , F05B2230/236
Abstract: A gas turbine engine includes an axial compressor which includes a rotor assembly including a first rotor segment with a first inner rim, a first sealing surface, and a first aft engagement feature, and a second rotor segment positioned aft of the first rotor segment and having a second inner rim, a second sealing surface, and a second inner rim with a second fore engagement feature that is complementary to the first aft engagement feature. The first and second sealing surfaces are complementary to each other, and are bonded together via a transient liquid phase diffusion process. The first and second sealing surfaces are disposed on the outer rim. The first aft engagement member may be a notch that is complementary to the second fore engagement feature, which may be a shelf.
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公开(公告)号：US09879537B2
公开(公告)日：2018-01-30
申请号：US14793479
申请日：2015-07-07
Applicant: United Technologies Corporation
Inventor： James Hill , Brian Merry , Gabriel Suciu
CPC classification number: F01D5/085 , F01D5/084 , F01D11/003 , F01D11/005 , F02C7/12 , F02C7/28 , F04D29/083 , F04D29/321 , F04D29/584 , Y02T50/676
Abstract: A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel. The cooling channels are configured to delivery air to contact the inner surface of the rear hub.
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Patent Agency Ranking
公开(公告)号：US20160032726A1
公开(公告)日：2016-02-04
申请号：US14793479
申请日：2015-07-07
Applicant: United Technologies Corporation
Inventor： James Hill , Brian Merry , Gabriel Suciu
CPC classification number: F01D5/085 , F01D5/084 , F01D11/003 , F01D11/005 , F02C7/12 , F02C7/28 , F04D29/083 , F04D29/321 , F04D29/584 , Y02T50/676
Abstract: A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel. The cooling channels are configured to delivery air to contact the inner surface of the rear hub.
Abstract translation: 燃气涡轮发动机包括轴向高压压缩机，其包括设置在后转子部分的后方的后轮毂。 后轮毂包括内表面，外表面和密封面，其中密封面与后转子段密封接合，并与冷却通道流体连通。 冷却通道构造成输送空气以接触后轮毂的内表面。
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公开(公告)号：US11156161B2
公开(公告)日：2021-10-26
申请号：US16111870
申请日：2018-08-24
Applicant: United Technologies Corporation
Inventor： Nathan Snape , James D. Hill , Gabriel L. Suciu , Brian Merry
IPC: F02C7/14
Abstract: An aircraft thermal management system includes a first fluid system containing a first fluid, a fluid loop containing a thermally neutral heat transfer fluid, a second fluid system containing a second fluid, a first heat exchanger configured to transfer heat from the first fluid to the thermally neutral heat transfer fluid, and a second heat exchanger configured to transfer heat from the thermally neutral heat transfer fluid to the second fluid. The fluid loop is configured to provide the thermally neutral heat transfer fluid to the first heat exchanger at a pressure that matches the pressure of the first fluid.
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公开(公告)号：US10808622B2
公开(公告)日：2020-10-20
申请号：US16047634
申请日：2018-07-27
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Brian Merry
Abstract: A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.
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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：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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