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公开(公告)号：US09963972B2
公开(公告)日：2018-05-08
申请号：US14797923
申请日：2015-07-13
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
IPC: F01D5/08 , F01D11/00 , F01D25/12 , F01D5/06 , F01D5/12 , F01D5/34 , F01D25/00 , F04D29/32 , F04D29/58
CPC classification number: F01D5/087 , F01D5/06 , F01D5/081 , F01D5/12 , F01D5/34 , F01D11/006 , F01D25/005 , F01D25/12 , F04D29/321 , F04D29/58 , F05D2220/32 , F05D2220/3219 , F05D2240/30 , F05D2260/20 , F05D2300/175 , Y02T50/672 , Y02T50/676
Abstract: A gas turbine engine may comprise a first rotor with a primary flowpath along an outer diameter of the first rotor. A secondary flowpath may be radially inward from the primary flowpath. The secondary flowpath may pass through an opening through the first rotor. A blade may be disposed on a distal end of the first rotor. The blade may extend into the primary flowpath. A bleed tube may be in a wall of the primary flowpath and forward of the blade. The bleed tube may extend radially inward from the primary flowpath. The bleed tube may fluidly connect to the opening through the first rotor. A plenum may be aft of the blade and radially inward from the primary flowpath. The plenum may be fluidly connected to the opening through the first rotor. A second rotor may be aft of the plenum.
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公开(公告)号：US09920652B2
公开(公告)日：2018-03-20
申请号：US14617339
申请日：2015-02-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , William K. Ackermann , James D. Hill , Brian D. Merry
CPC classification number: F01D25/14 , F01D5/081 , F01D5/082 , F01D25/12 , F05D2220/3212 , F05D2240/24 , F05D2240/55 , F05D2260/20 , F05D2260/201 , F05D2260/213
Abstract: A section of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a thermally isolated area, and a first rotor disk and a second rotor disk. Each of the first and second rotor disks are provided within the thermally isolated area.
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公开(公告)号：US09869248B2
公开(公告)日：2018-01-16
申请号：US14647537
申请日：2013-05-29
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry
CPC classification number: F02C6/02 , F02C3/10 , F02C7/06 , F02K3/025 , F02K3/06 , F05D2220/324 , F05D2220/326 , F05D2250/31 , F05D2260/4031
Abstract: A method of configuring a plurality of gas turbine engines includes the steps of configuring each of the engines with respective ones of a plurality of propulsors. Each propulsor includes a propulsor turbine and one of a fan and a propeller. Each of the engines is configured with respective ones of a plurality of substantially mutually alike gas generators, with the respective propulsor turbine driven by products of combustion downstream of the gas generator.
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公开(公告)号：US20170167388A1
公开(公告)日：2017-06-15
申请号：US14967446
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Michael G. McCaffrey
CPC classification number: F02C9/18 , F01D17/105 , F01D25/12 , F02C7/143 , F02C7/185 , F02C7/32 , F02C7/36 , F04D29/284 , F05D2220/32 , F05D2220/3212 , F05D2260/211 , F05D2260/213 , F05D2260/4031 , F05D2260/606 , F05D2270/112 , F05D2270/335 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor, and at least one more upstream compressor. A turbine section has a high pressure turbine. A tap line taps air from at least one of the more upstream compressors in the 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, and delivers 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. An intercooling system is also disclosed.
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公开(公告)号：US20170058830A1
公开(公告)日：2017-03-02
申请号：US15173288
申请日：2016-06-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
CPC classification number: F02K3/06 , B64D27/26 , B64D2027/266 , B64D2027/268 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C7/20 , F02C7/36 , F02C9/18 , F02C9/20 , F02K1/15 , F05D2220/32 , F05D2220/36 , F05D2260/4031 , F05D2260/40311 , F05D2270/42
Abstract: A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a first nacelle which at least partially surrounds a second nacelle and the fan rotor, the fan section configured to communicate airflow into the first nacelle and the second nacelle, a first turbine, and a second turbine followed by the first turbine. The first turbine is configured to drive the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.
Abstract translation: 燃气涡轮发动机尤其包括风扇部分，其包括风扇转子，围绕发动机旋转轴线限定的齿轮系，至少部分地围绕第二机舱的第一机舱和风扇转子，风扇部分配置为 将气流传送到第一机舱和第二机舱，第一涡轮机和第二涡轮机，随后是第一涡轮机。 第一涡轮机构造成通过齿轮系驱动风扇转子。 静态结构包括第一发动机安装位置和第二发动机安装位置。
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Patent Agency Ranking
公开(公告)号：US20160290149A1
公开(公告)日：2016-10-06
申请号：US15036019
申请日：2014-11-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James D. Hill , Gabriel L Suciu , Brian D. Merry , Ioannis Alvanos
CPC classification number: F01D11/005 , F01D5/06 , F01D5/081 , F01D9/041 , F01D11/001 , F05D2220/32 , F05D2240/57 , F05D2240/80 , F05D2260/30 , Y02T50/676
Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first rotor disk, a second rotor disk, and a circumferentially segmented seal. The segmented seal engages the first rotor disk and the second rotor disk. The segmented seal further includes a fore surface contacting the first disk, an aft surface contacting the second disk, and a radially outer surface. Further, (1) the aft surface and (2) one of the fore surface and the radially outer surface include perforations to allow fluid to flow through the interior of the segmented seal.
Abstract translation: 本公开的一个示例性实施例涉及燃气涡轮发动机。 发动机包括第一转子盘，第二转子盘和周向分段密封件。 分段密封件接合第一转子盘和第二转子盘。 分段密封件还包括接触第一盘的前表面，接触第二盘的后表面和径向外表面。 此外，（1）后表面和（2）前表面和径向外表面中的一个包括穿孔以允许流体流过分段密封件的内部。
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公开(公告)号：US20160280387A1
公开(公告)日：2016-09-29
申请号：US14667975
申请日：2015-03-25
Applicant: United Technologies Corporation
Inventor： Nathan Snape , James D. Hill , Gabriel L. Suciu , Brian D. Merry
IPC: B64D33/02
CPC classification number: F02C7/14 , F05D2260/213 , F05D2260/232 , F05D2260/98 , Y02T50/671 , Y02T50/675
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.
Abstract translation: 飞机热管理系统包括第一流体系统，其包含第一流体，包含热中性传热流体的流体回路，包含第二流体的第二流体系统，被配置为将热量从第一流体传递到热 中性传热流体和被配置为将热量从热中性传热流体传递到第二流体的第二热交换器。 流体回路构造成以与第一流体的压力匹配的压力将热中性传热流体提供给第一热交换器。
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公开(公告)号：US20160131044A1
公开(公告)日：2016-05-12
申请号：US15000077
申请日：2016-01-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Alan H. Epstein , Wesley K. Lord , Michael E. McCune , Brian D. Merry
CPC classification number: F02C7/36 , F01D15/12 , F02C3/06 , F02C3/107 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2240/60 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.
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公开(公告)号：US20160053688A1
公开(公告)日：2016-02-25
申请号：US14813284
申请日：2015-07-30
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
CPC classification number: F02C7/12 , F01D5/066 , F01D5/084 , F01D5/087 , F01D11/001 , F01D25/12 , F01D25/24 , F02C3/04 , F02C7/20 , F04D29/164 , F04D29/321 , F04D29/545 , F04D29/584 , F05D2220/32 , F05D2260/221 , Y02T50/676
Abstract: A rotor for a gas turbine engine includes a cold shell, a hot shell, and a spoke. The spoke is connected to and extends radially outward from the cold shell. The hot shell is connected to the cold shell by the spoke and includes an axially extending outboard segment and an axially extending inboard segment. The outboard segment is connected to the inboard segment and the inboard segment is disposed radially inboard of the outboard segment for sealably engaging a stator blade shroud.
Abstract translation: 用于燃气涡轮发动机的转子包括冷壳，热壳和辐条。 辐条与冷壳连接并径向向外延伸。 热壳通过轮辐连接到冷壳，并且包括轴向延伸的外侧段和轴向延伸的内侧段。 外侧段连接到内侧段，并且内侧区段径向设置在外侧段的内侧，用于与定子叶片护罩密封接合。
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20.发明申请公开(公告)号：US20160047306A1
公开(公告)日：2016-02-18
申请号：US14922386
申请日：2015-10-26
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry
CPC classification number: F02C3/107 , F01D25/162 , F02K3/06
Abstract: A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a fan drive turbine section and a second turbine section. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. The second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed.
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