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公开(公告)号：US20150361890A1
公开(公告)日：2015-12-17
申请号：US14740312
申请日：2015-06-16
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
CPC classification number: F02C9/18 , F01D9/065 , F02C7/185 , Y02T50/671 , Y02T50/675
Abstract: A gas turbine engine includes a compressor section having a plurality of compressor stages, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, the turbine section having at least one stage, a compressor bleed structure disposed in one of the plurality of compressor stages and operable to remove air from the compressor stage, a heat exchanger having an input connected to the compressor bleed, and an output connected to an active cooling system of at least one turbine stage, and wherein the compressor stage in which the compressor bleed structure is disposed includes airflow at a pressure above a minimum pressure threshold, and wherein the airflow has a temperature above a maximum temperature threshold.
Abstract translation: 燃气涡轮发动机包括具有多个压缩机级的压缩机部分，与压缩机部分流体连接的燃烧器，与燃烧器部分流体连接的涡轮机部分，具有至少一个级的涡轮机部分， 的多个压缩机级，并且可操作以从压缩机级移除空气，具有连接到压缩机排气口的输入端的热交换器和连接到至少一个涡轮级的主动冷却系统的输出，并且其中压缩机级 压缩机排气结构被布置成包括处于最高压力阈值以上的压力的气流，并且其中气流具有高于最大温度阈值的温度。
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公开(公告)号：US20150354465A1
公开(公告)日：2015-12-10
申请号：US14729002
申请日：2015-06-02
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Mark F. Zelesky
CPC classification number: F02C3/13 , F01D5/081 , F01D25/12 , F02C3/04 , F02C7/18 , F02C7/185 , F02C9/18 , F05D2260/213 , F05D2270/112 , F05D2270/20 , F05D2270/3032 , F05D2270/3062 , Y02T50/673 , Y02T50/676
Abstract: A turbine cooling air generation system for a gas turbine engine includes a first fluid pathway connecting a compressor bleed outlet and a mixing valve, a second fluid pathway connecting the compressor bleed outlet and an input of a heat exchanger, and a third fluid pathway connecting an output of the heat exchanger and the mixing valve. The mixing valve is further connected to an input of a turbine stage active cooling system.
Abstract translation: 一种用于燃气涡轮发动机的涡轮机冷却空气产生系统包括连接压缩机排气口和混合阀的第一流体路径，连接压缩机排气口和热交换器的输入口的第二流体路径，以及连接 输出热交换器和混合阀。 混合阀进一步连接到涡轮级主动冷却系统的输入端。
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公开(公告)号：US20150354456A1
公开(公告)日：2015-12-10
申请号：US14732319
申请日：2015-06-05
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
Abstract: A cooling system for gas turbine engines includes a turbine rotor compartment defining a cooling air plenum. A plurality of turbine discs are rotatably housed within the rotor compartment. A cooling air inlet is in fluid communication with the plenum. Each turbine disc includes a cooling outlet in fluid communication with the plenum for cooling the rotor compartment.
Abstract translation: 用于燃气涡轮发动机的冷却系统包括限定冷却空气室的涡轮转子隔室。 多个涡轮盘可旋转地容纳在转子室内。 冷却空气入口与气室流体连通。 每个涡轮盘包括一个冷却出口，该冷却出口与用于冷却转子室的增压室流体连通。
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公开(公告)号：US10393016B2
公开(公告)日：2019-08-27
申请号：US15109049
申请日：2014-12-19
Applicant: United Technologies Corporation
Inventor： James D. Hill , Michael J. Cuozzo
Abstract: An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second zone to slow the air from the compressor; a plenum disposed in a third zone located next to second zone to provide the air from the compressor to chambers; and a splitter disposed in a fourth zone to split the air from the compressor into an airflow required by each pulse detonation tube for detonation.
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公开(公告)号：US10316671B2
公开(公告)日：2019-06-11
申请号：US14802512
申请日：2015-07-17
Applicant: United Technologies Corporation
Inventor： Pitchaiah Vijay Chakka , James D. Hill , David R. Pack
Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.
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Patent Agency Ranking
公开(公告)号：US20190072052A1
公开(公告)日：2019-03-07
申请号：US16179082
申请日：2018-11-02
Applicant: United Technologies Corporation
Inventor： James D. Hill , Roger F. Blinn , Michael J. Cuozzo
Abstract: A flow-management system may comprise a center body impermeable to air. A conical surface of the center body may face forward. A blocking surface of the center body may be coaxial with the conical surface and may comprise an annular recess. An annular ring may be aft of the center body and fluidly coupled with the blocking surface. A tube may encase the center body and annular ring. The annular ring may comprise an air-foil shape to direct a pulse to the blocking surface. The blocking surface may comprise a central peak and a circular ridge separated by the annular recess.
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公开(公告)号：US10151271B2
公开(公告)日：2018-12-11
申请号：US14754342
申请日：2015-06-29
Applicant: United Technologies Corporation
Inventor： James D. Hill , Roger F. Blinn , Michael J. Cuozzo
Abstract: A flow-management system may comprise a center body impermeable to air. A conical surface of the center body may face forward. A blocking surface of the center body may be coaxial with the conical surface and may comprise an annular recess. An annular ring may be aft of the center body and fluidly coupled with the blocking surface. A tube may encase the center body and annular ring. The annular ring may comprise an air-foil shape to direct a pulse to the blocking surface. The blocking surface may comprise a central peak and a circular ridge separated by the annular recess.
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公开(公告)号：US10138751B2
公开(公告)日：2018-11-27
申请号：US14733984
申请日：2013-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James D. Hill , Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
Abstract: A seal segment according to an exemplary aspect of the present disclosure includes, among other things, a first axial wall, a second axial wall radially spaced from the first axial wall and a radially outer wall that interconnects the first axial wall and the second axial wall. At least one curved member is radially inwardly offset from the radially outer wall and extending between the first and second axial walls.
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公开(公告)号：US20180291760A1
公开(公告)日：2018-10-11
申请号：US15484166
申请日：2017-04-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan Ortiz , Matthew A. Devore , Lane Mikal Thornton , James D. Hill
Abstract: A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface defining a diffuser chamber radially outwardly of the combustor, and a cooling air chamber wall positioned outwardly of the diffuser chamber and the combustor, and radially inwardly of a second wall to define a cooling air chamber. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor and is passed through a heat exchanger. Air downstream of the heat exchanger passes into the cooling chamber, and then to the blade outer air seal.
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公开(公告)号：US20180202557A1
公开(公告)日：2018-07-19
申请号：US15405692
申请日：2017-01-13
Applicant: United Technologies Corporation
Inventor： James D. Hill
CPC classification number: F16K1/12 , F01D17/145 , F01D25/12 , F01D25/18 , F02C6/08 , F02C7/232 , F05D2220/32 , F05D2250/311 , F05D2250/36 , F16K1/42 , F16K27/02 , F16K27/0254
Abstract: An assembly includes a valve housing and a valve element such as a poppet valve. The valve housing includes a tubular duct and an annular valve seat disposed within the tubular duct. A first flowpath includes an inner bore of the annular valve seat. A second flowpath includes an aperture formed between the annular valve seat and the tubular duct. The poppet valve is configured to engage the annular valve seat and substantially close the first flowpath when the poppet valve is in a first position. The poppet valve is further configured to disengage the annular valve seat and at least partially open the first flowpath when the poppet valve is in a second position.
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