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公开(公告)号：US20160186571A1
公开(公告)日：2016-06-30
申请号：US14797923
申请日：2015-07-13
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
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.
Abstract translation: 燃气涡轮发动机可以包括具有沿着第一转子的外径的主流路的第一转子。 二次流路可以从主流路径向向内。 二次流路可穿过第一转子的开口。 叶片可以设置在第一转子的远端上。 叶片可以延伸到主流路。 放气管可以在主流路的壁中并且在叶片的前方。 排放管可以从主流路径向向内延伸。 排放管可以通过第一转子流体连接到开口。 集气室可以是叶片后部并且从主流路径向向内。 气室可以通过第一转子流体连接到开口。 第二转子可能是集气室的后部。
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12.发明申请公开(公告)号：US20160024935A1
公开(公告)日：2016-01-28
申请号：US14802512
申请日：2015-07-17
Applicant: United Technologies Corporation
Inventor： Pitchaiah Vijay Chakka , James D. Hill , David R. Pack
CPC classification number: F01D5/18 , F01D5/141 , F01D5/147 , F01D5/28 , F05D2230/211 , F05D2300/1723 , Y02T50/673
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.
Abstract translation: 用于燃气涡轮发动机的叶片包括主体，该主体包括翼型件，该翼型件在翼型基座附近的0％跨度位置处沿径向方向延伸到翼型端部处的100％跨度位置。 翼型件包括具有第一密度的翼型底座附近的第一部分，并且包括具有第二密度的翼型末端附近的第二部分。 第二密度小于第一密度。 第二部分包括在径向方向上增加的真弦长度。
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公开(公告)号：US20150354822A1
公开(公告)日：2015-12-10
申请号：US14728991
申请日：2015-06-02
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
CPC classification number: F23R3/10 , F01D5/082 , F01D9/06 , F01D25/125 , F02C3/04 , F02C6/08 , F02C7/185 , F05D2220/323 , F05D2260/213 , F05D2270/303 , F05D2270/3062 , Y02T50/676
Abstract: A turbine injection system for a gas turbine engine includes a first end operable to receive air from a heat exchanger, a second end operable to distribute mixed cooling air to a turbine stage, an opening downstream of said first end and a mixing plenum downstream of said first end and said opening. The opening provides a direct fluid pathway into said turbine injection system.
Abstract translation: 一种用于燃气涡轮发动机的涡轮喷射系统包括可操作以从热交换器接收空气的第一端，可操作以将混合冷却空气分配到涡轮级的第二端，在所述第一端下游的开口和在所述第一端下游的混合增压室 第一端和开口。 开口提供到所述涡轮喷射系统的直接流体通路。
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公开(公告)号：US09021783B2
公开(公告)日：2015-05-05
申请号：US13650523
申请日：2012-10-12
Applicant: United Technologies Corporation
Inventor： James D. Hill , Michael J. Cuozzo
Abstract: The engine (10) includes at least one firing tube (12) wherein an exhaust stream (32) from the firing tube (12) drives a turbine (30). A scroll ejector attenuator (40) is secured between and in fluid communication with an outlet end (28) of the firing tube (12) and an inlet (76) of the turbine (30). The attenuator (40) defines a turning, narrowing passageway (72) that extends a distance the exhaust stream (32) travels before entering the turbine (30) to attenuate shockwaves and mix the pulsed exhaust stream (32) into an even stream with minimal temperature differences to thereby enhance efficient operation of the turbine (30) without any significant pressure decline of exhaust stream (32) pressure and without any backpressure from the attenuator (40) on the firing tube (12).
Abstract translation: 发动机（10）包括至少一个燃烧管（12），其中来自燃烧管（12）的排气流（32）驱动涡轮机（30）。 涡卷喷射器衰减器（40）固定在燃烧管（12）的出口端（28）和与涡轮机（30）的入口（76）流体连通之间。 衰减器（40）限定了在进入涡轮机（30）之前延伸排气流（32）移动一段距离的转动，变窄的通道（72），以便衰减冲击波并将脉冲排气流（32）混合成均匀的流 从而增强了涡轮机（30）的有效运行，而没有任何明显的排气流（32）的压力下降并且没有来自激发管（12）上的衰减器（40）的任何背压。
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公开(公告)号：US11215120B2
公开(公告)日：2022-01-04
申请号：US15424927
申请日：2017-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James D. Hill , Frederick M. Schwarz
Abstract: A gas turbine engine comprises a compressor section and a turbine section, the compressor section having a last compressor stage. High pressure cooling air is tapped from a location downstream of the last compressor stage and passed through a heat exchanger. Lower pressure air passes across the heat exchanger to cool the high pressure cooling air. A housing surrounds the compressor section and the turbine section and there being a space radially outwardly of the housing, and a mixing chamber received in the space radially outwardly of the housing, the mixing chamber receiving the high pressure cooling air downstream of the heat exchanger, and further receiving air at a temperature higher than a temperature of the high pressure cooling air downstream of the heat exchanger. Mixed air from the mixing chamber is returned into the housing and utilized to cool at least the turbine section.
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Patent Agency Ranking
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：US10520097B2
公开(公告)日：2019-12-31
申请号：US15405692
申请日：2017-01-13
Applicant: United Technologies Corporation
Inventor： James D. Hill
IPC: F16L37/00 , F16K1/12 , F16K27/02 , F01D17/14 , F16K1/42 , F01D25/12 , F01D25/18 , F02C7/232 , F02C6/08
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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公开(公告)号：US10392968B2
公开(公告)日：2019-08-27
申请号：US15495283
申请日：2017-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ram Ranjan , James D. Hill , Glenn Levasseur , Joel H. Wagner
Abstract: A turbine casing may comprise a casing body a heat pipe disposed in the casing body. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be located forward the condensation section. The vaporization section may be located in a high pressure turbine region of the casing body. The condensation section may be located in a low pressure turbine region of the casing body.
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公开(公告)号：US10323536B2
公开(公告)日：2019-06-18
申请号：US14682653
申请日：2015-04-09
Applicant: United Technologies Corporation
Inventor： James D. Hill
Abstract: A system includes a stator assembly including at least one stator airfoil. The system also includes a rotor assembly including at least one rotor airfoil configured to rotate about an axis. The system also includes an actuator coupled to the stator assembly and configured to actuate the stator assembly in an axial direction relative to the rotor assembly, creating an axial movement such that a clearance between the at least one rotor airfoil and the stator assembly varies based on an axial position of the stator assembly.
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公开(公告)号：US10094393B2
公开(公告)日：2018-10-09
申请号：US15023289
申请日：2014-08-01
Applicant: United Technologies Corporation
Inventor： James D. Hill , Gabriel L. Suciu , Jesse M. Chandler
Abstract: A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades. The inlet frame connects to an inlet end of the compressor case. The outlet frame connects to an outlet end of the compressor case portion at an end opposite the compressor case inlet end. An axially fore mounting structure of the mounting structure connects to the inlet frame. An axially aft mounting structure of the mounting structure connects to the outlet frame. A bridging structure of the mounting structure is offset from the compressor case and connects the fore and aft mounting structures, thereby bridging engine loads across the inlet and outlet frames to reduce load induced distortion of the compressor case portion.
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