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.

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

IPC: F01D25/14 ,  F01D5/08 ,  F01D25/12

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.

公开(公告)号：US20170167385A1

公开(公告)日：2017-06-15

申请号：US14963545

申请日：2015-12-09

Applicant: United Technologies Corporation

Inventor： James D. Hill ,  Steven J. Laporte ,  Wendell V. Twelves, JR. ,  Stephen K. Kramer ,  Simon Pickford

IPC: F02C7/18

CPC classification number: F02C7/141 ,  F05D2260/213 ,  Y02T50/671 ,  Y02T50/676

Abstract: A thermal energy exchange system for cooling air of a gas turbine engine includes a heat exchanger located at a diffuser of the gas turbine engine. The diffuser is positioned axially between a compressor and a combustor of the gas turbine engine. A fuel source is operably connected to the heat exchanger to direct a flow of fuel through the heat exchanger via a fuel pipe and toward a fuel nozzle of the combustor. An airflow inlet directs a cooling airflow through the heat exchanger to reduce an airflow temperature via thermal energy exchange between the cooling airflow and the flow of fuel. An airflow outlet directs the cooling airflow from the heat exchanger toward one or more of components of the turbine to cool the one or more components.

公开(公告)号：US20170002735A1

公开(公告)日：2017-01-05

申请号：US14789036

申请日：2015-07-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jeffery F. Perlak ,  Joseph B. Staubach ,  Gabriel L. Suciu ,  James D. Hill ,  Frederick M. Schwarz

IPC: F02C3/107

CPC classification number: F02C3/107 ,  F02C3/10 ,  F02C3/145 ,  F05D2210/44 ,  F05D2260/4031

Abstract: A gas turbine engine according to the present disclosure includes a first compressor and a first turbine for driving the first compressor. A core section includes a second compressor and a second turbine for driving the second compressor. A third turbine is arranged fluidly downstream of the first turbine and the second turbine and configured to drive a power take-off. A first duct system is arranged fluidly between the low-pressure compressor and the core section. The first duct system is arranged to reverse fluid flow before entry into the core section.

Abstract translation: 根据本公开的燃气涡轮发动机包括第一压缩机和用于驱动第一压缩机的第一涡轮机。 核心部分包括用于驱动第二压缩机的第二压缩机和第二涡轮机。 第三涡轮机布置在第一涡轮机和第二涡轮机的流体下游并被配置成驱动动力输出。 第一管道系统流体地布置在低压压缩机和铁芯段之间。 第一管道系统布置成在进入核心部分之前逆转流体流动。

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

IPC: F01D11/00 ,  F01D9/04 ,  F01D5/06

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。

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。

公开(公告)号：US20160186579A1

公开(公告)日：2016-06-30

申请号：US14868951

申请日：2015-09-29

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  James D. Hill

IPC: F01D5/28 ,  F01D9/04 ,  F01D25/06 ,  F01D5/14

CPC classification number: F01D5/28 ,  B23K35/0233 ,  B23K35/0244 ,  B23K35/025 ,  B23K35/325 ,  C23C24/00 ,  F01D5/147 ,  F01D9/041 ,  F01D9/042 ,  F01D25/06 ,  F01D25/246 ,  F05D2230/23 ,  F05D2230/236 ,  F05D2230/60 ,  F05D2240/80 ,  F05D2300/174 ,  F05D2300/175 ,  F05D2300/5023

Abstract: A hybrid component for a turbine engine having a casing includes a first part of a gamma TiAl intermetallic alloy and a second part of a material of at least one of nickel, a nickel base, a cobalt base, an iron base superalloy or mixtures thereof. The second part is coupled to and configured to attach the first part to the casing of the engine. The first and second parts are attached to each other by transient liquid phase (TLP) bonding.

Abstract translation: 用于具有壳体的涡轮发动机的混合部件包括伽马TiAl金属间合金的第一部分和镍，镍基，钴基，铁基超级合金或其混合物中的至少一种的材料的第二部分。 第二部分联接并构造成将第一部分附接到发动机的壳体。 第一和第二部分通过瞬态液相（TLP）结合而相互连接。

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

IPC: F02C7/12 ,  F02C3/04 ,  F02C7/20 ,  F01D25/24

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。

公开(公告)号：US20160025040A1

公开(公告)日：2016-01-28

申请号：US14754342

申请日：2015-06-29

Applicant: United Technologies Corporation

Inventor： James D. Hill ,  Roger F. Blinn ,  Michael J. Cuozzo

IPC: F02K7/02 ,  F17D3/01

CPC classification number: F02K7/02 ,  F02C5/10 ,  F02C5/11 ,  F02K7/067

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.

Abstract translation: 流量管理系统可以包括不透气的中心体。 中心体的锥形表面可能面向前方。 中心体的阻挡表面可以与锥形表面同轴并且可以包括环形凹部。 环形环可以是中心体的后部并且与阻挡表面流体连接。 管可以包住中心体和环形环。 环形环可以包括将箔脉冲引导到阻挡表面的空气箔形状。 阻挡表面可以包括由环形凹部分开的中心峰和圆形脊。

公开(公告)号：US20150247456A1

公开(公告)日：2015-09-03

申请号：US14608227

申请日：2015-01-29

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  James D. Hill ,  Jesse M. Chandler

IPC: F02C3/14 ,  F02C6/02 ,  F02C3/06

CPC classification number: F02C3/14 ,  F02C3/06 ,  F02C3/10 ,  F02C6/02 ,  F02C7/05 ,  F02K3/12 ,  F05D2220/32 ,  F05D2250/314

Abstract: A gas turbine engine has a propulsion unit and a gas generating core. The propulsion unit includes a fan and a free turbine, wherein the free turbine is connected to drive the fan about a first axis. The gas generating core includes a compressor, a combustion section, and a gas generating core turbine. The compressor and the gas generating core turbine are configured to rotate about a second axis. An inlet duct is configured to deliver air from the fan to the gas generating core. The inlet duct has a crescent shaped cross-section near the fan.

Abstract translation: 燃气涡轮发动机具有推进单元和气体发生芯。 推进单元包括风扇和自由涡轮机，其中自由涡轮机被连接以围绕第一轴线驱动风扇。 气体发生芯包括压缩机，燃烧部分和气体发生芯涡轮机。 压缩机和气体发生芯涡轮机构造成围绕第二轴线旋转。 入口管道构造成将空气从风扇输送到气体生成芯。 入口管道在风扇附近具有月牙形横截面。