公开(公告)号：US10082078B2

公开(公告)日：2018-09-25

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: F02C7/14

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.

公开(公告)号：US10077666B2

公开(公告)日：2018-09-18

申请号：US14844082

申请日：2015-09-03

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  Mark F. Zelesky

IPC: F01D5/18 ,  F01D5/08 ,  F01D11/00 ,  F02C3/08 ,  F01D5/06

CPC classification number: F01D5/18 ,  F01D5/06 ,  F01D5/185 ,  F01D5/186 ,  F01D5/187 ,  F01D11/001 ,  F01D11/003 ,  F01D11/005 ,  F02C3/08 ,  F05D2220/32 ,  F05D2260/20 ,  Y02T50/676

Abstract: A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage.

公开(公告)号：US20180216535A1

公开(公告)日：2018-08-02

申请号：US15421593

申请日：2017-02-01

Applicant: United Technologies Corporation

Inventor： James D. Hill ,  Glenn Levasseur

IPC: F02C7/16

CPC classification number: F02C7/16 ,  B23P15/14 ,  F01D9/065 ,  F02C7/14 ,  F02C7/36 ,  F05D2260/208 ,  F16H1/36 ,  F28D15/02 ,  Y02T50/675

Abstract: A thermal management system for a geared architecture of a gas turbine engine includes an evaporator portion located at the geared architecture and configured to exchange thermal energy with the geared architecture via boiling of a volume of heat transfer fluid flowing therethrough and a condenser portion located at a fan bypass flowpath of the gas turbine engine to reject thermal energy from the volume of heat transfer fluid into the fan bypass flowpath. One or more fluid pathways extend from the evaporator portion to the condenser portion to convey the volume of heat transfer fluid therebetween.

公开(公告)号：US10006364B2

公开(公告)日：2018-06-26

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: F01D5/06 ,  F02C7/12 ,  F01D5/08 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F01D11/00 ,  F01D25/12 ,  F04D29/32 ,  F04D29/16 ,  F04D29/54 ,  F04D29/58

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.

公开(公告)号：US20170037782A1

公开(公告)日：2017-02-09

申请号：US15332249

申请日：2016-10-24

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  James D. Hill ,  William K. Ackermann

IPC: F02C7/18 ,  F02C7/141 ,  F01D5/08 ,  F02C3/04

CPC classification number: F02C7/18 ,  F01D5/082 ,  F01D9/02 ,  F02C3/04 ,  F02C6/08 ,  F02C6/18 ,  F05D2240/126 ,  F05D2240/129 ,  F05D2240/35 ,  F05D2260/14 ,  F05D2260/213 ,  F05D2300/175 ,  F23R3/04 ,  F23R3/045 ,  Y02T50/673 ,  Y02T50/676

Abstract: Air mixing systems for gas turbine engines include a heat exchanger, a first extraction conduit fluidly coupled to an inlet of the heat exchanger, a second extraction conduit fluidly coupled to an outlet of the heat exchanger, an injection conduit fluidly coupled to the second extraction conduit, an onboard injector supply chamber fluidly coupled to the injection conduit, and an onboard injector fluidly coupled to the onboard injector supply chamber.

Abstract translation: 用于燃气涡轮发动机的空气混合系统包括热交换器，流体耦合到热交换器的入口的第一提取管道，流体地联接到热交换器的出口的第二提取管道，流体地联接到第二提取管道 流体地联接到注射管道的车载喷射器供应室，以及流体地联接到车载喷射器供应室的板载喷射器。

公开(公告)号：US20160298483A1

公开(公告)日：2016-10-13

申请号：US14682653

申请日：2015-04-09

Applicant: United Technologies Corporation

Inventor： James D. Hill

IPC: F01D11/22 ,  F01D9/04 ,  F04D29/32

CPC classification number: F01D11/22 ,  F01D9/041 ,  F04D29/164 ,  F04D29/324 ,  F04D29/642 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/57

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.

Abstract translation: 一种系统包括一个包括至少一个定子翼型的定子组件。 该系统还包括转子组件，其包括构造为围绕轴线旋转的至少一个转子翼型件。 该系统还包括联接到定子组件并被构造成相对于转子组件在轴向上致动定子组件的致动器，产生轴向运动，使得至少一个转子翼型件和定子组件之间的间隙基于 定子组件的轴向位置。

公开(公告)号：US20160230661A1

公开(公告)日：2016-08-11

申请号：US14614785

申请日：2015-02-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  James D. Hill

IPC: F02C7/18 ,  F02C3/10

CPC classification number: F02C7/18 ,  F01D5/08 ,  F01D5/081 ,  F01D5/082 ,  F01D5/088 ,  F02C3/10 ,  F02C3/107 ,  F05D2220/3217 ,  F05D2220/3219 ,  F05D2250/411

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a first compressor having a first overall pressure ratio, and a second compressor having a second overall pressure ratio. A ratio of the first overall pressure ratio to the second overall pressure ratio is greater than or equal to about 2.0. Further, a section of the gas turbine engine includes a thermally isolated area.

Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机尤其包括具有第一总压力比的第一压缩机和具有第二总压力比的第二压缩机。 第一总压力比与第二总压力比的比率大于或等于约2.0。 此外，燃气涡轮发动机的一部分包括热隔离区域。

公开(公告)号：US20160208703A1

公开(公告)日：2016-07-21

申请号：US14600862

申请日：2015-01-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James D. Hill ,  William K. Ackermann

IPC: F02C7/18 ,  F02C3/04

CPC classification number: F02C7/18 ,  F01D5/081 ,  F01D5/082 ,  F01D9/02 ,  F01D25/12 ,  F02C3/04 ,  F02C6/06 ,  F02C6/08 ,  F02C7/12 ,  F02C7/185 ,  F02C9/18 ,  F02K3/115 ,  F05D2260/209 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2300/175 ,  F23R3/04 ,  F23R3/045 ,  Y02T50/676

Abstract: A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.

Abstract translation: 提供冷却系统。 冷却系统可以包括热交换器和流体耦合到热交换器的出口的第一导管。 环形通道可流体地联接到第一导管。 切向板载喷油器（TOBI）可以流体地联接到环形通道。 还提供燃气涡轮发动机，并且可以包括压缩机，与压缩机流体连通的燃烧器，以及围绕燃烧器和涡轮机的扩散器。 热交换器可以具有流体地联接到扩散器的入口。 第二导管可以流体耦合到热交换器的出口。 环形通道可以流体地联接到第二导管。 切向板载喷油器（TOBI）可以流体地联接到环形通道。

公开(公告)号：US20160208698A1

公开(公告)日：2016-07-21

申请号：US14600445

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  William Ackermann

IPC: F02C7/12

CPC classification number: F02C7/12 ,  F05D2260/213

Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.

Abstract translation: 本公开提供了与燃气涡轮发动机的热管理系统相关的系统和方法。 例如，热管理系统包括热中性传热流体回路，设置在流体回路上的第一热交换器和设置在流体回路上的第二热交换器。

公开(公告)号：US20160186578A1

公开(公告)日：2016-06-30

申请号：US14868903

申请日：2015-09-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  James D. Hill ,  Gopal Das

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/02

CPC classification number: F01D5/28 ,  F01D5/02 ,  F01D5/147 ,  F05D2230/23 ,  F05D2230/60 ,  F05D2240/24 ,  F05D2300/174 ,  F05D2300/5023 ,  Y02T50/671

Abstract: Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating temperature over 1180° F. (638° C.). At least two of the rotor assemblies include gamma TiAl intermetallic alloy blades. In an embodiment, a method of making a turbine having a plurality of rotor assemblies includes attaching a first gamma TiAl intermetallic alloy blade to an upstream stage of the plurality of rotor assemblies.

Abstract translation: 组件包括具有多个转子组件的低压涡轮机，其包括具有超过1180°F（638℃）的最大工作温度的第一伽马TiAl金属间刀片。 至少两个转子组件包括γTiAl金属间合金刀片。 在一个实施例中，制造具有多个转子组件的涡轮机的方法包括将第一伽马TiAl金属间合金叶片附接到多个转子组件的上游级。