公开(公告)号：WO2014149122A3

公开(公告)日：2014-09-25

申请号：PCT/US2013/078182

申请日：2013-12-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L ,  DAS, Gopal ,  ALVANOS, Ioannis ,  MERRY, Brian D. ,  HILL, James D ,  PENDA, Allan R

IPC: B22F3/105 ,  B22F7/02

Abstract: A process for manufacturing a turbine engine component includes the steps of: providing a powder containing gamma titanium aluminide; and forming a turbine engine component from said powder using a direct metal laser sintering technique.

Abstract translation: 制造涡轮发动机部件的方法包括以下步骤：提供含有γ-钛铝化物的粉末; 以及使用直接金属激光烧结技术由所述粉末形成涡轮发动机部件。

公开(公告)号：WO2014100316A1

公开(公告)日：2014-06-26

申请号：PCT/US2013/076347

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： HILL, James D. ,  SUCIU, Gabriel L. ,  ALVANOS, Ioannis ,  MERRY, Brian D.

IPC: F02C7/28 ,  F01D25/00 ,  F01D11/00

CPC classification number: F01D11/122 ,  F01D5/06 ,  F01D11/001 ,  F01D11/008 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/55 ,  F05D2250/71

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.

Abstract translation: 根据本公开的示例性方面的密封段包括第一轴向壁，与第一轴向壁径向间隔开的第二轴向壁和将第一轴向壁和第二轴向壁互连的径向外壁 。 至少一个弯曲构件径向向内偏离径向外壁并且在第一和第二轴向壁之间延伸。

公开(公告)号：WO2014098961A1

公开(公告)日：2014-06-26

申请号：PCT/US2013/043029

申请日：2013-05-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  HASEL, Karl L. ,  TSAY, Jessica

IPC: F01D5/02 ,  F02C7/00 ,  F02K3/00

CPC classification number: F02C9/00 ,  F01D13/006 ,  F01D13/02 ,  F02C3/10 ,  F02C3/107 ,  F02K3/06 ,  F02K3/062 ,  F05D2220/324 ,  F05D2220/326 ,  F05D2250/31 ,  F05D2260/4031

Abstract: A gas turbine engine has a first shaft including a first compressor rotor. A second shaft includes a second compressor rotor disposed upstream of the first compressor rotor. The second compressor rotor has a first overall pressure ratio. The first compressor rotor has a second overall pressure ratio, with a ratio of the first overall pressure ratio to the second overall pressure ratio being greater than or equal to about 3.0.

Abstract translation: 燃气涡轮发动机具有包括第一压缩机转子的第一轴。 第二轴包括设置在第一压缩机转子的上游的第二压缩机转子。 第二压缩机转子具有第一总压力比。 第一压缩机转子具有第二总压力比，第一总压力比与第二总压力比的比率大于或等于约3.0。

公开(公告)号：WO2014093279A1

公开(公告)日：2014-06-19

申请号：PCT/US2013/074009

申请日：2013-12-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SNAPE, Nathan ,  MERRY, Brian D. ,  PENDA, Allan R. ,  SUCIU, Gabriel L.

IPC: F02C9/18 ,  F01D17/00

CPC classification number: F02C9/18 ,  F02C6/08 ,  F02C6/12 ,  F02C7/141 ,  Y02T50/675

Abstract: A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.

Abstract translation: 公开的泄放空气系统利用来自高压压缩机的高压空气来驱动涡轮压缩机以增加从低压压缩机抽出的排出空气的压力。 从低压压缩机抽出的空气的压力低于高压压缩机所遇到的温度和压力。 涡轮压缩机增加了气流的压力，并且使得流入主排气通道的气流被传送到利用排放空气的系统。

公开(公告)号：WO2013180788A3

公开(公告)日：2013-12-05

申请号：PCT/US2013/030123

申请日：2013-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  GLAHN, Jorn A. ,  DYE, Christopher M.

IPC: F02C7/32 ,  F02C7/00 ,  F04D25/02

Abstract: A gas turbine engine has an impeller pump for delivering air to an environmental control system and a speed control pump connected to the impeller pump for driving the impeller pump at a constant speed.

公开(公告)号：WO2013116009A1

公开(公告)日：2013-08-08

申请号：PCT/US2013/022032

申请日：2013-01-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel, L. ,  MERRY, Brian D. ,  HASEL, Karl L.

IPC: F01D15/12 ,  F01D25/26 ,  F01D25/28 ,  F03D11/02 ,  F03D11/04 ,  F03D5/00 ,  F03B11/00 ,  F04D29/60

CPC classification number: F02K3/06 ,  F02C3/107 ,  F02C7/04 ,  F04D29/522 ,  F05D2260/40311 ,  F05D2270/17

Abstract: An exemplary geared turbomachine assembly includes a core inlet having a radially inner boundary that is spaced a first radial distance from a rotational axis of a turbomachine, and a compressor section inlet having a radially inner boundary that is spaced a second radial distance from the rotational axis. A ratio of the second radial distance to the first radial distance is of about 0.65 to about 0.9.

Abstract translation: 示例性的齿轮涡轮机组件包括具有径向内边界的芯入口，该径向内边界与涡轮机的旋转轴线间隔开第一径向距离;以及压缩机部分入口，其具有径向内边界，该径向内边界与旋转轴线间隔开第二径向距离 。 第二径向距离与第一径向距离的比率为约0.65至约0.9。

公开(公告)号：EP3584427A1

公开(公告)日：2019-12-25

申请号：EP19179765.3

申请日：2019-06-12

Applicant: United Technologies Corporation

Inventor： SCHWARZ, Frederick M. ,  LEVASSEUR, Glenn ,  MERRY, Brian D.

IPC: F02C6/08 ,  F02C7/18 ,  F02C9/18 ,  F02C7/06

Abstract: A gas turbine engine (20) includes a plurality of rotatable components housed within a main compressor section (102) and a turbine section (122). A cooling system (100; 199; 209) is connected to tap air from said main compressor section (102). A first tap (106) is connected to a first heat exchanger (110). The first heat exchanger (110) is connected to a cooling compressor (112) for raising a pressure of the tapped air downstream of the first heat exchanger (110). A second heat exchanger (124) is downstream of the cooling compressor (112), and a connection is downstream of the second heat exchanger (124) for delivering air to a bearing compartment (130). A connection intermediate the cooling compressor (112) and the second heat exchanger (124) delivers cooling air to at least one of the rotatable components.

公开(公告)号：EP3081768B1

公开(公告)日：2019-06-05

申请号：EP15199861.4

申请日：2015-12-14

Applicant: United Technologies Corporation

Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L.

IPC: F01D25/16 ,  F02K3/06 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F01D25/24 ,  F01D25/18

公开(公告)号：EP2935837B1

公开(公告)日：2019-02-06

申请号：EP13865215.1

申请日：2013-12-19

Applicant: United Technologies Corporation

Inventor： HILL, James D. ,  SUCIU, Gabriel L. ,  ALVANOS, Ioannis ,  MERRY, Brian D.

IPC: F01D11/00

公开(公告)号：EP3085924B1

公开(公告)日：2018-10-31

申请号：EP16166724.1

申请日：2016-04-22

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  STAUBACH, Joseph Brent ,  MERRY, Brian D.

IPC: F02C3/13 ,  F02C7/18 ,  F02C9/18

CPC classification number: F04D29/5826 ,  F01D25/12 ,  F02C3/13 ,  F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02C9/18 ,  F04D29/5833 ,  F05D2220/3212 ,  F05D2220/3217 ,  F05D2220/3219 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2270/3062 ,  Y02T50/675

Abstract: A gas turbine engine (121) comprises a main compressor section having a high pressure compressor (141) with a downstream most end (140), and more upstream locations (126). A turbine section has a high pressure turbine (144). A first tap taps air from at least one of the more upstream locations (126) in the main compressor section, passes the tapped air through a heat exchanger (122) and then to a cooling compressor (124). The cooling compressor (124) compresses air downstream of the heat exchanger (122). A second tap taps air from a location closer to the downstream most end (140) than the location(s) (126) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine (144). An intercooling system for a gas turbine engine (121) is also disclosed.