公开(公告)号：WO2014062491A2

公开(公告)日：2014-04-24

申请号：PCT/US2013064488

申请日：2013-10-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： JEWESS GORDON F ,  LYDON PATRICK M ,  BARKLEY ROBERT O ,  ALEXANDER ERIC J ,  BUNONE DAVIS

CPC classification number: F01D15/10 ,  F02C3/145 ,  F02C7/22 ,  F02C7/222 ,  F02C7/228 ,  F05D2220/768 ,  F05D2250/82 ,  F23C2900/03001 ,  F23R3/28 ,  F23R3/283 ,  F23R3/286 ,  F23R3/34

Abstract: A nozzle formed of one piece for a jet engine includes a mixing tube, a fuel conduit integrally formed with the mixing tube, and an opening through the fuel conduit and directed radially into the mixing tube.

Abstract translation: 由喷气发动机一体形成的喷嘴包括混合管，与混合管一体形成的燃料导管，以及通过燃料导管的径向引导到混合管中的开口。

公开(公告)号：WO2014123626A3

公开(公告)日：2014-11-20

申请号：PCT/US2013075623

申请日：2013-12-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： JONES ANTHONY C ,  TRAVELBEE CHARLES BRIAN ,  LYDON PATRICK M ,  ALEXANDER ERIC J ,  THAYALAKHANDAN NAGAMANY

IPC: F02C7/12 ,  F01D25/12 ,  F02C7/04 ,  F02C7/18

CPC classification number: F02K3/02 ,  B64C39/02 ,  B64C2201/048 ,  B64D27/20 ,  B64D33/02 ,  B64D33/08 ,  B64D2033/0273 ,  F02C7/18 ,  F02C9/18 ,  F02K1/822 ,  F42B15/10 ,  Y02T50/675

Abstract: A gas turbine engine has an inlet duct, which is configured to communicate with an inlet to a compressor. The inlet duct is further configured to communicate air outwardly of an outer casing of the gas turbine engine, and to pass the air along an axial length of the gas turbine engine to cool a component associated with the gas turbine engine.

Abstract translation: 燃气涡轮发动机具有入口管道，该入口管道被构造成与压缩机的入口连通。 进气管进一步构造成使空气与燃气涡轮发动机的外壳向外连通，并沿着燃气涡轮发动机的轴向长度传递空气以冷却与燃气涡轮发动机相关联的部件。

公开(公告)号：EP2935835A4

公开(公告)日：2015-12-23

申请号：EP13874584

申请日：2013-12-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： JONES ANTHONY C ,  TRAVELBEE CHARLES BRIAN ,  LYDON PATRICK M ,  ALEXANDER ERIC J ,  THAYALAKHANDAN NAGAMANY

IPC: F02C7/12 ,  B64D33/02 ,  B64D33/08 ,  F01D25/12 ,  F02C7/04 ,  F02C7/18

CPC classification number: F02K3/02 ,  B64C39/02 ,  B64C2201/048 ,  B64D27/20 ,  B64D33/02 ,  B64D33/08 ,  B64D2033/0273 ,  F02C7/18 ,  F02C9/18 ,  F02K1/822 ,  F42B15/10 ,  Y02T50/675

Abstract: A gas turbine engine has an inlet duct, which is configured to communicate with an inlet to a compressor. The inlet duct is further configured to communicate air outwardly of an outer casing of the gas turbine engine, and to pass the air along an axial length of the gas turbine engine to cool a component associated with the gas turbine engine.

公开(公告)号：EP2981696A4

公开(公告)日：2016-04-20

申请号：EP14778145

申请日：2014-03-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： JONES ANTHONY C ,  LYDON PATRICK M ,  THAYALAKHANDAN NAGAMANY ,  ALEXANDER ERIC J

IPC: F02C7/04 ,  B64D33/02 ,  F02C7/057 ,  F02C7/06 ,  F02C9/16

CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0273 ,  F02C3/04 ,  F02C7/06 ,  F05D2220/323 ,  F05D2250/51 ,  F05D2250/80 ,  F05D2250/82

Abstract: A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine. A rotor and a turbine drive a shaft to drive the rotor with the shaft including a bearing mounted at a location downstream of the nose cone upstream end.

Abstract translation: 燃气涡轮发动机具有鼻锥体，其具有鼻锥上游端，并且入口壳体在壳体上游端处包括多个独立的流动路径，其在鼻锥上游端的下游。 入口壳体包括在壳体上游端下游的混合部分，其混合来自分离的流动路径的气流，使得气流通常大约为燃气涡轮发动机的旋转轴线的360度。 转子和涡轮机驱动轴以驱动转子，轴包括安装在鼻锥上游端下游位置的轴承。