公开(公告)号：WO2006110122A3

公开(公告)日：2007-04-05

申请号：PCT/US2004039989

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORP ,  SUCIU GABRIEL L ,  PORTLOCK LAWRENCE E ,  MERRY BRIAN

Inventor： SUCIU GABRIEL L ,  PORTLOCK LAWRENCE E ,  MERRY BRIAN

IPC: F16K7/10 ,  F01D5/02 ,  F01D17/14 ,  F02C3/073 ,  F02C3/14 ,  F02C6/08 ,  F02C9/18 ,  F02K3/068 ,  F16K7/12 ,  F16K31/126

CPC classification number: F16K7/10 ,  F01D5/022 ,  F01D17/14 ,  F01D17/141 ,  F01D17/143 ,  F02C3/073 ,  F02C3/14 ,  F02C6/08 ,  F02C9/18 ,  F02K3/068 ,  F04D27/0215 ,  F04D27/023 ,  F05D2300/501 ,  F16K7/123 ,  F16K31/1266

Abstract: A compressor (22) for a turbine engine (10) includes an inflatable bleed valve (57) that selectively bleeds core airflow from the compressor. The bleed valve has an inlet (58) leading from the compressor and a passageway (112) leading from the inlet. An inflatable valve (116) selectively obstructs the passageway based upon a controlled supply of high pressure air to the inflatable valve. The supply of high pressure air may be compressed core airflow from an area downstream of the inlet to the bleed valve .

Abstract translation: 用于涡轮发动机（10）的压缩机（22）包括选择性地从压缩机中排出核心气流的可膨胀放气阀（57）。 排放阀具有从压缩机引出的入口（58）和从入口引出的通道（112）。 充气阀（116）基于受控地向可充气阀供应高压空气来选择性地阻塞通道。 高压空气的供应可以是从入口下游到排放阀的压缩空气流。

公开(公告)号：WO2006059970A2

公开(公告)日：2006-06-08

申请号：PCT/US2004039972

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORP ,  SUCIU GABRIEL L ,  PAGLUICA GINO J ,  DUONG LOC QUANG ,  PORTLOCK LAWRENCE E

Inventor： SUCIU GABRIEL L ,  PAGLUICA GINO J ,  DUONG LOC QUANG ,  PORTLOCK LAWRENCE E

IPC: F02C7/36 ,  F02C3/113

CPC classification number: F02K3/06 ,  F02C3/113 ,  F02C7/36 ,  F04D25/04 ,  F05D2260/40311

Abstract: A turbine engine provides a differential gear system coupling the turbine to the bypass fan and the compressor. In this manner, the power/speed split between the bypass fan and the compressor can be optimized under all conditions. In the example shown, the turbine drives a sun gear, which drives a planet carrier and a ring gear in a differential manner. One of the planet carrier and the ring gear is coupled to the bypass fan, while the other is coupled to the compressor.

Abstract translation: 涡轮发动机提供将涡轮联接到旁路风扇和压缩机的差速齿轮系统。 以这种方式，可以在所有条件下优化旁通风扇和压缩机之间的功率/速度分配。 在所示的示例中，涡轮驱动太阳齿轮，其以差动方式驱动行星架和齿圈。 行星架和环形齿轮中的一个联接到旁路风扇，而另一个联接到压缩机。

公开(公告)号：WO2014011245A2

公开(公告)日：2014-01-16

申请号：PCT/US2013033207

申请日：2013-03-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCUNE MICHAEL E ,  SHERIDAN WILLIAM G ,  PORTLOCK LAWRENCE E

CPC classification number: F02K3/06 ,  F01D25/18 ,  F02C3/107 ,  F05D2260/40311 ,  F16H57/0471 ,  F16H57/0479 ,  Y02T50/671

Abstract: A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed.

Abstract translation: 燃气涡轮发动机具有风扇，第一和第二压缩机级，第一和第二涡轮机级。 第一个涡轮机级以高速驱动第二压缩机级。 第二涡轮级驱动第一压缩机级作为低阀芯的一部分。 齿轮系用低速轴驱动风扇，使得风扇和第一压缩机级以相同的方向旋转。 高阀芯在比低阀芯更高的压力下运行。 还公开了一种润滑系统。

公开(公告)号：DE602004029950D1

公开(公告)日：2010-12-16

申请号：DE602004029950

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  PORTLOCK LAWRENCE E ,  MERRY BRIAN

IPC: F02C7/36 ,  F02C3/073 ,  F02K3/068

公开(公告)号：DE602007006253D1

公开(公告)日：2010-06-17

申请号：DE602007006253

申请日：2007-08-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCUNE MICHAEL E ,  PORTLOCK LAWRENCE E

IPC: F16H57/08 ,  F01D5/02 ,  F16H57/04

公开(公告)号：CA2936576C

公开(公告)日：2018-05-01

申请号：CA2936576

申请日：2016-07-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCUNE MICHAEL E ,  PORTLOCK LAWRENCE E ,  SCHWARZ FREDERICK M

IPC: F02C7/36 ,  F02C7/06

Abstract: A turbine engine has a fan shaft. At least one tapered bearing is mounted on the fan shaft. The fan shaft includes at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear. A ring gear surrounds and meshes with the intermediate gears. Each of the intermediate gears are supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train. The turbine section has a fan drive turbine that includes a pressure ratio that is greater than about 5. The fan includes a pressure ratio that is less than about 1.45, and the fan has a bypass ratio of greater than about ten (10).

公开(公告)号：CA2936576A1

公开(公告)日：2017-02-12

申请号：CA2936576

申请日：2016-07-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCUNE MICHAEL E ,  PORTLOCK LAWRENCE E ,  SCHWARZ FREDERICK M

IPC: F02C7/36 ,  F02C7/06

Abstract: A turbine engine has a fan shaft. At least one tapered bearing is mounted on the fan shaft. The fan shaft includes at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear. A ring gear surrounds and meshes with the intermediate gears. Each of the intermediate gears are supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train. The turbine section has a fan drive turbine that includes a pressure ratio that is greater than about 5. The fan includes a pressure ratio that is less than about 1.45, and the fan has a bypass ratio of greater than about ten (10).

公开(公告)号：DE602004020125D1

公开(公告)日：2009-04-30

申请号：DE602004020125

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PORTLOCK LAWRENCE E

IPC: F01D25/18 ,  F02C7/06 ,  F16H57/04

公开(公告)号：ES2695074T3

公开(公告)日：2018-12-28

申请号：ES12198045

申请日：2012-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCUNE MICHAEL E ,  PORTLOCK LAWRENCE E ,  SCHWARZ FREDERICK M

IPC: F02C3/107 ,  F02C7/36 ,  F02K3/06

Abstract: Un motor (10) de turbina que comprende: un árbol (20) de ventilador; un ventilador (18); y un tren (22) de engranajes epicicloidales acoplado para accionar el ventilador (18), incluyendo el tren (22) de engranajes epicicloidales un portador (26), que soportan engranajes (32) intermedios que engranan con un engranaje (30) solar, y un engranaje (38) de anillo que rodea y engrana con los engranajes (32) intermedios, caracterizado por que: cada uno de los engranajes (32) intermedios es soportado sobre un cojinete (34) de apoyo; el tren (22) de engranajes epicicloidales define una relación de reducción de engranaje de más de o igual a 2,5; el motor (10) comprende además al menos un cojinete (80) cónico montado sobre el árbol (20) de ventilador; el árbol (20) de ventilador incluye al menos un paso (82) que se extiende radialmente adyacente al menos a un cojinete (80) cónico; al menos un cojinete (80) cónico incluye un primer cojinete (80a) cónico y un segundo cojinete (80b), de rodillo cónico axialmente Espaciado, y al menos un paso (82) que se extiende radialmente incluye: un primer paso (82a) y un segundo paso (82b), estando ubicado el primer paso (82a) en un lado axialmente hacia adelante del primer cojinete (80a) cónico y estando ubicado el segundo paso (82b) en un lado axialmente hacia atrás del primer cojinete (80a) cónico; y un tercer paso y un cuarto paso, estando ubicado el tercer paso en un lado axialmente hacia delante del segundo cojinete (80b) cónico y estando ubicado el cuarto paso en un lado axialmente hacia atrás del segundo cojinete (80b) cónico; y el ventilador (18) tiene una relación de presión que es menor que 1,45 durante la operación y es montado para rotación sobre el cojinete (80) cónico.

公开(公告)号：SG11201404964XA

公开(公告)日：2014-10-30

申请号：SG11201404964X

申请日：2013-03-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCUNE MICHAEL E ,  SHERIDAN WILLIAM G ,  PORTLOCK LAWRENCE E

IPC: F02C7/06 ,  F01D25/18

Abstract: A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed.