公开(公告)号：EP2909458A4

公开(公告)日：2016-07-20

申请号：EP13870075

申请日：2013-10-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HASEL KARL L

IPC: F02C7/057 ,  F02C3/04 ,  F02K3/04 ,  F02K3/06 ,  F02K3/075

CPC classification number: F02K3/075 ,  F02K3/06

公开(公告)号：EP2946102A4

公开(公告)日：2016-01-20

申请号：EP13872228

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HASEL KARL L

IPC: F02K3/06 ,  F02C7/36

CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2260/4031

Abstract: Please replace the abstract with the following rewritten abstract. No new matter has been added. An example gas turbine engine includes, among other things, a geared architecture rotatably coupling a fan drive shaft to an engine fan, the geared architecture having a speed reduction ratio that is greater than or equal to 2.4. The gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90.

公开(公告)号：EP2809936A4

公开(公告)日：2015-09-02

申请号：EP13775841

申请日：2013-01-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HASEL KARL L ,  SMITH PETER G ,  OCHS STUART S

IPC: F02K3/02

CPC classification number: F01D17/162 ,  F04D29/563 ,  F05D2220/36 ,  F05D2240/121

Abstract: A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has an expansion ratio greater than or equal to about 5. The fan has a bypass ratio greater than or equal to about 8. In other features, a turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.

公开(公告)号：EP2780570A4

公开(公告)日：2015-05-20

申请号：EP13852366

申请日：2013-09-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SHERIDAN WILLIAM G ,  HASEL KARL L

IPC: F02C7/36 ,  F02K3/06

CPC classification number: F02C7/36 ,  F01D1/04 ,  F01D9/041 ,  F01D25/162 ,  F02C3/04 ,  F02C7/00 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/50 ,  F05D2260/40311

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an axis and a speed reduction device in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps.

Abstract translation: 燃气涡轮发动机包括发动机中心线纵向轴线和风扇部分，风扇部分包括具有风扇叶片并可围绕发动机中心线纵向轴线旋转的风扇。 小于约1400ft / sec的低校正风扇叶尖速度和低校正风扇叶尖速度是在环境温度除以[（Tram°R）/（518.7°R）] 0.5时确定的实际风扇叶尖速度，其中T 表示环境温度，以度兰为单位。 旁路比大于约11，减速装置具有齿轮比齿轮系。 分别与第一和第二轴连通的低压和高压涡轮机。 第一和第二轴是同心的，并且经由至少一个轴承系统安装，用于围绕发动机中心线纵向轴线旋转，并且第一轴通过减速装置与风扇连通，低压涡轮机包括四个台阶。