公开(公告)号：US20140174056A1

公开(公告)日：2014-06-26

申请号：US14190429

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven M. Johnson ,  Frederick M. Schwarz

IPC: F02K3/06

CPC classification number: F02K3/06 ,  B64D27/26 ,  B64D2027/266 ,  B64D2027/268 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2270/42

Abstract: A gas turbine engine comprises a gear train defined along an axis. A spool along the axis drives the gear train and includes a low stage count low pressure turbine. A fan i s rotatable at a fan speed about the axis and driven by the low pressure turbine through the gear train. The fan speed is less than a speed of the low pressure turbine. A core is surrounded by a core nacelle defined about the axis. A fan nacelle i s mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10).

Abstract translation: 燃气涡轮发动机包括沿轴线限定的齿轮系。 沿着轴的线轴驱动齿轮系并且包括低阶数低压涡轮机。 风扇可以围绕轴线以风扇转速旋转，并由低压涡轮机通过齿轮系驱动。 风扇转速小于低压汽轮机的转速。 一个核心围绕着围绕轴定义的核心机舱。 一个风扇机舱至少部分安装在核心机舱周围，以便为风扇旁路气流定义一个风扇旁路气流路径。 由风扇旁路通道气流除以通过芯的气流所限定的旁路比大于约十（10）。