公开(公告)号：EP3940201A1

公开(公告)日：2022-01-19

申请号：EP21196396.2

申请日：2013-12-18

申请人： Raytheon Technologies Corporation

发明人： LORD, Wesley K. ,  MALECKI, Robert E. ,  QIU, Yuan J. ,  ROSE, Becky E. ,  GILSON, Jonathan

IPC分类号： F01D5/14 ,  F01D5/12 ,  F02C7/00 ,  F02C7/04

摘要： According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and 0.45.

公开(公告)号：EP3985240A1

公开(公告)日：2022-04-20

申请号：EP21197138.7

申请日：2016-12-23

申请人： Raytheon Technologies Corporation

发明人： QIU, Yuan J. ,  MALECKI, Robert E. ,  LORD, Wesley K.

IPC分类号： F02C7/04 ,  B64D33/02

摘要： A fan assembly for a gas turbine engine (20) includes a fan (42) including a plurality of fan blades (92). Each fan blade extends radially outwardly from a fan hub to a blade tip (94). The plurality of blade tips define a fan diameter (D). A nacelle (80) surrounds the fan (42) and defines a fan inlet upstream of the fan (42), relative to an airflow direction into the fan (42). The nacelle (80) has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade of the plurality of fan blades (92). A ratio of inlet length to fan diameter (D) is between 0.20 and 0.45. A nacelle (80) inner surface defines a nacelle flowpath. The nacelle flowpath has a convex throat portion (122) and a concave diffusion portion (126) between the throat portion and the leading edge of the fan blade at a bottommost portion of the nacelle (80).