公开(公告)号：SG11201403917TA

公开(公告)日：2014-09-26

申请号：SG11201403917T

申请日：2013-02-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GILSON JONATHAN ,  MORIN BRUCE L ,  REBA RAMONS A ,  TOPOL DAVID A ,  LORD WESLEY K

IPC: F02C7/045 ,  F02C7/24 ,  F02K3/06

Abstract: A fan section for a gas turbine engine has a fan rotor with a plurality of fan blades. A plurality of exit guide vanes are positioned to be downstream of the fan rotor. The fan rotor is driven through a gear reduction relative to a turbine section. The exit guide vanes are desired to address resultant sound from interaction of wakes from the fan blades across exit guide vanes. A gas turbine engine incorporating a fan section is also disclosed.

公开(公告)号：EP2820270A4

公开(公告)日：2015-12-02

申请号：EP13754643

申请日：2013-02-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GILSON JONATHAN ,  MORIN BRUCE L ,  REBA RAMONS A ,  TOPOL DAVID A ,  LORD WESLEY K

IPC: F02C7/045 ,  F01D9/04 ,  F02C7/24 ,  F02K3/06 ,  F04D29/66

CPC classification number: F01D9/041 ,  F01D25/162 ,  F02C3/107 ,  F02K3/06 ,  F04D29/544 ,  F04D29/667 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2250/191 ,  F05D2250/38 ,  F05D2260/40311 ,  F05D2260/96 ,  F05D2260/961

Abstract: A fan section for a gas turbine engine has a fan rotor with a plurality of fan blades. A plurality of exit guide vanes are positioned to be downstream of the fan rotor. The fan rotor is driven through a gear reduction relative to a turbine section. The exit guide vanes are desired to address resultant sound from interaction of wakes from the fan blades across exit guide vanes. A gas turbine engine incorporating a fan section is also disclosed.

Abstract translation: 用于燃气涡轮发动机的风扇部分具有带多个风扇叶片的风扇转子。 多个出口导向叶片位于风扇转子的下游。 风扇转子通过相对于涡轮部分的齿轮减速而被驱动。 出口导向叶片需要通过来自风扇叶片的离开引导叶片的相互作用来解决合成的声音。 还公开了一种并入风扇部分的燃气涡轮发动机。