公开(公告)号：WO2007130768A1

公开(公告)日：2007-11-15

申请号：PCT/US2007/065750

申请日：2007-04-02

Applicant: ROHR, INC. ,  YU, Jia ,  CHIEN, Eugene

Inventor： YU, Jia ,  CHIEN, Eugene

IPC: F02K1/82

CPC classification number: F02K1/04 ,  F02K1/827 ,  F05D2230/13 ,  F05D2250/283 ,  F05D2260/96

Abstract: A sound-absorbing exhaust nozzle center plug (100) for an aircraft gas turbine engine can include an outer skin (102) and at least one forward cavity within the outer skin. At least one aft cavity can be located within the outer skin and substantially aft of the forward cavity (132). A perforated wall (130) including a plurality of first openings can be disposed between the forward and aft cavities. The outer skin can include a second plurality of openings (110) providing an acoustic pathway through the outer skin and into the forward cavity. The forward and aft cavities can be configured to absorb and dissipate relatively low-frequency sound energy emitted from an aircraft gas turbine engine's combustor.

Abstract translation: 用于飞机燃气涡轮发动机的吸音排气喷嘴中心塞（100）可以包括外皮（102）和外皮内的至少一个前腔。 至少一个后腔可以位于外表皮内并且基本上位于前腔（132）的后方。 包括多个第一开口的穿孔壁（130）可以设置在前空腔和后空腔之间。 外皮可以包括第二多个开口（110），其提供穿过外皮并进入前腔的声学路径。 前空腔和后空腔可以被配置为吸收和消散从飞机燃气涡轮发动机的燃烧器发射的相对低频的声能。