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公开(公告)号：US20160001890A1
公开(公告)日：2016-01-07
申请号：US14771431
申请日：2014-03-03
CPC分类号： B64D33/06 , B64D41/00 , B64D2041/002 , F01D25/30 , F02C7/24 , F02C7/32 , F05D2220/50 , F05D2260/96 , Y02T50/44
摘要： An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.
摘要翻译： 一种用于燃气涡轮发动机飞行器中的APU的排气系统，其具有减少排气噪声的尾锥。 APU排气衬套连接到APU并延伸到尾锥处的椭圆形切口。衬套具有从APU到靠近尾锥的点的第一恒定横截面，以及从接近尾部点的第二个增加的横截面 尾锥到衬里切口。 衬里转向尾部侧面。 衬套切口进一步放大至少一个更大的切口。
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公开(公告)号：US20150361902A1
公开(公告)日：2015-12-17
申请号：US14764998
申请日：2014-02-26
发明人： James C. Napier , Jay M. Francisco
IPC分类号： F02C9/18
CPC分类号： F02C9/18 , F04D27/0238 , F05D2260/96 , F05D2270/101
摘要： An anti-surge mechanism has a duct for tapping compressed air and delivering that air into an exhaust flow. A selectively open valve allows the tapped air to flow into the exhaust flow through a plurality of holes. The holes are sized to tune a frequency of a sound created by the tapped air to a frequency range outside of normal human hearing. A gas turbine engine is also disclosed.
摘要翻译： 防喘振机构具有用于抽出压缩空气并将空气输送到排气流中的管道。 选择性打开的阀允许抽头的空气通过多个孔流入排气流。 这些孔的大小适合于将由敲击的空气产生的声音的频率调谐到正常人类听觉之外的频率范围。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US20150353203A1
公开(公告)日：2015-12-10
申请号：US14729689
申请日：2015-06-03
发明人： Farooq Rehman , James C. Napier
IPC分类号： B64D41/00
CPC分类号： B64D41/00 , B64D33/02 , B64D2033/0213
摘要： An inlet door for an auxiliary power unit includes a door body with opposed interior and exterior surfaces. The interior surface of the inlet door is curved to diffuse sound waves received by the interior surface.
摘要翻译： 用于辅助动力单元的入口门包括具有相对的内表面和外表面的门体。 入口门的内表面弯曲，以扩散由内表面接收的声波。
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公开(公告)号：US09540114B2
公开(公告)日：2017-01-10
申请号：US14771431
申请日：2014-03-03
CPC分类号： B64D33/06 , B64D41/00 , B64D2041/002 , F01D25/30 , F02C7/24 , F02C7/32 , F05D2220/50 , F05D2260/96 , Y02T50/44
摘要： An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.
摘要翻译： 一种用于燃气涡轮发动机飞行器中的APU的排气系统，其具有减少排气噪声的尾锥。 APU排气衬套连接到APU并延伸到尾锥处的椭圆形切口。衬套具有从APU到靠近尾锥的点的第一恒定横截面，以及从接近尾部的点增加的第二截面 尾锥到衬里切口。 衬里转向尾部侧面。 衬套切口进一步放大至少一个更大的切口。
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