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公开(公告)号：US20210310411A1
公开(公告)日：2021-10-07
申请号：US17224514
申请日：2021-04-07
申请人： Rohr, Inc.
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes an exhaust center body and a duct system. The exhaust center body includes an exterior skin. The duct system is fluidly coupled with a plurality of exterior skin perforations in the exterior skin. The duct system is configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the exterior skin perforations.
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公开(公告)号：US20210348581A1
公开(公告)日：2021-11-11
申请号：US17307570
申请日：2021-05-04
申请人： Rohr, Inc.
发明人： Adam Saunders , Bryce T. Kelford , Travis M. Frazier , Richard Haslim , Richard S. Alloway , Vijay V. Pujar
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a nozzle extending axially along and circumferentially about an axial centerline. The nozzle includes a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle. The nozzle is configured with an internal flow passage radially between the nozzle panel and the nozzle fairing. The internal flow passage extends axially within the nozzle to an outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle.
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公开(公告)号：US11560847B2
公开(公告)日：2023-01-24
申请号：US17224514
申请日：2021-04-07
申请人： Rohr, Inc.
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes an exhaust center body and a duct system. The exhaust center body includes an exterior skin. The duct system is fluidly coupled with a plurality of exterior skin perforations in the exterior skin. The duct system is configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the exterior skin perforations.
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公开(公告)号：US11746726B2
公开(公告)日：2023-09-05
申请号：US17307570
申请日：2021-05-04
申请人： Rohr, Inc.
发明人： Adam Saunders , Bryce T. Kelford , Travis M. Frazier , Richard Haslim , Richard S. Alloway , Vijay V. Pujar
IPC分类号： F02K1/52 , B64D29/06 , F02K1/80 , F02K1/04 , F02K1/82 , F02K1/38 , B64D27/26 , B64D27/18 , F02K3/06
CPC分类号： F02K1/52 , B64D27/18 , B64D29/06 , F02K1/805 , F02K3/06 , B64D27/26 , F05D2220/323 , F05D2240/128
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a nozzle extending axially along and circumferentially about an axial centerline. The nozzle includes a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle. The nozzle is configured with an internal flow passage radially between the nozzle panel and the nozzle fairing. The internal flow passage extends axially within the nozzle to an outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle.
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