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公开(公告)号：US10563578B2
公开(公告)日：2020-02-18
申请号：US15550800
申请日：2015-02-18
发明人： Andrew Michael Roach , Richard David Cedar , Steven Thomas Davies , Timothy Richard Depuy , Graham Frank Howarth , Michael Moses Martinez
IPC分类号： F02C7/045 , F02K1/82 , G10K11/168 , G10K11/172 , B05D5/08 , B64D33/02 , B32B3/12 , B32B3/24 , B32B3/26 , F02C7/24 , F02K1/44 , G10K11/16
摘要： An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perforated sheet supported by the support layer such that perforations are in overlying relationship with the open faces to form paired perforations and cavities that define acoustic resonator cells, and a coating applied to the perforated sheet.
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公开(公告)号：US11434819B2
公开(公告)日：2022-09-06
申请号：US16370124
申请日：2019-03-29
发明人： Shanmugam Murugappan , Michael Moses Martinez , Egbert Geertsema , Rudramuni Kariveerappa Majjigi , Richard David Cedar , Wendy Wenling Lin , Robert William Davidoff , David Patrick Calder , Graham Frank Howarth
摘要： An acoustic liner may include an acoustic core having an array of resonant cells, and an acoustic screen disposed across the array of resonant cells. The resonant cells include a plurality of cell walls and a resonant space defined by the plurality of cell walls. The acoustic core may include a folded acoustic core. Additionally, or in the alternative, at least some of the resonant cells may include an oblique polyhedral cellular structure and/or a multitude of sound-attenuating protuberances. The acoustic screen may include a reticulate membrane and a support lattice.
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公开(公告)号：US20220106907A1
公开(公告)日：2022-04-07
申请号：US17644510
申请日：2021-12-15
摘要： An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.
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公开(公告)号：US10669881B2
公开(公告)日：2020-06-02
申请号：US14771975
申请日：2013-10-23
IPC分类号： F01D17/16 , B64C11/46 , F02K3/02 , F02C6/20 , B64C11/00 , F01D9/02 , F02K1/46 , B64C11/18 , B64C11/48
摘要： A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.
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公开(公告)号：US20180128206A1
公开(公告)日：2018-05-10
申请号：US15347301
申请日：2016-11-09
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , F02K3/06 , F05D2220/327 , F05D2260/904 , Y02T50/671
摘要： A turbofan engine is provided having a fan and a nacelle assembly enclosing the fan. The nacelle assembly includes a thrust reverser system having one or more cascade segments configured to translate at least partially along an axial direction of the turbofan engine. The turbofan engine further includes a core operable with the fan and at least partially enclosed by the nacelle. The core includes a turbine section having a low pressure turbine defining an exit diameter. A ratio of the exit diameter of the low pressure turbine to a fan diameter of the fan is less than 0.5, providing for a more compact turbofan engine.
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公开(公告)号：US20180100434A1
公开(公告)日：2018-04-12
申请号：US15291110
申请日：2016-10-12
CPC分类号： F02C7/057 , B64D33/02 , B64D2033/0226 , F02C3/04 , F02C7/042 , F02K3/06 , F05D2220/323 , F05D2240/127 , F05D2260/57 , Y02T50/671
摘要： The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.
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公开(公告)号：US20200271010A1
公开(公告)日：2020-08-27
申请号：US16871660
申请日：2020-05-11
IPC分类号： F01D17/16 , B64C11/46 , F02K3/02 , F02C6/20 , F02K1/46 , B64C11/00 , B64C11/18 , B64C11/48 , F01D9/02
摘要： A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.
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公开(公告)号：US20190270504A1
公开(公告)日：2019-09-05
申请号：US15911260
申请日：2018-03-05
IPC分类号： B64C1/06 , B64C1/40 , G10K11/172 , F02K1/82 , E04B1/86
摘要： The present disclosure provides acoustic structures and related systems and methods which may be used to dampen or attenuate sound waves, including, for example, noise generated by or emanating from various aspects or components of turbomachines such as turbine engines. These acoustic structures include oblique polyhedral cellular structures, including converging polyhedral cells and diverging polyhedral cells, and related systems and methods of making and using such acoustic structures.
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公开(公告)号：US20180016987A1
公开(公告)日：2018-01-18
申请号：US15553207
申请日：2015-03-10
发明人： Graham Frank Howarth , Andrew Michael Roach , Steven Thomas Davies , Richard David Cedar , Michael Moses Martinez , Timothy Richard DePuy
IPC分类号： F02C7/24
CPC分类号： F02C7/24 , F02C7/045 , F02K1/827 , F05D2220/323 , F05D2250/11 , F05D2250/14 , F05D2250/283 , F05D2260/963 , G10K11/172 , Y02T50/672
摘要： An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a facing sheet operably coupled to the support layer such that the facing sheet overlies and closes the open faces, a set of perforations located in the facing sheet and in fluid communication with a corresponding one of the cavities to form a set of acoustic resonators, and at least a subset of the perforations have an axially-oriented, relative to the axial flow path, inlet.
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公开(公告)号：US09810178B2
公开(公告)日：2017-11-07
申请号：US14818596
申请日：2015-08-05
CPC分类号： F02K1/78 , F01D25/24 , F01D25/30 , F02K1/00 , F02K1/06 , F02K1/08 , F02K1/09 , F02K3/06 , F05D2250/14
摘要： A turbofan exhaust nozzle includes: a conical inner shell disposed coaxially inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell and the inner shell terminates in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct, wherein at least a portion of the trailing edge of the outer shell is vertically non-coplanar.
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