-
公开(公告)号：US11555449B2
公开(公告)日：2023-01-17
申请号：US17088199
申请日：2020-11-03
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.
-
公开(公告)号：US20200309028A1
公开(公告)日：2020-10-01
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.
-
13.发明授权公开(公告)号：US10399664B2
公开(公告)日：2019-09-03
申请号：US15145894
申请日：2016-05-04
发明人： William Joseph Bowden , Andrew Breeze-Stringfellow , Richard David Cedar , Syed Arif Khalid , Patrick John Lonneman , Aleksander Piotr Pasieczny , Daniel Lawrence Tweedt
IPC分类号： B64C11/14 , B64D33/02 , F02C6/20 , F02C7/05 , F01D5/02 , F01D9/04 , F01D25/04 , F01D25/24 , F04D29/32 , F04D29/38 , B64D27/00
摘要： An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.
-
公开(公告)号：US20190241248A1
公开(公告)日：2019-08-08
申请号：US15890785
申请日：2018-02-07
发明人： Jixian Yao , Nikolai N. Pastouchenko , Patrick John Lonneman , Patrick Michael Marrinan , Richard David Cedar
摘要： An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.
-
公开(公告)号：US10167088B2
公开(公告)日：2019-01-01
申请号：US14886262
申请日：2015-10-19
摘要： Aircraft gas turbine engine spinner includes conical forward spinner section extending aftwardly from spinner tip to a curved aft spinner section circumscribed about centerline axis, a spinner aspect ratio greater than about 1.8, and wherein spinner aspect ratio is an axial distance between spinner tip and spinner end divided by radial distance from axis to spinner end. Aspect ratio may be in a range of about 2.0-2.2 or about 2.2-2.8. Aft spinner section may be substantially tangential to platform leading edges of platforms of fan blades. Aft spinner section may have cambered or an elliptical axially curved cross-section.Spinner axial cross-section may have longer spinner axial distance compared to baseline axial distance of baseline cross-section and spinner aspect ratio greater than baseline aspect ratio of baseline cross-section.
-
公开(公告)号：US11059559B2
公开(公告)日：2021-07-13
申请号：US15911260
申请日：2018-03-05
IPC分类号： B64C1/06 , B64C1/40 , E04B1/86 , F02K1/82 , G10K11/172 , G10K11/168 , F02C7/045 , B29L7/00 , B29L31/30 , E04B1/74 , E04B1/84 , B64D33/02
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.
-
公开(公告)号：US10907495B2
公开(公告)日：2021-02-02
申请号：US16871660
申请日：2020-05-11
IPC分类号： F01D9/02 , F01D17/16 , B64C11/00 , B64C11/18 , F02K1/46 , F02K3/02 , B64C11/46 , F02C6/20 , 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.
-
公开(公告)号：US20180237120A1
公开(公告)日：2018-08-23
申请号：US15439082
申请日：2017-02-22
发明人： Brandon Wayne Miller , Richard Byron Stewart , Jeffrey Donald Clements , Richard David Cedar , David William Crall
CPC分类号： B64C3/32 , B64D27/18 , B64D2027/262 , F01D21/045 , F02K3/06 , F05D2300/603 , F05D2300/6033 , Y02T50/672
摘要： The present disclosure is directed to an aircraft including a fuselage to which a pair or more of wings attaches. The aircraft defines a transverse direction, a longitudinal direction, and a latitudinal direction. The aircraft includes a wing extended from the fuselage along the transverse direction in which the wing defines a leading edge, and a gas turbine engine coupled to the wing. The engine defines an axial centerline therethrough along the longitudinal direction. The engine includes a nacelle including an outer wall extended around the axial centerline. The nacelle defines a radial reference plane extended perpendicular from the axial centerline. The outer wall defines an outer wall point closest to the fuselage. The radial reference plane extends through a reference line defined along the latitudinal direction from the outer wall point to the leading edge of the wing. The engine further includes a low pressure (LP) turbine rotor that includes an upstream-most first turbine rotor concentric to the axial centerline. The first turbine rotor is disposed downstream along the longitudinal direction of the radial reference plane.
-
公开(公告)号：US20210231054A1
公开(公告)日：2021-07-29
申请号：US17088199
申请日：2020-11-03
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.
-
公开(公告)号：US10814955B2
公开(公告)日：2020-10-27
申请号：US15890785
申请日：2018-02-07
发明人： Jixian Yao , Nikolai N. Pastouchenko , Patrick John Lonneman , Patrick Michael Marrinan , Richard David Cedar
摘要： An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.
-
-
-
-
-
-
-
-
-
搜索结果
22 条记录 (耗时 0.018 秒)
