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公开(公告)号:US12038011B2
公开(公告)日:2024-07-16
申请号:US17851918
申请日:2022-06-28
Applicant: Raytheon Technologies Corporation
Inventor: Allison Clark Nicklous , Steven Tyler Englerth
IPC: F04D27/00 , F01D17/02 , F01D25/04 , F01D25/16 , F02C7/045 , F02C9/24 , F02K3/06 , F04D29/32 , F04D29/38 , F04D29/52 , G01H1/00 , G01L19/06 , G01M15/12
CPC classification number: F04D27/001 , F01D17/02 , F01D25/04 , F01D25/164 , F02C7/045 , F02C9/24 , F02K3/06 , F04D29/329 , F04D29/38 , F04D29/522 , G01H1/006 , G01L19/0609 , G01M15/12 , F05D2260/12 , F05D2260/16 , F05D2260/80 , F05D2260/83 , F05D2260/96 , F05D2270/334 , F05D2270/804
Abstract: An aero damping measurement system is provided. The system includes a shroud defining a tunnel, a hub disposed within the tunnel, and a plurality of blades coupled to the hub. The blades may rotate about the hub. A gas pressure probe may have a tip extending to the tunnel to deliver a pressurized burst into the tunnel. An aeromechanical identification system may include a pressurized gas source, a valve in fluid communication with the pressurized gas source, and the gas pressure probe may be in fluid communication with the valve. The valve may control a flow of a pressurized gas from the pressurized gas source into the gas pressure probe. A pressure sensor may be coupled to the gas pressure probe and configured to measure a pressure within the gas pressure probe.
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2.
公开(公告)号:US20240200493A1
公开(公告)日:2024-06-20
申请号:US18565281
申请日:2022-06-30
Applicant: SAFRAN POWER UNITS
Inventor: Laurent Stéphane Tardy , Jaime Georges Paul Culla
CPC classification number: F02C7/045 , B64D33/02 , B64D41/00 , F02C3/08 , B64D2033/0206 , B64D2033/0213 , F05D2220/50 , F05D2260/96
Abstract: The invention relates to an acoustic insulation assembly for an auxiliary power unit having a centrifugal compressor (1), comprising a ring-shaped casing (8) for an air inlet (3) and comprising a plurality of reinforcing arms (9) connecting its inner walls, a plurality of removable mechanical acoustic insulation parts (10), each mechanical part (10) being ring-shaped and comprising attachment means (11) intended to engage with the casing (8), such that the mechanical part (10) and the flow surface of the casing (8), defined by a pair of reinforcing arms (9), overlie one another.
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公开(公告)号:US20240191656A1
公开(公告)日:2024-06-13
申请号:US18554958
申请日:2022-04-11
Applicant: SAFRAN NACELLES
Inventor: Marc VERSAEVEL , Bertrand Léon Marie DESJOYEAUX , Pierre-Yves GINI
IPC: F02C7/045
CPC classification number: F02C7/045
Abstract: An acoustic panel for a turbine engine includes a first strip and a second strip each comprising an alternation of first ridges and second ridges connected by sidewalls. The first and second strips are joined to each other to form a plurality of cells, each delimited by a first ridge of the first strip and a first ridge of the second strip. A third strip is interposed between the first strip and the second strip and includes a first lateral wall bearing on the first strip The third strip further includes at least one tab that extends inside one of the cells and delimits all or part of a passage inside the associated cell.
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公开(公告)号:US11946414B2
公开(公告)日:2024-04-02
申请号:US17553700
申请日:2021-12-16
Inventor: Robert W. Heeter , Christopher D. Hall , Daniel E. Molnar, Jr.
IPC: F02C7/045 , F02K1/82 , G10K11/168 , G10K11/172
CPC classification number: F02C7/045 , F02K1/827 , G10K11/168 , G10K11/172 , F05D2220/323 , F05D2260/963 , F05D2300/121 , F05D2300/603 , F05D2300/612
Abstract: An acoustic panel for a gas turbine engine, includes a panel body, a panel-body cover, and a support bracket. The panel body is configured to dampen vibrations caused by the gas turbine engine. The forward support bracket is configured to mount the acoustic panel to portions of the gas turbine engine.
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公开(公告)号:US11932399B2
公开(公告)日:2024-03-19
申请号:US17412676
申请日:2021-08-26
Applicant: Safran Nacelles , SAFRAN CERAMICS
CPC classification number: B64C7/02 , B64D29/06 , B64D33/02 , F02C7/045 , F02K1/827 , B64D2033/0206 , F05D2260/96 , F05D2300/6033
Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.
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公开(公告)号:US20230407775A1
公开(公告)日:2023-12-21
申请号:US18458588
申请日:2023-08-30
Applicant: THE BOEING COMPANY
Inventor: Michael Hayes , Keith A. Etling , Jordan Kreitzman , Rehan Kaluarachchi , Manny Urcia , Andrews Guadron
IPC: F01N1/02 , B64D27/00 , G10K11/16 , G10K11/172 , F02C7/045
CPC classification number: F01N1/023 , B64D27/00 , G10K11/161 , G10K11/172 , F02C7/045 , F02C6/20
Abstract: A flow path duct system for a propulsion system of an aircraft includes a base defining a flow surface. The base has an internal surface and an external surface. A plurality of perforations are formed through the base between the internal surface and the external surface. A plurality of supports define a plurality of cavities. The plurality of supports extend outwardly from the external surface of the of the base. One or more of the plurality of cavities are in fluid communication with the one or more of the plurality of perforations. A backing surface is secured to the plurality of supports. The plurality of supports are disposed between the base and the backing surface. The one or more of the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations. The base, the plurality of supports, and the backing surface can be integrally formed together as a monolithic, load-bearing structure.
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公开(公告)号:US20190084261A1
公开(公告)日:2019-03-21
申请号:US15708573
申请日:2017-09-19
Applicant: The Boeing Company
Inventor: Eric Herrera , John Scott Bauman , Peter James Oberst
IPC: B29D99/00 , B29D24/00 , B29C65/04 , B29C65/08 , B29C65/10 , B32B3/12 , G10K11/16 , F02C7/045 , F02K1/82 , E04B1/82
CPC classification number: B29D99/001 , B29C65/04 , B29C65/08 , B29C65/10 , B29C66/431 , B29C66/4326 , B29C66/49 , B29C66/729 , B29C66/8322 , B29D24/005 , B29D99/0089 , B29L2031/38 , B29L2031/608 , B29L2031/7724 , B32B3/12 , B32B2307/10 , B64D29/00 , B64D33/02 , B64D2033/0206 , B64F5/10 , E04B1/82 , E04B2001/748 , E04B2001/8245 , F02C7/045 , F02K1/827 , F05D2230/23 , F05D2250/283 , F05D2260/96 , G10K11/16 , G10K11/172 , G10K2210/1281
Abstract: A method and system for manufacturing a conical shaped acoustic structure. A sheet of acoustical material is cut to form individual pieces using a cutter system. Each individual piece in the individual pieces has a flat pattern for the conical shaped acoustic structure. An individual piece is positioned around a mandrel with a conical shape using an actuator system. Two edges of the individual piece are positioned for joining. The two edges of the individual piece positioned around the mandrel are joined to form the conical shaped acoustic structure.
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8.
公开(公告)号:US20190024534A1
公开(公告)日:2019-01-24
申请号:US15653721
申请日:2017-07-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor: Bhushan Singh Gautam , Gladys Gaude
CPC classification number: F01D25/04 , F01D5/26 , F02B29/04 , F02B37/00 , F02C7/045 , F02C7/24 , F02M35/1211 , F02M35/1244 , F02M35/1266 , F02M35/1272 , F23R3/34 , F23R3/42
Abstract: An acoustic damper includes a housing with an inlet aperture and an outlet aperture. The housing is configured to receive a gas flow that enters via the inlet aperture and that exits via the outlet aperture. The acoustic damper also includes a barrier member that is disposed within the housing. The barrier member is configured to be disposed within the gas flow and to dampen acoustic energy that propagates in an upstream direction generally from the outlet aperture toward the inlet aperture. The barrier member includes an outer structure that defines an interior volume of the barrier member. The interior volume is oriented toward the outlet aperture.
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公开(公告)号:US20180363558A1
公开(公告)日:2018-12-20
申请号:US15626913
申请日:2017-06-19
Applicant: Rohr, Inc.
Inventor: Luby Weaver , Charles M. Biset , Jeffrey Woods , David M. Adams
IPC: F02C7/24 , F02C7/045 , F02K1/82 , G10K11/172 , E04B1/84
CPC classification number: F02C7/24 , B64D2033/0206 , E04B1/8409 , E04B1/86 , E04B2001/8471 , F02C7/045 , F02K1/827 , F05D2260/96 , G10K11/168 , G10K11/172
Abstract: A panel is provided for attenuating noise. This panel includes a perforated first skin, a second skin, an array of corrugations, a first channel, a second channel, a plurality of first sidewalls and a plurality of second sidewalls. The array of corrugations includes a first corrugation and a second corrugation. Each of the corrugations includes a baffle and a septum. The first channel is formed by the baffle of the first corrugation, the septum of the first corrugation and the first skin. The second channel is formed by the baffle of the second corrugation, the septum of the first corrugation and the second skin. The first sidewalls divide the first channel into a plurality of first chambers. The second sidewalls divide the second channel into a plurality of second chambers. A first of the second chambers is fluidly coupled with a subset of the first chambers through perforations in the septum of the first corrugation.
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公开(公告)号:US20180347465A1
公开(公告)日:2018-12-06
申请号:US15608547
申请日:2017-05-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Paul W. Baumann , Brian Barainca , Rolf Thorsen , Mark E. Simonds , Gary F. Fowler , Hector M. Pinero
CPC classification number: F02C7/055 , F01D5/24 , F01D11/122 , F01D21/045 , F02C7/045 , F02C7/05
Abstract: An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion- of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.
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