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公开(公告)号：US10473030B2
公开(公告)日：2019-11-12
申请号：US15452341
申请日：2017-03-07
Applicant: Rolls-Royce Corporation
Inventor： Robert W. Heeter , Jonathan Rivers , Dennes Kyle Burney
Abstract: An aircraft engine includes a rotating structure and a casing circumferentially surrounding the rotating structure. The aircraft engine further includes an acoustic panel for noise reduction circumferentially surrounding the rotating structure. The acoustic panel is disposed proximal the casing. Furthermore, the acoustic panel includes a plurality of acoustic panel members. In addition, the acoustic panel is secured to the casing by at least one securement mechanism such that the acoustic panel is substantially circumferentially fixed relative to the casing.
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公开(公告)号：US20170335862A1
公开(公告)日：2017-11-23
申请号：US15159467
申请日：2016-05-19
Applicant: Rolls-Royce Corporation
Inventor： Robert Warren Heeter , Timothy John Unton , Eric Engebretsen , Jonathan Rivers
CPC classification number: F04D29/526 , F01D21/045 , F01D25/246 , F04D29/325 , F05D2220/36
Abstract: The present disclosure provides a liner system for a turbine engine. The liner system includes a fan track liner panel that is positionable axially within a casing that is arranged around a rotatable fan and that forms a blade containment zone. The fan track liner panel is further positionable radially outward of the rotatable fan. The fan track liner panel includes a body that extends a length of the fan track liner panel from a fore portion of the fan track liner panel to an aft portion of the fan track liner panel. The fan track liner panel is configured to be directly secured to the casing by a fastener that extends through only part of the body and entirely through the casing within the blade containment zone such that the aft portion of the fan track liner panel abuts an interior surface of the casing.
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公开(公告)号：US10344675B2
公开(公告)日：2019-07-09
申请号：US15165731
申请日：2016-05-26
Applicant: Rolls-Royce Corporation
Inventor： Matthew Joseph Jordan , Dennes Kyle Burney , Robert Warren Heeter , Jonathan Rivers
Abstract: According to one aspect, an apparatus includes a first member that has a first aperture and a second member adjacent to the first member and having a second aperture extending between opposed first and second faces of the second member and aligned with the first aperture to define a combined aperture that has a longitudinal extent. The second aperture is defined by a surface that has a portion having an extent transverse to the longitudinal extent. The apparatus further includes at least a portion of a fastener disposed in the combined aperture. The fastener has a first end proximal the first member and a second end proximal the second member and includes a first retaining member in contact with the first member, a second retaining member in interfering relationship with the portion, and a third retaining member in contact with the second face.
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Patent Agency Ranking
公开(公告)号：US11162425B2
公开(公告)日：2021-11-02
申请号：US16437966
申请日：2019-06-11
Applicant: Rolls-Royce Corporation
Inventor： Mark Fleckenstein , Jonathan Rivers , Robert Heeter
Abstract: An assembly fixture for a fan casing of a gas turbine engine wherein the fan casing includes a casing having a flange with a plurality of apertures extending therethrough, comprises a locating structure having a positioning feature that is engageable by a fastener extending through a particular aperture of the plurality of apertures to secure the locating structure to the fan casing. The locating structure further includes a locating feature indicating a particular location of the fan casing when the locating structure is mounted to the fan casing.
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公开(公告)号：US10260522B2
公开(公告)日：2019-04-16
申请号：US15159467
申请日：2016-05-19
Applicant: Rolls-Royce Corporation
Inventor： Robert Warren Heeter , Timothy John Unton , Eric Engebretsen , Jonathan Rivers
Abstract: The present disclosure provides a liner system for a turbine engine. The liner system includes a fan track liner panel that is positionable axially within a casing that is arranged around a rotatable fan and that forms a blade containment zone. The fan track liner panel is further positionable radially outward of the rotatable fan. The fan track liner panel includes a body that extends a length of the fan track liner panel from a fore portion of the fan track liner panel to an aft portion of the fan track liner panel. The fan track liner panel is configured to be directly secured to the casing by a fastener that extends through only part of the body and entirely through the casing within the blade containment zone such that the aft portion of the fan track liner panel abuts an interior surface of the casing.
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公开(公告)号：US20180258954A1
公开(公告)日：2018-09-13
申请号：US15452311
申请日：2017-03-07
Applicant: Rolls-Royce Corporation
Inventor： Robert W. Heeter , Jonathan Rivers , Dennes Kyle Burney
CPC classification number: F04D29/663 , F02C7/045 , F02C7/20 , F02K3/06 , F04D29/526 , F04D29/644 , F05D2220/323 , F05D2220/36 , F05D2230/60 , F05D2230/70
Abstract: An aircraft engine includes a rotating structure and a casing circumferentially surrounding the rotating structure. The aircraft engine further includes an acoustic panel for noise reduction circumferentially surrounding the rotating structure and disposed adjacent the casing. The acoustic panel comprises a plurality of acoustic panel members arranged adjacent to one another to form a substantially complete ring of the acoustic panel. A first acoustic panel member of the plurality of acoustic members is adjacent to a second acoustic panel member of the plurality of acoustic members. The first acoustic panel member is removably secured to the second acoustic panel member by a releasable fastening assembly.
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公开(公告)号：US20180258852A1
公开(公告)日：2018-09-13
申请号：US15452341
申请日：2017-03-07
Applicant: Rolls-Royce Corporation
Inventor： Robert W. Heeter , Jonathan Rivers , Dennes Kyle Burney
IPC: F02C7/045
CPC classification number: F02C7/045 , B64D33/02 , B64D2033/0206 , F02K1/827 , F04D29/664 , F05D2260/30 , F05D2260/31 , F05D2260/96 , Y02T50/672
Abstract: An aircraft engine includes a rotating structure and a casing circumferentially surrounding the rotating structure. The aircraft engine further includes an acoustic panel for noise reduction circumferentially surrounding the rotating structure. The acoustic panel is disposed proximal the casing. Furthermore, the acoustic panel includes a plurality of acoustic panel members. In addition, the acoustic panel is secured to the casing by at least one securement mechanism such that the acoustic panel is substantially circumferentially fixed relative to the casing.
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公开(公告)号：US20170342906A1
公开(公告)日：2017-11-30
申请号：US15165731
申请日：2016-05-26
Applicant: Rolls-Royce Corporation
Inventor： Matthew Joseph Jordan , Dennes Kyle Burney , Robert Warren Heeter , Jonathan Rivers
CPC classification number: F02C7/20 , F01D11/122 , F01D25/24 , F01D25/243 , F01D25/246 , F02C3/04 , F05D2220/36 , F05D2260/31 , F05D2260/311 , F16B35/041 , Y02T50/672
Abstract: According to one aspect, an apparatus includes a first member that has a first aperture and a second member adjacent to the first member and having a second aperture extending between opposed first and second faces of the second member and aligned with the first aperture to define a combined aperture that has a longitudinal extent. The second aperture is defined by a surface that has a portion having an extent transverse to the longitudinal extent. The apparatus further includes at least a portion of a fastener disposed in the combined aperture. The fastener has a first end proximal the first member and a second end proximal the second member and includes a first retaining member in contact with the first member, a second retaining member in interfering relationship with the portion, and a third retaining member in contact with the second face.
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