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Patent Agency Ranking
公开(公告)号：US20190048887A1
公开(公告)日：2019-02-14
申请号：US16039590
申请日：2018-07-19
Applicant: ROLLS-ROYCE plc
Inventor： Christopher BENSON , Dale E. EVANS
Abstract: A fan disc apparatus for a gas turbine engine comprises a fan disc; a first drive arm for connecting the fan disc to a fan drive shaft of the gas turbine engine; and a second drive arm for connecting the fan disc to the fan drive shaft.
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公开(公告)号：US20180320534A1
公开(公告)日：2018-11-08
申请号：US15969167
申请日：2018-05-02
Applicant: ROLLS-ROYCE plc
Inventor： Dale E. EVANS , Steven A. Radomski , Clive Grafton-Reed
Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.
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公开(公告)号：US20160356286A1
公开(公告)日：2016-12-08
申请号：US15153339
申请日：2016-05-12
Applicant: ROLLS-ROYCE plc
Inventor： James A. FINLAYSON , Dale E. EVANS , Ian C.D. CARE
CPC classification number: F01D21/045 , F05D2250/184 , F05D2250/61 , F05D2300/603
Abstract: The present invention provides a gas turbine engine comprising a tubular containment casing surrounding a rotary fan blade assembly. The radially outer perimeter (and optionally the radially inner perimeter) of the radial cross-sectional profile of the containment casing is non-circular e.g. polygonal, corrugated, fluted or wavy.
Abstract translation: 本发明提供一种燃气涡轮发动机，其包括围绕旋转风扇叶片组件的管状容纳壳体。 容纳壳体的径向横截面轮廓的径向外周边（以及任选的径向内周边）是非圆形的。 多边形，波纹状，槽纹或波浪形。
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公开(公告)号：US20180318966A1
公开(公告)日：2018-11-08
申请号：US15969178
申请日：2018-05-02
Applicant: ROLLS-ROYCE plc
Inventor： Dale E. EVANS , Steven A. RADOMSKI , Clive GRAFTON-REED
Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub with a through hole extending therethrough. The method comprises welding the aerofoil to the stub such that the open end of the hollow cavity of the aerofoil is aligned with the through hole of the stub so as to define a hollow region extending through the support member and stub to the cavity of the aerofoil. During welding a tool is positioned within the through hole and cavity and is aligned with an interface between the stub and aerofoil, the tool being configured to prevent weld splatter onto a surface of the cavity or through hole.
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公开(公告)号：US20200298987A1
公开(公告)日：2020-09-24
申请号：US16810970
申请日：2020-03-06
Applicant: ROLLS-ROYCE plc
Inventor： Dale E. EVANS
IPC: B64D33/02
Abstract: A containment for a gas turbine engine, the containment comprising: a plurality of acoustic panels angularly arranged around a central longitudinal axis of the containment, each forming part of an annular acoustic liner. Each acoustic panel comprises: a core of cellular material comprising a plurality of elongate cells which are elongate along respective cell directions, wherein each of the elongate cells is circumferentially inclined relative to a local radial direction such that the cell direction has a circumferential component and a radial component relative to the central longitudinal axis; at least one axially-extending panel side wall which is circumferentially inclined relative to a local radial direction such that, in a plane normal to the central longitudinal axis, the panel side wall has a circumferential component and a radial component. Each acoustic panel radially overlaps with another at adjacent panel side walls, with respect to a local radial direction extending through the adjacent panel side walls. Accordingly each acoustic panel is removable from between adjacent overlapping acoustic panels along a removal path which has substantially no axial component.
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