公开(公告)号：US09797269B2

公开(公告)日：2017-10-24

申请号：US14593418

申请日：2015-01-09

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward Evans ,  Mickael Drozdz ,  David Laker Christmas

IPC: F01D21/04 ,  F01D25/24

CPC classification number: F01D21/045 ,  F01D25/243 ,  F05D2220/36 ,  F05D2240/14 ,  Y02T50/672

Abstract: Fan containment system fitting around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system includes a fan case having an annular casing element for encircling the array of fan blades and a hook projecting in a radially inward direction from the annular casing element and positioned axially forward of the array of fan blades when the fan containment system fitted around fan blades. An annular fan track liner positioned substantially coaxial to the annular casing element. Clamping arrangement connects fan track liner to the hook. Clamping arrangement is configured under the condition that a fan blade impacts the fan track liner, the clamping arrangement releases connection between the hook and a portion of fan track liner so that a portion of the fan track liner can move towards the annular casing element to encourage the fan blade to impact the hook.

公开(公告)号：US09732626B2

公开(公告)日：2017-08-15

申请号：US13660186

申请日：2012-10-25

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward Evans

IPC: F01D21/04 ,  F01D25/24

CPC classification number: F01D21/045 ,  F01D25/24 ,  Y02T50/672

Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element and one or more arcuate fence elements positioned between the first and second casing elements. Following impact of a detached fan blade, a radially outward movement of the first casing element causes the or each fence element to project into the air flow passing through the turbomachine.

公开(公告)号：US09228444B2

公开(公告)日：2016-01-05

申请号：US13666613

申请日：2012-11-01

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward Evans ,  Ian Colin Deuchar Care

IPC: F01D5/22 ,  F01D5/30 ,  F02K3/06 ,  F01D11/00

CPC classification number: F01D5/225 ,  F01D5/22 ,  F01D5/30 ,  F01D5/3007 ,  F01D11/008 ,  F02K3/06

Abstract: A rotor assembly for a gas turbine engine, the rotor assembly has a disc supporting a plurality of radially extending blades. The blades define passages therebetween and each passage has an annulus filler assembly. The annulus filler assembly includes at least two bodies and a brace, each of the bodies being arranged to abut respective adjacent blades and the brace is arranged to occupy a position centrally of the two bodies. The brace is mounted to the disc and each body and the brace are arranged to engage one another to form an airwash surface. The airwash surface improves aerodynamic flow of air entering the gas turbine engine.

Abstract translation: 一种用于燃气涡轮发动机的转子组件，转子组件具有支撑多个径向延伸叶片的盘。 叶片在其间限定通道，并且每个通道具有环形填料组件。 环形填料组件包括至少两个主体和支架，每个主体被布置成邻接相应的相邻的叶片，并且所述支架被布置成占据两个主体中心的位置。 支架安装到盘上，并且每个主体和支架被布置成彼此接合以形成空气清洗表面。 喷气表面改善了进入燃气涡轮发动机的空气的空气动力学流量。

公开(公告)号：US20140064949A1

公开(公告)日：2014-03-06

申请号：US13741842

申请日：2013-01-15

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward Evans ,  Ian Colin Deuchar Care

IPC: F01D25/24

CPC classification number: F01D25/24 ,  F01D21/045 ,  F01D25/243 ,  F02K3/06 ,  F05D2250/283 ,  Y02T50/672

Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine and a second casing element located radially distal to the first casing element. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. Release of one of the rotating aerofoil elements results in the element, or part thereof, impacting the first casing element which results in the cantilever bending into the void provided between the first and second casing elements.

Abstract translation: 涡轮机壳体组件包括位于涡轮机的一个或多个旋转机翼元件的径向外侧的第一壳体元件和位于第一壳体元件径向远侧的第二壳体元件。 在第一壳体元件的第一端处，在第一壳体元件的径向近端面和第二壳体元件的径向近端面之间设置有空隙。 第一壳体元件的第一端通过能量吸收元件与第一壳体元件抵靠第二壳体元件的对应的第一端; 包括悬臂。 旋转机翼元件之一的释放导致元件或其一部分冲击第一壳体元件，导致悬臂弯曲到设置在第一和第二壳体元件之间的空隙中。