公开(公告)号：US09683490B2

公开(公告)日：2017-06-20

申请号：US14529810

申请日：2014-10-31

Applicant: ROLLS-ROYCE PLC

Inventor： Cedric Brett Harper ,  Ian Colin Deuchar Care ,  Julian Mark Reed

IPC: F02C7/05 ,  F01D11/12 ,  F01D21/04 ,  F02K3/06 ,  F01D21/10 ,  F01D25/24

CPC classification number: F02C7/05 ,  F01D11/122 ,  F01D21/04 ,  F01D21/045 ,  F01D21/10 ,  F01D25/246 ,  F02K3/06 ,  F05D2220/36

Abstract: A fan containment system includes an annular casing element and a hook projecting in a generally radially inward direction from the annular casing element. A fan track liner is connected to the hook via a fastener. The fan track liner has a forward end proximal to the hook and a rearward end distal to the hook. A pivot member protrudes radially inward from the annular casing element and is arranged and positioned between the forward and rearward end of the fan track liner such that a forward portion of the fan track liner is pivotable about the pivot member, so that upon release of a fan blade the forward portion of the fan track liner pivots about the pivot member into a voidal region provided between the annular casing element and the forward portion of the fan track liner to encourage engagement of the hook with a released fan blade.

公开(公告)号：US09816510B2

公开(公告)日：2017-11-14

申请号：US14160985

申请日：2014-01-22

Applicant: ROLLS-ROYCE PLC

Inventor： Cedric Brett Harper

IPC: F04D17/00 ,  F01D11/12 ,  F04D29/52 ,  F01D5/20 ,  F01D5/22 ,  F01D21/04

CPC classification number: F04D17/00 ,  F01D5/20 ,  F01D5/225 ,  F01D11/122 ,  F01D11/127 ,  F01D21/045 ,  F02C7/04 ,  F04D29/526 ,  F05D2220/36 ,  F05D2250/11 ,  F05D2250/182 ,  F05D2250/183 ,  Y02T50/672 ,  Y02T50/673

Abstract: A fan containment system arranged to be fitted around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. Each fan blade has a respective tip. The system includes: a cylindrical fan case including a hook projecting in a radially inward direction and positioned axially forward of the radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a damaging tool which projects radially inwards from the fan case towards the tips. The damaging tool has a tip radially outward of the fan blade tips. The damaging tool is configured that in the event that one of the fan blades is released from the hub, the tip of the damaging tool damages the fan blade tip of the released fan blade to promote penetration of the fan blade into the fan track liner.

公开(公告)号：US09677570B2

公开(公告)日：2017-06-13

申请号：US14523336

申请日：2014-10-24

Applicant: ROLLS-ROYCE PLC

Inventor： Ian Colin Deuchar Care ,  Cedric Brett Harper

IPC: F04D19/00 ,  F04D29/52 ,  F01D21/04 ,  F01D25/24 ,  F02C7/05

CPC classification number: F04D29/526 ,  F01D21/045 ,  F01D25/24 ,  F02C7/05 ,  F04D19/002 ,  F05D2220/36 ,  Y02T50/671

Abstract: A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element. The fan containment system further includes an annular fan track liner comprising a plurality of adjacent arcuate fan track liner panels. Each of the plurality of fan track liner panels is connected to the fan case at the hook via one or more fasteners configured to permit movement of the fan track liner panel relative to the hook such that the fan track liner panel can pivot towards the annular casing element when a released fan blade impacts the fan track liner panel.

公开(公告)号：US09222368B2

公开(公告)日：2015-12-29

申请号：US13741656

申请日：2013-01-15

Applicant: ROLLS-ROYCE PLC

Inventor： Cedric Brett Harper ,  Ian Colin Deuchar Care

IPC: F01D21/04 ,  F01D25/24 ,  F02K3/06

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

Abstract: A turbomaehine casing assembly includes a first casing element, located radially outward of one or more rotating aerofoil elements of a turbomachine, and a second casing element, located radially distal to the first element. A void is provided at a first end of the first element, between radially proximal faces of the first and second elements. The first end of the first element is located against a corresponding first end of the second element by an energy absorbing element. The first element includes a cantilever, arranged in a region extending along the first element from the first end with a pivot axis at its mid-portion. Release of one of the rotating aerofoil elements, resulting in impact with the first element, further results in the cantilever bending into the void between the first and second elements, enabling the rotating aerofoil element to be trapped within the casing assembly.

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元件的径向远侧的第二壳体元件。 在第一元件的第一端处，在第一和第二元件的径向近端面之间设置有空隙。 第一元件的第一端通过能量吸收元件抵靠第二元件的对应的第一端。 第一元件包括悬臂，布置在沿着第一元件从第一端延伸的区域中，其中部具有枢转轴线。 旋转的机翼元件中的一个的释放导致与第一元件的冲击，进一步导致悬臂弯曲到第一和第二元件之间的空隙中，使得旋转的机翼元件被捕获在壳体组件内。