公开(公告)号：US20150218964A1

公开(公告)日：2015-08-06

申请号：US14596664

申请日：2015-01-14

Applicant: Rolls-Royce PLC

Inventor： Dale Edward EVANS

IPC: F01D25/14 ,  F01D25/00

CPC classification number: F01D25/145 ,  F01D25/005 ,  F01D25/243 ,  F04D29/023 ,  F04D29/545 ,  F05D2300/174 ,  F05D2300/21 ,  F05D2300/43 ,  F05D2300/502 ,  F05D2300/603 ,  F05D2300/702

Abstract: The present invention relates to a fire resistant fan casing for a gas turbine engine. The casing has a projection such as a reinforcing rib or a mounting pad. The projection comprises at least one shell portion formed of a fibre/plastic composite material encasing a core of fire resistant material such as a metallic material or a ceramic matrix composite material.

Abstract translation: 本发明涉及燃气轮机的防火风扇壳体。 壳体具有诸如加强肋或安装垫的突起。 突出部包括至少一个壳体部分，其由包含诸如金属材料或陶瓷基体复合材料的耐火材料芯体的纤维/塑料复合材料形成。

公开(公告)号：US20150218961A1

公开(公告)日：2015-08-06

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

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

Abstract: Fan containment system fitting around 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 array of fan blades and a hook projecting in radially inward direction from the annular casing element and positioned axially forward of an 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.

Abstract translation: 围绕安装在轴向燃气涡轮发动机的轮毂上的径向延伸的风扇叶片阵列的风扇容纳系统。 风扇容纳系统包括风扇壳体，其具有用于环绕风扇叶片的环形壳体元件和从环形壳体元件沿径向向内的方向突出并且当风扇容纳系统安装在风扇附近时位于风扇叶片阵列的轴向前方的环形壳体元件 刀片。 环形风扇轨道衬套，其定位成基本上与环形壳体元件同轴。 夹紧装置将风扇履带板与挂钩相连。 夹紧装置在风扇叶片撞击风扇履带衬板的情况下被配置，夹紧装置释放钩和一部分风扇履带衬板之间的连接，使得风扇履带衬板的一部分能够朝向环形壳体元件移动以鼓励 风扇叶片冲击钩子。

公开(公告)号：US20140227076A1

公开(公告)日：2014-08-14

申请号：US14154671

申请日：2014-01-14

Applicant: ROLLS-ROYCE PLC

Inventor： Matthew Ashley Charles HOYLAND ,  Dale Edward EVANS

IPC: F01D21/04

CPC classification number: F01D21/045 ,  F02C7/04 ,  F05D2220/36 ,  F05D2250/25 ,  Y02T50/672

Abstract: A fan containment system having a generally cylindrical fan case including a hook projecting in a generally radially inward direction and positioned axially forward of a radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a panel which is positioned axially rearward of the hook and positioned axially forward of the radial array of fan blades and forms a substantially continuous air washed surface with the fan track liner. The panel is temporarily deformable so as to absorb the impacts of any foreign bodies, which enter the gas turbine engine, without compromising the structural integrity of the panel while being weak enough so that in the event that one of the fan blades is released from the hub, the fan blade tip of the detached fan blade is not inhibited from moving radially outward of the hub.

Abstract translation: 一种风扇容纳系统，其具有大致圆柱形的风扇壳体，该风扇壳体包括沿大体上径向向内的方向突出并沿径向阵列的风扇叶片轴向定位的钩子; 设置在风扇壳体的径向内表面上的风扇轨道衬套; 以及面板，其位于所述钩的轴向后方并且位于所述风扇叶片的所述径向阵列的轴向前方并且与所述风扇履带衬板形成基本连续的空气清洁表面。 面板可暂时变形，以便吸收进入燃气涡轮发动机的任何异物的冲击，而不会在足够弱的情况下损害面板的结构完整性，从而在风扇叶片中的一个从 拆卸的风扇叶片的风扇叶片尖端不被阻止从轮毂径向向外移动。

公开(公告)号：US20130336761A1

公开(公告)日：2013-12-19

申请号：US13660186

申请日：2012-10-25

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward EVANS

IPC: F01D21/04

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.

Abstract translation: 涡轮机壳体组件包括位于径向向外位于涡轮机的一个或多个旋转机翼元件的第一壳体元件，位于第一壳体元件的径向远侧的第二壳体元件和位于第一和第二壳体元件之间的一个或多个弓形挡板元件 。 在分离的风扇叶片的冲击之后，第一壳体元件的径向向外的运动导致或每个挡板元件突出到通过涡轮机的空气流中。