A fan containment system (200) arranged to be fitted around an array of radially extending fan blades (40) which are mounted on a hub in an axial gas turbine engine. The fan containment system comprises: a generally cylindrical fan case (250) including a h...

The method involves applying and manufacturing an abradable coating (20) on a component of a turbomachine by a kinetic cold gas compacting process. The component is a static or rotating component (16) of the turbomachine. An adhesive layer or a thermal ins...

A turbine casing assembly, comprising an annular seal segment assembly for surrounding the turbine adjacent to the turbine blades. An abradable coating (44) is provided on the inboard surface of the seal segments (40) of the assembly and one or more coolan...

A turbine engine fan case assembly includes a structural case (100) and a liner assembly (140). A radially accommodating attachment system connects the liner assembly (140) to the structural case (100). The attachment system comprises a circumferentially-d...

The insert (2) has a hollow portion inserted through an aperture in a wall (12). A membrane is arranged at one end of the hollow portion. The membrane comprises an outer surface that defines a fluid stream within a turbomachine along an inner surface of th...

The method involves pivoting a rotor (4) at a bearing housing (2), and fastening a flow-throughable housing (6) at the bearing housing facing the rotor. The housing (6) is provided with a coating (7) in an area of its inner surface. A layer is polished by ...

The present invention provides, in one embodiment, an annular turbine seal for disposition in a turbine between a rotatable component (110) having an axis of rotation and a turbine housing (120) about the same axis of rotation. The turbine seal has a plura...