The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. One or more spring tabs extend from the first seal section and/or the second seal section, are disposed between the first and second seal sections, and bias the first and second seal sections away from one another.

A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.

A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.

A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of alloys or allotropes of the material. The phononic regions modify the behavior of the phonons and control heat conduction.

A seal for sealing a space defined between first and second components, the seal having: an annular member having a substantially U-shaped cross section along at least a portion thereof, the portion configured to provide a seal interface at each of the first and second components.

The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components.

The invention relates to a turbine housing (2) for an exhaust gas turbocharger. The turbine housing (2) comprises an outer housing (3) and an inner housing (4) as well as a bearing flange (5). The outer housing (3) is joined to the bearing flange (5). The inner housing (4) comprises a first shell component (7) and a second shell component (8), wherein said first shell component and said second shell component are made of different cast steel materials and are placed side by side in a transverse plane (QE), which is oriented transversely to the longitudinal axis (LA) of the turbine housing (2), and are joined to each other. The bearing flange (5) is a one-piece part, made of uniform material, of the first shell component (7).

The present disclosure relates generally to a sliding seal between two components. At least one of the two components includes a ramped surface on which the sliding seal slides during relative movement between the two components.

A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.

In a manufacturing method of a turbine rotor blade using an Ni-based forged alloy, provided is a manufacturing method of a turbine rotor blade having an excellent workability and a high degree of freedom in the design of a cooling structure. A manufacturing method of a turbine rotor blade according to the present invention is, in a manufacturing method of a turbine rotor blade, using an Ni-based forged alloy, characterized by including: a softening process of increasing a ? phase incoherent with a ? phase that is a matrix phase in the Ni-based forged alloy; a first working process of forming at least two members constituting a rotor blade by using the Ni-based forged alloy after subjected to the softening process; a second working process of forming cooling structural parts in the respective members; and a third working process of joining the members.