A seal assembly for a turbine blade tip shroud including a one-piece bent metallic sheet inter-segment seal having an axial component and a vertical component adapted to fit in a groove formed in the end walls of each shroud segment, wherein the shroud segment has a plateform and radially extending ribs, and the seal fits tightly in the groove providing an axial an a radial component to the seal. A ring seal is also provided for sealing a joint between the shroud and a mounting structure where an annular gap is formed having an "L" shaped cross section, the ring seal having a "C" shaped configuration and one of the legs of the "C" extending within an axial component of the "L" shaped gap. The leg has a wave pattern with the peaks of the wave in contact with opposite radial walls of the axial component of the gap for creating a gas seal at the joint.

Gas turbine engine shroud seals

A shroud segment for being incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case of the gas turbine engine is provided with a back plate having first and second plate portions formed in an arc shape and supported by the turbine case, a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade, a pair of first seal slots for receiving a pair of first spline seal plate, a pair of second seal slots for receiving a pair of second spline seal plate and a pair of seal gaps respectively communicating with the first seal slots and the second seal slots. The seal gaps are respectively provided with abutment surfaces recessed from front surfaces of the second seal slots so as to receive front ends of the first spline seal plates.

Turbine shroud segment

A sealing member for sealing between static members, for example between static members of a gas turbine engine. The seal includes a first annular sealing member which includes a first sealing portion and a flange portion. The first sealing member seals a passageway between static members. The flange portion clamps around a flange of a static member, and also seals a portion of circumferential gaps. The first sealing member cooperates with a second sealing member to seal a passageway. Attached to another leg of the flange portion is a ring.

Interstage van seal apparatus

A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim (26) having transverse legs (32,34) at each end, a flattened leaf spring (38) to urge the shim (26) into sealing contact with the sealing surfaces (18, 24) of the turbine parts (10,12), and a shim protection material (46) to avoid wear to the shim (26) on the contact side (18). The shim protection material (46) can include one or more metal fiber cloth layers secured to the shim (26), for example, by seam welding to a pair of rails (52) or to the legs (32,34) of the shim (26).

Biased wear resistant turbine seal assembly

A seating spring is provided for a compressor stator having a radially outer casing with a circumferential casing slot for mounting a plurality of circumferentially adjoining vane sectors at outer bands thereof. The seating spring includes a reaction tab configured to abut the casing at one side of the casing slot. A resilient spring arm is fixedly joined to the reaction tab and is configured to abut a respective one of the outer bands to in-turn bias the one outer band against the casing at an opposite side of the casing slot.

Vane sector spring

A wear shim assembly is provided which includes a substantially U-shaped wear shim for protecting selected wear surfaces on the engine casing of a gas turbine engine. The wear shim advantageously simultaneously protects multiple surfaces of the engine casing, namely, a radial seating surface and an axial seating surface of the engine casing, from undesired differential thermal expansion wear and vibrational wear.

Keith G. Jacobs

Papers

Wear shim for a turbine engine