A damper for a turbine blade in a gas turbine engine includes a main body and may include at least one extended end which is adapted to clear radially inner surfaces of two adjacent blade platforms, to enhance the damping profile of the damper and radial support for a seal. An associated seal for the turbine blade includes supported and sealing portions and may further include a locator that interfaces with a catch structure on the blade to maintain the seal in the proper axial position with respect to the radially inner surfaces of the adjacent platforms. The seal may further include a projection adapted to provide interference with the blade in the event that the damper and seal are installed improperly with respect to each other to prevent such improper assembly.

Turbine blade damper and seal

A stator assembly for a rotary machine having a shroud for a stator vane is disclosed. Various construction details are developed which limit movement of the stator vane into the flowpath by reason of the stator vane being restrained by the shroud. In one particular embodiment, a clip member extends through an opening in the tip of the vane and is disposed at a location adjacent a nonflowpath surface of the shroud to restrain the tip of the vane against inward movement through the shroud.

Stator assembly for a rotary machine and clip member for a stator assembly

An improved, highly stable blade-to-blade vibration damper (22) configuration is disclosed which provides substantially continuous blade vibration damping and sealing of an interplatform gap due to positional stability thereof. Disposed in a subplatform cavity, the damper (22) is comprised of a generally triangular shaped body having a vertex (42) thereof aligned with the interplatform gap (64). A primary damper load face (38) abuts a first inclined platform load face (66) and a secondary damper load (40) face abuts a second inclined platformload face (68). Maintenance of sliding planar contact between primary (38) and first load (66) faces and sliding linear contact between secondary (40) and second load (68) faces is afforded by orienting inclined platform faces to have an included angle greater than that of the damper vertex (42) and offsetting a damper center of gravity (58) toward the primary load face (38). The damper (22) may include one or more legs (52,54) to orient the damper in the cavity and one or more extending tabs (56) to discourage hot gas flow thereby. In a preferred embodiment, the damper is utilized as an as-cast member, without the need for additional processing or machining, and the vertex (42) included angle is greater than about 90 degrees.

Stable blade vibration damper for gas turbine engine

A seal means 66 for a blade attachment slot of a rotor assembly 12 is disclosed. Various construction details which adapt the rotor assembly to block the leakage of cooling air from the blade attachment slot 40 as the cooling air is flowed to a rotor blade 22 are developed. In one embodiment, the seal means has a seal plate 68 and baffles 70,72 integral with the seal plate which define a cooling air chamber for receiving cooling air from a passage way 38 in a rotor disk 20. The seal plate extends axially and laterally to block the leakage of cooling air in the radial direction. Baffles extend radially from the plate for blocking the leakage of cooling air in the axial direction.

Seal means for a blade attachment slot of a rotor assembly

A seal for a turbine blade in a gas turbine engine has a sealing portion with two subportions, where the subportions are longitudinally offset from one another, so that the seal may provide sealing for adjacent turbine blades having longitudinally offset inner platform surfaces. The offset between the sealing subportions should correspond generally to the offset between the platform surfaces.

Turbine blade platform seal

A baffle and damper assembly includes end plates for closing the opening between adjacent blade shanks, a connecting member extending between the end plates, retaining means to lock the assembly to its adjacent blades against the urging of centrifugal force, and at least one damper weight movably secured to the connecting member and adapted to bear against the blade platforms under the urging of centrifugal force.

Harvey Waldo Mason

Papers

Interblade baffle and damper

Leit- und daempfungsvorrichtung