United Technologies Corporation

Keith C Belsom

M Stefan Maier

Charles Giles

Warren Schuler

A stator vane assembly for a gas turbine engine is provided which includes a plurality of stator vane segments and a seal ring. Each stator vane segment has an outer platform, an inner platform, and an airfoil extending between the platforms. The stator vane segments collectively form an annular structure. The seal ring includes an abradable bearing pad which extends out from an axial surface of the body of the seal ring. The seal ring is attached to a non-rotating member within the engine, positioned in close proximity to the stator vane segments. Contact, and consequent friction, between the individual stator vane segments and the abradable bearing pad causes the abradable bearing pad to abrade, thereby creating a sealing surface reflective of the opposing stator vane segments in contact with the abradable bearing pad.

Method and apparatus for sealing a gas turbine stator vane assembly

A replaceable clip formed from an elongated bowed member having one end adapted to fit a lug through an aperture and the opposite end fit another lug through a slot. The lugs extend from a panel secured by the clip to an annular shaped shell and the bowed surface bears again the upper surface of the shell to retain the panel while allowing it to grow thermally in both the axial and circumferential directions. The clip is particularly adapted to be used in a transition duct or combustor liner of a gas turbine engine.

Replaceable clip

This invention relates to a clip for securing a segmented panel, such as that of a combustor liner for a gas turbine engine, to the outer shell of the combustor, a clip characterized by having two distinctly different spring rates depending on the magnitude of the load which the clip must support.

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Stuart, FL, United States of America

Keith C Belsom