Patent ID: 9200530
Filing Date: 2015-12-01
Classification: F01D,Y02T

Abstract:
1. A radial position control assembly for a gas turbine engine stage comprising: a case structure; a supported structure operatively supported by the case structure, the supported structure including a hook providing an annular recess; a support ring received in the recess, the supported structure and the support ring having different coefficients of thermal expansion, wherein the support ring is a continuous annular structure about 360° of a circumference about which the support ring cannot uncouple from itself such that the support ring is configured to expand and contract as a unitary structure, and the support ring is a continuous circumferentially unbroken annular structure; and a sealing structure adjacent to the supported structure, the support ring maintaining the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure.