Jason David Shapiro

TL;DR: In this article, an annular support member (14), a turbine shroud (12), and a spring (32) are arranged between the support member and the turbine shroud to push the shroud to a concentric position within the support members.

TL;DR: In this paper, a gas turbine engine shroud is constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface.

TL;DR: A composite annular shroud (42) supported by a support assembly (46) including at least two single piece full 360 degree rings (50, 52, 54 or 130) and at least partially disposed within an innermost one of the rings is described in this article.

TL;DR: A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle (34) having spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane (36), disposed in a primary flowpath of the engine; and (c) a supporting structure coupled to the outer band (38) such that an outer band cavity (68) is defined between the inner band and the stationary structure as discussed by the authors.

TL;DR: A turbine wall includes opposite back and front sides as discussed by the authors, where cooling holes are inclined longitudinally through the wall and adjacent holes are spaced laterally apart and are inclined oppositely for channeling cooling air there in counterflow.