A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.

Turbine ring assembly

A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment comprising a low-ductility material 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 of the segment; and (b) a first seal assembly received in at least one slot formed in the first end face, the first seal assembly comprising one or more spline seals which protrude from the first end face and which are arranged to define a continuous sealing surface around the perimeter of the first end face

Turbine shroud sealing apparatus

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. The shroud (42) is biased against and in sealing engagement with an inner flange (84) of the innermost ring. A three ring assembly includes the inner ring (50) disposed radially inwardly of a middle ring (52) disposed radially inwardly of an outer ring (54) and the shroud (42) at least partially disposed within the inner ring (50). At least three clocking pins (74) extend radially inwardly from the middle ring (52) through slots (76) in the inner ring (50) into notches (78) in the shroud (42). The middle ring (52) may be an aft end (70) of a support ring (68) fixedly connected to an engine backbone (58). Mounting pins (104) may be press fitted into pin holes (106) in the middle ring (52) and extend radially outwardly from the middle ring (52) through radial holes (107) in the outer ring (54).

Continuous ring composite turbine shroud

A shroud hanger assembly (30) or shroud assembly (30) is provided for a gas turbine engine wherein a hanger (32) includes a radially depending and axially extending arm. The arm (45) or retainer (60) engages a pocket (56) formed in a shroud (50) so as to retain the shroud (50) in a desired position relative to the hanger (32). An aft retaining structure is provided on the hanger (32) and provides a seat for a seal structure which biases the retainer (60) so that the arm (45) of the hanger (32) maintains engagement in the shroud pocket (56). A baffle (52) may be utilized at the hanger (32) to cool at least some portion of the shroud (50).

Shroud hanger assembly

A turbine flowpath apparatus for a gas turbine engine includes: a flowpath component exposed at least partially to a primary combustion gas flowpath of the engine, the flowpath component comprising low-ductility material; a metallic annular stationary structure surrounding the flowpath component, including a bearing surface which bears against the flowpath component, so as to restrain the flowpath component from axial movement in a first direction; and a spring element disposed between the flowpath component and the stationary structure which resilient urges the flowpath component in the first direction against the bearing surface.

Resilient mounting apparatus for low-ductility turbine shroud

A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).

Mounting apparatus for low-ductility turbine shroud

PROBLEM TO BE SOLVED: To provide a turbine shroud mounting assembly for supporting a turbine shroud, while allowing thermal expansion. SOLUTION: A turbine shroud device is provided for a gas turbine engine having a central axis. The device includes: (a) an annular support member (14); (b) the turbine shroud (12) arranged in the support member(14), the shroud being a continuous ring comprising a low-ductility material and having opposed flow passage and back surface and opposed front end and rear end; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14). COPYRIGHT: (C)2011,JPO&INPIT

Robert Carella

Papers

Mounting apparatus for low-ductility turbine shroud

Mounting device for low-ductility turbine shroud