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

A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments arranged as an annular shroud, each of the shroud segments comprising 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, wherein an open channel is formed through the outer wall of each shroud segment; an annular stationary structure surrounding the shroud segments; and a hanger received in the open channel of each shroud segment and mechanically coupled to the stationary structure, each of the hangers passing through the respective open channel and including an enlarged portion having greater cross-sectional area than the open channel, the enlarged portion engaging the outer wall of the respective shroud segment, so as to retain the shroud segment radially relative to the stationary structure.

Low-ductility open channel turbine shroud

A shroud segment for a gas turbine engine, the shroud segment 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; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.

Low-ductility turbine shroud

A turbine flowpath apparatus is provided for a gas turbine engine having a centerline axis. The apparatus includes: an annular flowpath member of low-ductility material, the flowpath member having a flowpath surface and an opposed back surface, and having a cross-sectional shape comprising a generally cylindrical forward section and an aft section that extends aft and radially outward at a non-perpendicular, non-parallel angle to the centerline axis; an annular stationary structure surrounding the flowpath member; and an annular centering spring disposed between the stationary structure and the flowpath member, the centering spring urging the flowpath member towards a centered position within the stationary structure.

Low-ductility turbine shroud flowpath and mounting arrangement therefor

A turbine shroud apparatus for a gas turbine engine includes an arcuate turbine shroud segment of 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. At least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall. Radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof.

Low-ductility turbine shroud and mounting apparatus

vanes 20 are generally hollow with a passage 23 through which service pipes 24 extend. These service pipes 24 must be connected such that they can allow for thermal expansion and contraction but also anti rotation features are needed in order to prevent damage when a supply coupling is connected through a pipe end 25. This anti-rotation feature is generally provided between a top hat 26 and a pipe end 25 through flanges 30, 31. In order to allow reduced spacing between the top of the vane 20 and a casing the flanges 30, 31 are arranged to allow at least recessing of a first flange 30 into a passage opening profile 27 whereby those flanges 30 inter-engage with second flanges 31 at a surface interface 33 to prevent rotation.

Service pipe coupling within a gas turbine nozzle guide vane

A blade track for a gas turbine engine, the blade track (20) comprises a plurality of blade track segments (22) each comprised of ceramic-matrix composite materials and shaped to extend part-way around a central axis (A). Each blade track segment (22) includes opposing circumferential end faces (21, 23) and a radially outer surface (25) extending between the end faces. A composite-lock structure (24) is positioned to engage the outer surfaces (25) of the blade track segments (22). The composite-lock structure (24) includes at least one reinforcement fiber (52) of ceramic-containing material suspended in ceramic-matrix material. The blade track segments (22) are positioned circumferentially around the central axis (A) to form a ring. The end faces (21, 23) of the blade track segments (22) are engaged with one another, and the composite-lock structure (24) is configured to provide a radially-inward force toward the central axis against the blade track segments (22) such that each blade track segment (22) acts as a keystone to maintain the form of the ring.

Composite keystoned blade track

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Impingement tubes for gas turbine engine assemblies with ceramic matrix composite components

A turbine section adapted for use in a gas turbine engine includes a turbine case, a turbine wheel, and a turbine vane assembly. The turbine case is made from metallic materials. The turbine wheel is housed in the case. The turbine vane assembly is fixed to the case and configured to smooth and redirect air moving along a primary gas path of the turbine section.

Steven Hillier

Papers

Service pipe coupling within a gas turbine nozzle guide vane

Composite keystoned blade track

Impingement tubes for gas turbine engine assemblies with ceramic matrix composite components

Turbine vane assembly with ceramic matrix composite vanes