A brush seal includes a first plate and a second plate. A plurality of bristles have a first end and a second end. The plurality of bristles are arranged between the first and second plates such that the first and second ends extend beyond the first and second plates. The first end is arranged at an angle relative to the second end.

A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.

The austenitic heat resistant steel of the embodiment contains: 24 to 50% by mass of Ni, 5 to 13% by mass of Cr, 0.1 to 12% by mass of Co, 0.1 to 5% by mass of Nb, 0.1 to 0.5% by mass of V, 1.90 to 2.35% by mass of Ti, 0.01 to 0.30% by mass of Al, 0.001 to 0.01% by mass of B, 0.001 to 0.1% by mass of C, and the balance being Fe and inevitable impurities.

A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, ≧35% nickel, 12.0-20.0% cobalt, 5.0-15.0% aluminum, and 5.0-15.0% chromium.

Attaching a fastener to a ceramic matrix composite or ceramic body by inserting a portion of the fastener into a compartment of the body, the compartment having a first portion and a second portion, the second portion outboard of and narrower than the first portion; and delivering a fluid into the fastener to expand a portion of the fastener within the blind compartment first portion.

A shroud segment including a forward radial wall, an aft radial wall and at least one interlocking subcomponent. The forward radial wall, an aft radial wall and the at least one interlocking subcomponent are each formed of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The shroud segment further including an interlocking mechanical joint joining each of the forward radial wall and the aft radial wall to the at least one interlocking subcomponent. Methods are also provided for joining the forward radial wall and the aft radial wall to the at least one interlocking subcomponent using an interlocking mechanical joint.

An annular turbine engine stator portion including a structural support provided in succession with a bonding underlayer and with an abradable coating formed by a resin filled with microbeads, the bonding underlayer for fastening the abradable coating to the structural support being formed by fiber reinforcement made of long fibers having a peripheral portion of the reinforcement that is secured to the structural support and having a central portion thereof that is impregnated with the resin filled with microbeads while the abradable coating is being fastened to the structural support.

The present invention relates to a turbine engine comprising a wheel, (2) mounted on a shaft (4), and a disk (18), adjacent to the wheel (2) and mounted on the same shaft while being rotated by the latter. The disk (18) is made of a material having a density greater than that of the material used to manufacture the wheel (2). The invention is of use in a compressor/turbine.

A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer system comprising a plurality of layers including a relatively erosion-resistant first layer atop a relatively abradable second layer.

An embodiment of a turbine assembly includes, among other possible things, a first component including a first component surface, a second component including a second component surface spaced apart from the first component surface, and a brush seal disposed between the first component and the second component. The brush seal includes, among other things, a first bristled region extending in a first direction from a backing plate, and sealingly engaging one of the first component surface and the second component surface. At least one of the backing plate and the first bristled region includes a nickel-based superalloy material having at least 40% of a Ni.sub.3(Al,X) precipitate phase, X being a metallic or refractory element other than Al.