Abstract: A gas turbine combustor includes a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, the combustor liner composed through a ceramic matrix composite material, a forward end of the combustor liner provided with a plurality of circumferentially arranged bolt holes. An inner metal ring is located about an outside surface of the forward end of the combustor liner, the inner metal ring provided with a second plurality of circumferentially spaced bolt holes, with a plurality of bolts extending through the first and second pluralities of bolt holes and secured by self-locking nuts. An outer metal ring is spaced radially outwardly of the inner metal ring, with a plurality of circumferentially spaced struts extending between the inner and outer rings.

Abstract: A mounting assembly for a forward end of a liner in a combustor of a gas turbine engine including a dome and a cowl, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings formed in the forward end of the liner, an aft portion of the cowl, and a portion of the dome, with each pin member including a head portion at one end thereof. A nut is adjustably connected to an end of each pin member opposite the head portion. A bushing is located on each pin member at a position intermediate the head portion and the nut, wherein the openings in the liner forward end are sized to fit around the bushings.

Abstract: A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.

Abstract: A method for securing a nozzle for a turbine is provided. The nozzle includes an airfoil having a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity is defined within the airfoil, the airfoil extending between an inner band and an outer band. The method includes extending at least one member through the airfoil, and at least one of the inner band and the outer band. The method further includes securing the nozzle assembly in position with at least one fastener such that the at least one member is coupled adjacent to at least one of the inner band and the outer band.

Abstract: At least one shroud segment, floating axially independently of adjacent turbine engine shroud assembly members, includes a segment body comprising a radially outer surface and a radially outwardly projecting segment support that includes an axial support wall surface therein. The assembly includes a shroud hanger in axial juxtaposition with the segment support, and at least one axial support projection from the shroud hanger into the segment support at the support wall surface. The support projection supports the shroud segment releasably at the support wall surface sufficiently to enable relative axial movement of the shroud segment on the support projection independently of the shroud hanger and adjacent engine members.

Abstract: A turbine engine axial series of members, axially distinct at least radially outwardly, enables independent axial movement to close gaps therebetween, eliminating need for fluid seals. During engine operation, an axially forward first member surface is movable an axial movement distance to close any gap between the first member and a second member that floats axially independently of adjacent members and that is movable axially responsive to axial force from the first member. Axial movement of the second member toward a third member closes any gap therebetween, the axial length of the gap, prior to engine operation, being substantially no greater than the axial movement distance of the first member.

Abstract: A turbine engine shroud segment having a body including a circumferentially arcuate radially inner surface defining a circumferential arc and a radially outer surface is provided, at least at one axially spaced apart outer surface edge portion surface, with a surface depression extending circumferentially across the outer edge portion and including a planar seal surface. The planar seal surface is spaced apart radially outwardly from the circumferential arc defining a spaced apart chord of the arc. The planar seal surface is joined with the segment body radially outer surface through an arcuate transition surface. In a circumferential assembly of a plurality of the shroud segments into a turbine engine shroud assembly, at least one of the outer surface edge portions and its respective depression portion and fluid seal surface is distinct axially from an axially juxtaposed engine member by a separation therebetween.

Abstract: A turbine engine shroud segment comprises a body including a radially outer surface having axially and circumferentially spaced apart edge surfaces. The segment includes a projection integral with and projecting generally radially outwardly from the body, and positioned at a generally midway surface portion between the axially spaced apart edge surfaces. The projection comprises a head and a transition portion with a cross section smaller than that of the head and integral with and between the head and the body. In a turbine engine shroud assembly, a plurality of such shroud segments are assembled circumferentially with a shroud hanger carrying the projection in a hanger cavity through end portions of radially inner opposed hook members that register with the projection at the transition portion.

Abstract: A turbine engine shroud segment, preferably a low ductility material, for example a ceramic matrix composite, comprises a segment body extending between body circumferential ends. The body includes a body radially inner surface arcuate at least circumferentially, and a body radially outer surface from which a plurality of hooks extend generally radially outwardly. Each hook comprises a generally radially outwardly extending hook arm with a generally axially extending hook end having a generally radially inner surface in spaced apart juxtaposition with a portion of the body radially outer surface. Such body outer surface includes at least two body contact surfaces each matched in shape and in juxtaposition at least at body circumferential ends with a cooperating hanger contact surface. The radially inner surface of each hook end includes a hook end contact surface matched in shape with a cooperating hanger contact surface at least in a circumferential middle portion of such surface.

Abstract: A turbine nozzle baffle includes a plurality of apertures inclined through a shell for discharging a coolant tangentially therefrom. The baffle is disposed inside a nozzle vane and the tangentially discharged coolant flows generally parallel along the inner surface of the vane for convection cooling thereof.