Abstract: A turbine engine shroud segment comprises a body including an outer surface from and along which a segment projection extends away from and in an axial direction. The segment projection includes circumferentially spaced apart segment support surfaces. A shroud hanger comprises a body including an inner surface from and along which a hanger projection extends in an axial direction. The hanger projection includes circumferentially spaced hanger bearing surfaces. In a circumferential turbine engine shroud assembly of shroud segments and hangers, a shroud hanger is assembled between a pair of adjacent shroud segments separated by an axial interface. The hanger projection is in juxtaposition with the interface, and respective segment support surfaces and hanger bearing surfaces are in registry.

Abstract: A turbine engine shroud segment is provided with a radially outer surface including a pair of spaced apart, opposed first and second edge portion surface depressions, for example spaced circumferentially, having a seal surface shaped to receive, in a surface depression formed between assembled adjacent segments in a shroud assembly, or axially assembled adjacent segments and engine members, a radially outer fluid seal member. The depression portions of a shroud segment are joined with the radially outer surface of the shroud segment through an arcuate transition surface. Stresses generated during engine operation in the shroud material are reduced, enabling practical use of a low ductility material, for example a ceramic matrix composite. The edge portion surface depressions are provided with a first shape and the fluid seal member, disposed at the depression, is provided with a surface of a second shape matched in shape with the first shape.

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 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 is provided with a radially outer surface including a pair of spaced apart, opposed first and second edge portion surface depressions, for example spaced circumferentially, having a seal surface shaped to receive, in a surface depression formed between assembled adjacent segments in a shroud assembly, or axially assembled adjacent segments and engine members, a radially outer fluid seal member. The depression portions of a shroud segment are joined with the radially outer surface of the shroud segment through an arcuate transition surface. Stresses generated during engine operation in the shroud material are reduced, enabling practical use of a low ductility material, for example a ceramic matrix composite. The edge portion surface depressions are provided with a first shape and the fluid seal member, disposed at the depression, is provided with a surface of a second shape matched in shape with the first shape.

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 assembly comprises at least one shroud segment floating axially independently of other engine members disposed in adjacent juxtaposition with the shroud segment. In one embodiment, the assembly comprises a plurality of shroud segments, in one form of a low ductility material, disposed in circumferential juxtaposition. Each segment includes a segment body comprising a radially outer surface with which a radially outwardly projecting segment support is attached. The shroud segment support includes therein a support wall surface extending generally axially into and at least partially through the segment support. The assembly includes a shroud hanger in axial juxtaposition with the shroud segment support, and at least one support projection, for example a support pin, extending generally axially from the shroud hanger into the shroud segment support at the shroud segment support wall surface.

Abstract: A turbine engine comprising compressor, combustion and turbine sections includes a combination of an axially juxtaposed series of members, for example a turbine nozzle, a shroud and a turbine rear frame or additional nozzle, axially distinct one from another at least at a radially outer portion. The series of members function and are assembled axially together to enable appropriate relative, independent axial movement thereby eliminating a need for fluid seals between members of the series. An axially forward first member has a radially inner portion held by the engine and a radially outer portion cantilevered from the inner portion to enable general axial movement of the outer portion of a first axial length during engine operation. The outer portion includes an axially aft first surface in juxtaposition with an axially forward second surface of a middle or second member.

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 engine shroud segment comprises a segment body including a radially inner surface arcuate at least circumferentially, a radially outer surface, and a plurality of axially and circumferentially spaced apart edge surfaces connected with and between the inner and outer surfaces. For carrying the segment body, the segment includes a projection, in one form a single projection, integral with and projecting generally radially outwardly from the body. The projection is selected to be positioned at a generally midway surface portion of the body radially outer surface between at least one of the plurality of spaced apart edge surfaces. The projection comprises a projection head spaced apart from the body radially outer surface and a projection transition portion, having a transition surface, integral with both the projection head and the body radially outer surface.

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.