Abstract: An assembly of parts is prepared by providing a female part having a recess and a male part having an inserted surface received within the recess. A relief pattern such as knurling is formed on the inserted surface. The inserted surface of the male part is inserted into the recess of the female part with a contacting-channeled fit between the inserted surface and the recess surface, so that the knurl serves to align the inserted surface within the recess. The inserted surface of the male part is brazed or otherwise joined to the recess of the female part.

Abstract: A combustor liner has a stepped combustor liner surface and an overhang portion forming an air cooling slot. A contoured rear facing edge of the overhang portion reduces turbulence of combustion gas flow and reduces a combustor liner surface area exposed to combustion gases. A thermal barrier coating is also applied to the contoured rear facing edge, reducing heat flow into the overhang portion and hence reducing the operating temperature of the combustor liner. Thus, the amount of cooling air is reduced, which can reduce exhaust emissions, increase engine performance and extend a working life of the combustor assembly.

Abstract: A combustor liner has a stepped combustor liner surface and an overhang portion forming an air cooling slot. A contoured rear facing edge of the overhang portion reduces turbulence of combustion gas flow and reduces a combustor liner surface area exposed to combustion gases. A thermal barrier coating is also applied to the contoured rear facing edge, reducing heat flow into the overhang portion and hence reducing the operating temperature of the combustor liner. Thus, the amount of cooling air is reduced, which can reduce exhaust emissions increase engine performance and extend a working life of the combustor assembly.

Abstract: A combustor liner has a stepped combustor liner surface and an overhang portion forming an air cooling slot. A contoured rear facing edge of the overhang portion reduces turbulence of combustion gas flow and reduces a combustor liner surface area exposed to combustion gases. A thermal barrier coating is also applied to the contoured rear facing edge, reducing heat flow into the overhang portion and hence reducing the operating temperature of the combustor liner. Thus, the amount of cooling air is reduced, which can reduce exhaust emissions, increase engine performance and extend a working life of the combustor assembly.

Abstract: An apparatus for modulating a flow of cooling air from a compressor to a turbine in a gas turbine engine is disclosed. The apparatus includes a support member which forms a channel for receiving the cooling flow and has a throat at a downstream end with a radial orientation. A radial flow inducer is connected to the support member adjacent to the channel downstream end for accelerating the cooling flow through the throat of the support member. Apparatus for modulating the quantity of the cooling air flowing through the throat and into the turbine is provided in the form of an axially translating endwall, wherein variation of the throat area is accomplished through modulation of the endwall with respect to the support member. The support member may also house either a stationary, unmodulated axial flow inducer or a second modulated radial flow inducer in addition to the modulated radial flow inducer.

Abstract: A stator frame comprises a connection end (CE) casting having at least one CE integral partial tie bar extending from an inboard side of the CE casting and a pinion end (PE) casting having at least one PE integral partial tie bar extending from an inboard side of the PE casting. Each PE partial tie bar is welded to a respective CE partial tie bar.

Abstract: An insulative panel is attachable to a structure to thermally protect the structure. The insulative panel includes a piece of a compliant, porous material. A support base is bonded to a first side of the piece of porous material, the support base including means for attaching the support base to the structure that is to be protected. A skin made of a thermally resistant material is bonded to a second side of the piece of porous material. Preferably, the porous material is a piece of porous ceramic foam having an apparent density of less than about 25 percent, the support base is a piece of nonporous ceramic material, and the skin is a ceramic thermal barrier coating that is plasma sprayed onto the porous material.

Abstract: Thermally actuated flow diverters for gas turbine engines are provided which include an arrangement of vanes in spaced overlapping array, which direct, e.g. coolant air flow to rotating engine components, each vane having 3 foil components joined at 3 hinge points. That is, a leading foil positioned on the suction side of the vane, a trailing foil pivotably mounted to a rearward portion of such leading foil at a first pivot axis and a third foil positioned on the pressure side of the vane connecting a forward portion of such leading foil and such trailing foil at second and third pivot axes respectively. Either the third foil or the leading foil is fixedly mounted to engine walls of the same material, the other of these two foils defining an actuation link that is expandable and contractable relative to such walls; the third foil having a coefficient of thermal expansion greater than that of the leading foil.

Abstract: A relatively stationary segmented turbine engine shroud, nozzle or frame assembly is sealed against the passage of cooling air into the exhaust gas flowpath by a plurality of spline seals which cooperate with an annular stationary brush seal. The spline seals provide sealing between axially extending confronting edges of adjacent segments while the brush seal provides continuous circumferential sealing around the segments and spline seals.