Abstract: An airfoil structure for use in an axial flow turbomachine is disclosed. Various construction details which improve the durability, integrity and the cooling effectiveness of the structure are shown and a method for fabricating the structure is developed. The tip of the structure is closed by a tip cap, and in one embodiment, a ductile material is deposited between the tip of the structure and the tip cap to prevent the leakage of cooling medium.

Abstract: A turbofan engine is provided with a flow splitter at the inlet of the compressor with preloaded inner and outer walls. The inner wall and outer wall are positioned generally coaxially of each other and form a generally hollow, annular shell structure which is stressed in the axial direction. The inner wall comprised of two axially separable ring sections is placed in compression while the outer wall is placed in tension. The axial stressing compensates for transient growth differentials due to thermals in the inner and outer walls, also for tolerance buildup between the components forming the walls and for deflections that are created by blow-off loads transmitted through the walls from inlet guide vanes.

Abstract: A diffuser-burner casing in the combustion section of an axial flow gas turbine engine transmits axial engine loads between the compressor section and the turbine section and serves as a housing for the combustion chamber assemblies and as a bearing support for the shaft or shafts extending between the compressor and turbine sections. The casing has outer, intermediate and inner ring portions structurally interconnected for limited flexure under the influence of thermal gradients and stresses. The outer ring portion is connected to the intermediate ring portion by means of a frustoconical wall portion which defines the forward part of an annular plenum in which the combustion chamber assemblies are located. The intermediate ring portion and the inner ring portion are interconnected by means of a plurality of circumaxially spaced struts, and form the diffuser for the compressor which discharges into the annular plenum containing the combustion chamber assemblies.

Abstract: A gas turbine disk design having a sideplate construction which prevents the leakage of hot gas across the turbine disk is disclosed. The sideplates are segmented and facilitate cooling of the turbine blades. Slidably mounted studs hold the sideplates in surface contact with the disk and prevent the buildup of stress concentrations in either the plates or the attaching members.