Abstract: An improved combustor bulkhead 70 for a gas turbine engine 10 includes a plurality of holes 72 and baffles 90 which directs cooling air radially inward around a fuel injector to set up and shape a toroidal recirculation zone 114 surrounding the fuel injector vortex 116 and suppress smoke and carbon formation in the combustion chamber. Various construction details are described to provide an aerodynamically superior bulkhead design.

Abstract: A process for making a hybrid ceramic article is disclosed. The process involves embedding an array of refractory ceramic tiles in a fiber reinforced glass-ceramic matrix composite substrate. The hybrid ceramic article so formed exhibits high thermal stability and elevated temperature load-bearing ability.

Abstract: A hybrid ceramic article for high temperature applications is disclosed. The thermal barrier comprises an array of refractory ceramic tiles embedded in a fiber reinforced glass-ceramic matrix composite structure. The hybrid ceramic article exhibits high thermal stability and elevated temperature load bearing ability. A combustor liner and a combustor liner panel for a gas turbine engine and also disclosed.

Abstract: A rotor blade 14 having a spar 138 and shell 134 is disclosed. Various construction details are developed for efficiently transferring rotational loads on the rotor blade to the root section 28 of the spar. The spar has a projection 139 over which extends a portion 100 of the shell and a platform 36 of the rotor blade.

Abstract: A rotor assembly 10 having a coolable rotor blade 14 for a gas turbine engine is disclosed. Various construction details are discussed which enable the rotor blade to satisfy the aerodynamic requirements of the engine and the requirements of fatigue life for the rotor assembly. The rotor blade includes a spar 38 and a shell 34 which extends chordwisely beyond the root 42 of the spar. In one embodiment, an axis of symmetry A.sub.r of the root of the spar is parallel to the axis of rotation A of the rotor assembly.

Abstract: A coolable rotor blade 14 for an axial flow rotary machine and a method for making the rotor blade are disclosed. The rotor blade includes a spar 38 and a shell 34 for defining the airfoil surface of the rotor blade. A platform 36 extends over the shell and the spar. The spar has a root 42 and an airfoil section 40. The shell is spaced from the spar and is joined to the airfoil section of the spar for defining cooling passages in the blade. The shell and the platform are each attached to the spar for support against rotational force. The method includes the steps of joining a shell to the airfoil section of the spar which extends over a portion of a projection 139 on the spar and forming a platform about the spar and the shell such that the platform is attached to the spar and extends over the projection and a portion of the shell. In one embodiment, the spar is formed of a first material, the shell of a second material, and the platform a third material.

Abstract: A combustor liner is fabricated from a plurality of individual segments each containing counter/parallel Finwall material and are arranged circumferentially and axially to define the combustion zone. Each segment is supported by a hook and ring construction to an opened lattice frame with sufficient tolerance between the hook and ring to permit thermal expansion with a minimal of induced stresses.