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This paper addresses the design and fabrication of a high temperature radial turbine wheel constructed by a composite casting/bonding technique. Areas discussed include aerodynamic analyses; the design of blade internal passages for cooling the dual turbine wheel (star wheel and exducer) in a 2800°F (1810K) TIT service environment; the procedure for producing the castings; and the fabrication of cooling passages by a “split blade” technique in which the internal details are constructed independently from sheet metal and sintered powder and are subsequently HIP-bonded within the wheels.

Significant weight savings are therefore feasible with rotating assemblies using lower density materials such as ceramics and composites. This paper discusses the results of analytical studies supported by current development efforts and research paths to implement fast start technology for small gas turbine APU's.

Significant weight savings are therefore feasible with rotating assemblies using lower density materials such as ceramics and composites. Recent tests are described at the authors affiliation wherein a modified T20 small gas turbine was accelerated from zero to 100% speed in 2 1/2 seconds.