The GTP305-2 Advanced APU is a single shaft, all shaft power engine incorporating an axial-centrifugal compressor, a reverse flow annular combustor and a radial-axial turbine. Cycle analyses indicated a 10-percent high pressure compressor flow increase improved matching characteristics with the low pressure compressor. The combustion system is a reverse flow annular combustor with an airassist/airblast fuel injection system. The radial-axial turbine stages is characterized by an integrally cast turbine rotor and a cast exhaust duct assembly. The integrated Components Assembly (ICA) rig consists of the combustor and turbines with a dummy mass on the shaft to simulate the compressor. ICA testing was conducted to establish component performance at design operating conditions. ICA and cold air aerodynamic testing of the turbine stage and cooling flow effects, indicates design efficiency goals were exceeded. ICA test results, cold-air testing and combustion system parameters were input to the cycle model. Room temperature strain-control LCF tests were performed and results analyzed on a Weibull distribution. Data analysis indicated LCF life improvement was obtained through HIP and heat treatment. (de Posamentier)
Advanced technology components for model GTP 305-2 aircraft auxiliary power system
Fortschrittliche Technik fuer Teile des Modells GTB 305-2 Flugzeug-Hilfstriebwerk
US Government Research Reports ; Feb ; 1-541
1980
541 Seiten
Report
English
AUXILIARY POWER SYSTEM CONSIDERATIONS FOR ADVANCED MILITARY AIRCRAFT
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