SINGLE ROTOR ENGINE - FEASIBILITY.
Final rept., revised ed.
CURTISS-WRIGHT CORP WOOD-RIDGE N J WRIGHT AERONAUTICAL DIV
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The single rotor engine concept is a gas turbine engine configuration utilizing a single stage axial flow compressor which has interwoven through the compressor blading and disk a radial inflow-axial exit turbine. Thus, the rotating elements are uniquely combined within a single disk. The complete gas generator consists of stationary inlet guide vanes, the rotor, compressor exit stators and diffuser, combustion chamber, turbine nozzle assembly, and a turbine discharge diffuser. An experimental program was undertaken in which the feasibility of the concept was investigated. The effort involved the design, fabrication, and test of a turboshaft version of the concept. The Curtiss-Wright designation for this unit is WTS-11. During the course of the investigation, a total of 137 hours 50 minutes test time was accumulated in the component test phase of the work. A good understanding of the operating characteristics of the compressor, turbine, and combustionchamber was achieved. A self-sustaining gas generator run is possible, utilizing these components which are not fully developed at lower-than-design turbine entry temperature.
- Jet and Gas Turbine Engines