Accession Number:

AD0642257

Title:

SINGLE ROTOR ENGINE - FEASIBILITY.

Descriptive Note:

Final rept., revised ed.

Corporate Author:

CURTISS-WRIGHT CORP WOOD-RIDGE N J WRIGHT AERONAUTICAL DIV

Personal Author(s):

Report Date:

1966-07-23

Pagination or Media Count:

33.0

Abstract:

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.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE