STUDY OF AN ADVANCED GENERAL AVIATION TURBINE ENGINE (GATE)

The best technology program for a small, economically viable gas turbine engine applicable to the general aviation helicopter and aircraft market for 1985-1990 was studied. Turboshaft and turboprop engines in the 112 to 746 kW (150 to 1000 hp) range and turbofan engines up to 6672 N (1500 lbf) thrust were considered. A good market for new turbine engines was predicted for 1988 providing aircraft are designed to capitalize on the advantages of the turbine engine. Parametric engine families were defined in terms of design and off-design performance, mass, and cost. These were evaluated in aircraft design missions selected to represent important market segments for fixed and rotary-wing applications. Payoff parameters influenced by engine cycle and configuration changes were aircraft gross mass, acquisition cost, total cost of ownership, and cash flow. Significant advantage over a current technology, small gas turbine engines was found especially in cost of ownership and fuel economy for airframes incorporating an air-cooled high-pressure ratio engine. A power class of 373 kW (500 hp) was recommended as the next frontier for technology advance where large improvements in fuel economy and engine mass appear possible through component research and development.

  • Corporate Authors:

    Detroit Diesel Allison

    P.O. Box 894
    Indianapolis, Indiana,   United States  46206
  • Authors:
    • Gill, J C
    • Short, F R
    • Staton, D V
    • Zolezzi, B A
    • Curry, C E
  • Publication Date: 1979-4-10

Media Info

  • Pagination: 147 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00197951
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-CR-159559 Final Rpt.
  • Contract Numbers: NAS3-20756
  • Files: TRIS
  • Created Date: Sep 15 1980 12:00AM