Study of an advanced general aviation turbine engine (gate). Final report

Technical Report · Tue Apr 10 04:00:00 EST 1979

OSTI ID:5584244

Gill, J C; Short, F R; Staton, D V; Zolezzi, B A; Curry, C E

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.

• Research Organization: Detroit Diesel Allison, Indianapolis, IN (USA)
• OSTI ID: 5584244
• Report Number(s): N-79-21073
• Country of Publication: United States
• Language: English

Related Subjects

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION
320201* -- Energy Conservation
Consumption
& Utilization-- Transportation-- Air & Aerospace
DESIGN
ECONOMIC ANALYSIS
ECONOMICS
ENERGY CONSUMPTION
ENGINES
FUEL CONSUMPTION
GAS TURBINE ENGINES
INTERNAL COMBUSTION ENGINES
TECHNOLOGY ASSESSMENT