Cycle Analysis for Helicopter Gas Turbine Engines
Abstract
The performance potential of a 1000 kW gas turbine engine is determined in terms of specific fuel consumption and specific power. Compressor and turbine efficiencies are assumed size dependent and the cycle temperature is determined from the material capability and cooling technology available. Simple cycle and heat exchanger cycles engines for helicopters are considered. In the near term, engines with a two-stage gas generator turbine and uncooled power turbine offer an attractive simple cycle solution. However, as cycle temperatures are increased, a cooled power turbine becomes necessary and a lower pressure ratio engine with a single-stage gas generator turbine provides the most cost effective solution. The heat exchanger cycle is attractive only for those helicopter missions where endurance, or fuel conservation, is the dominating requirement. The benefits of variable power turbine geometry are considered marginal.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1989
- Accession Number
- ADA212209
Entities
People
- A. D. Bewley
Organizations
- Royal Aircraft Establishment