Advanced and Adaptable Military Propulsion
Abstract
Analyses and calculations were carried out to quantify the gain in performance (as measured in terms of thrust specific fuel consumption and range productivity) in aircraft turbine engines incorporating adaptability/variability. A 5-10% variability in (turbine and propelling) nozzle areas would allow the compression system to have an operating point for subsonic loiter identical to that for supersonic flight to destination, resulting in a 20% improvement in thrust specific fuel consumption. Zero spillage engines (engines in which the inlet and the engine capture the full streamtube, at constant area over flight Mach number ranging from 0.8 to 2.5) are shown to be feasible. Progress toward low fuel consumption (i.e. fuel efficient engine technology) can be achieved through engineering very high pressure ratio (-hundreds) compression system with high polytropic efficiency compressor components. Enablers that include the variable area swirling turbine, flow aspiration, compressor rim cooling and intercooling are suggested for realizing the required engine variability, zero spillage engines and fuel-efficient propulsion systems. While these technology enablers are technically challenging in practice, they are sure to pay off handsomely (such as significantly broadening the scope and flexibility of missions presently not accessible with engines of fixed geometry).
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 22, 2008
- Accession Number
- ADA476584
Entities
People
- Alan H. Epstein
- Choon S. Tan
Organizations
- Massachusetts Institute of Technology