This chapter reviews air‐breathing engine cycles and develops 1‐D, steady solution methodology based on thermodynamics and conservation laws for their performance parameters. The turbojet performance parameters are specific thrust, specific fuel consumption, thermal, propulsive, and overall efficiencies. The chapter presents a brief review of aircraft gas turbine propulsion. In gas turbine engines the working fluid is treated as perfect gas, often air, which behaves as continuum rather than individual molecules. At the heart of an aircraft gas turbine engine is a gas generator. An aircraft engine is designed to produce thrust. To augment the thrust of an aircraft gas turbine engine, an afterburner can be used. A fuel‐rich solid propellant rocket provides the takeoff thrust. The chapter also shows the various contributions to net installed thrust in an air‐breathing jet engine.
Aircraft Engines – A Review
2019-11-18
107 pages
Article/Chapter (Book)
Electronic Resource
English
SLUB | 1948
|Engineering Index Backfile | 1941
|Engineering Index Backfile | 1940
Engineering Index Backfile | 1941
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