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Unformatted text preview: ASE 376K Homework # 3 Fall 2010 3-1 An afterburner is a device used to increase the thrust of a jet engine for short periods of time. Additional fuel is burned in the gas leaving the turbine so that the gas entering the nozzle is much hotter than it would be otherwise. The following state designations are used for a turbojet engine equipped with afterburner: a 4 7 ( e ) u e f m &amp; 2 3 5 u 6 , f ab m &amp; a Ambient air 5 Turbine outlet, afterburner inlet 2 Compressor inlet 6 Afterburner outlet, nozzle inlet 3 Compressor outlet, combustor inlet 7 Nozzle outlet, engine exit 4 Combustor outlet, turbine inlet The data below have been computed in the simplified analysis of a turbojet being run on a test stand in ambient air T = 300 K , p = 100 kPa assuming = 1.4. For convenience we choose s ref = 0 J/kg-K at T ref = 300 K , p ref = 100 kPa . The stagnation state corresponding to a given state is indicated with a prefix o , e.g. o7 is the stagnation state corresponding to state 7, i.e. T o7 ,...
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This note was uploaded on 09/18/2011 for the course ASE 376K taught by Professor Staff during the Fall '10 term at University of Texas at Austin.
- Fall '10