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Unformatted text preview: combustor, and two turbines. The first turbine, the high pressure turbine, provides the power for the compressor through a coupling shaft. The second turbine provides the net power output of the system. You are given the following system specifications: T t,2 = 300 K (compressor inlet total temperature) T t4 = 1500 K (high pressure turbine max inlet total temperature) T t6 = 500 K (low pressure turbine exit total temperature) r c = 20 (compressor stagnation pressure ratio) m ± = 100 kg/s You may assume that air behaves as a perfect gas with cp=1000 J/kgK in the compressor and cp=1100 J/kgK in the turbines. You may also assume that the compressor is adiabatic and reversible. Find the power output of the low pressure turbine. Page 2 of 2...
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This note was uploaded on 01/28/2012 for the course AERO 16.050 taught by Professor Zoltanspakovszky during the Fall '02 term at MIT.
- Fall '02