This preview shows pages 1–2. Sign up to view the full content.
This preview has intentionally blurred sections. Sign up to view the full version.
View Full Document
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...
View
Full
Document
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
 ZoltanSpakovszky

Click to edit the document details