Air enters the compressor of an air-standard regenerative gas turbine at p1 5 14.7 lbf/in.2 , T1 5 5308R with a mass flow rate of 90,000 lb/h. The compressor pressure ratio is 10, the turbine inlet temperature is 22008R, and the regenerator effectiveness is 80%. Determine the thermal efficiency and net power developed, in hp, for each of the following configurations that build on 9.67(c). (a) Introduce two-stage compression with intercooling between the compressor stages at a pressure of 50 lbf/in.2 Each compressor stage has an isentropic efficiency of 84% and the temperature of the air entering the second stage is 5308R. The isentropic turbine efficiency is 88%. (b) Introduce two-stage expansion with reheat between the turbine stages at a pressure of 50 lbf/in.2 Each turbine stage has an isentropic efficiency of 88% and the temperature of the air entering the second stage is 20008R. The isentropic compressor efficiency is 84%.
The course outline of topics: Exam grades: Quizzes: Un-announced closed book & closed notes quizzes in class Homework: Problems and numerical cycle analysis assignments (submit hard copies) Project: Engine simulation modeling using GT Power software (submit hard copies) Exams: 3 Exams (2 Midterms, 1 Final) Unless otherwise noted, all tests are in-class, Exam # 1 is closed book/closed notes, Exam # 2 is open-book and open-notes, Exam # 3 has 2 parts: Part 1 is closed notes and closed book; Part 2 is open notes and open book Grading: Quizzes (10%), HW (15%), Project (15%), Exams (15%, 15%, 30%) Text book referred by professor Usman: Heywood, J., Internal Combustion Engine Fundamentals, McGraw-Hill, 1988. (Recommended) Stone,
