HW#5 - Jerry M. Seitzman
Transcription
HW#5 - Jerry M. Seitzman
AE4451/Seitzman Spring 2015 Due Mon., March 2 Problem Set #5: Turbine Engines Homework solutions should be neat and logically presented, see format requirements at http://seitzman.gatech.edu/classes/ae4451/homeworkformat.html. If appropriate, include a sketch of the flow/system, and indicate clearly your choice of control surface. Always indicate any assumptions you make. If you use any results or equations from the class notes or text in you solutions, please note and reference them (but you better be sure they are applicable to the problem at hand). Try to solve the problem algebraically first. If possible, only use numbers/values in the final steps of each solution. 1. Polytropic Efficiency For turbomachinery, the component’s adiabatic efficiency can be modeled using the concept of the polytropic efficiency p. It turns out that well-designed, modern compression machines have similar polytropic efficiencies, independent of the overall pressure ratio. The polytropic efficiency is the efficiency of an adiabatic device with an infinitesimal (very small) pressure change, and like the adiabatic efficiency, p<1. Since a finite pressure change can be thought of as many infinitesimal pressure changes, we can produce a relationship between the adiabatic efficiency of a real device and the polytropic efficiency. For a compressor or fan with a stagnation pressure ratio Pr (outlet/inlet) and a polytropic efficiency p, the adiabatic efficiency is given by Pr Pr 1 1 p 1 . 1 assuming a thermally and calorically perfect gas. Using this definition, find an expression for the exit stagnation temperature (To3) of a compressor with an inlet temperature To2, a polytropic efficiency p, a stagnation pressure ratio po3/po2, and a normalized specific heat cp/R. 2. Ram-Turbine (former 2nd midterm problem) An air-powered turbine (or ram-turbine) is shown below. On an aircraft or missile in flight, this device directs freestream air (at ambient temperature T a) into an internal combustor. The exhaust of the combustor runs a power turbine that drives an electric generator (to power electrical systems on the vehicle). Electric Generator Ta Combustor Nozzle Turbine To,c To,d To,b Te For this problem, you are to assume that: 1) the gas passing through the ramturbine is thermally & calorically perfect (=1.4); 2) all processes are reversible and the nozzle is perfectly expanded; 3) there is no heat loss from any device; 4) the fuel addition does not significantly change the total mass flowrate: (1+f)1; and 5) the ram-turbine is designed to produce zero specific thrust. a) For an aircraft flight velocity of 240 m/s, what is the nozzle exhaust velocity of such a ram-turbine system? b) Write an expression for Te in terms of the combustor exit temperature (T o,c), the flight Mach number (M) and whatever other properties of air you need. (It may help to draw a T-s diagram for this ideal cycle.) c) Find the power that can be delivered to the electric generator IF 0.5 kg/s of air enters the ram-turbine, M=0.90, Ta=220 K and the maximum temperature limit of the ram-turbine is 1200 K. 2