Consider A Single Stage Axial Compressor Which Has The Following Operating Conditions Inlet Stagnation Temperature 1 (46.08 KiB) Viewed 35 times
Consider a single-stage axial compressor which has the following operating conditions; = • Inlet stagnation temperature (T..) = 283 K; • Stage pressure ratio (Poz/Pol) = 1.09 • Stage isentropic efficiency ( )= 0.8; • Degree of reaction (R) = 0.367 • Blade speed (U) = 160 m/s • Flow coefficient (c./U) = 0.625 • Constant axial velocity. y =1.3, c, = 1244 J/kg.K Calculate the rotor blade inlet and outlet angles (B, and B). Accompany your calculations with a labelled drawing of the rotor-blade velocity diagram. 3(b). (5 marks) Sketch a T-s diagram for a single-stage 0.5 reaction compressor which clearly indicates all the relevant static temperatures and pressures. Briefly explain why the actual exit static temperature is greater than the isentropic exit static temperature.
Consider one stage of a multi-stage axial-flow turbine which has the following operating conditions; • Degree of reaction (R) = 0; • Blade speed at the mean rotor radius (U) = 80 m/s; • Rotor-blade inlet angle (B) = 450; • Stage inlet stagnation temperature (TO)= 878 K; • Stage outlet stagnation temperature (13)= 869 K; Constant axial velocity; • A stage isentropic efficiency equal to 1.0; • Y =1.311, C = 1209 J/kg.K For this stage, calculate the stage pressure ratio (Pog/poi) and the NGV inlet and outlet angles (a, and a). Accompany your calculations with a labelled drawing of the rotor-blade velocity diagram. 4b). (5 marks) Draw a h-s graph which clearly illustrates the different variations in fluid properties through a 0% reaction axial turbine and a pure impulse axial turbine. Clearly indicate all relevant constant static pressure lines. When are the flow conditions through the two types of turbine identical?
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