Question

Consider the flow of combustion gases, withyand R 287 J/(kg K), through a normal turbine stage (G-constant, αι α3.rn-constant), such that the flow angle at the exit of the rotor is the same as that entering the stator, and q a,- 3 14.4o. The inlet total temperature is To1 1200K. The axial velocity is constant cx- 280 m/s. The flow leaves the stator at angle α2 = 57.70. The mean radius of the rotor sr 17 cm, and the rotor turns at 20,000 rpm. (a) Find the work done and the drop in stagnation temperature across the stage. (b) Determine the flow angles of the relative velocity at the inlet and exit of the rotor. A normal stage turbine with R 0 operates with axial entry. The nozzle (stator) turns the flow by 64. (a) Find the flow coefficient. (b) What is the discharge velocity from the nozzles, if the axial velocity is cx 240 m/s? (c) Calculate the work delivered by the stage and the drop in the stagnation temperature, given gases with cp 1148J/(kg

Answer 1

Asger 식duen data W, 30 va auial vwlo ien 42.7 +230 vele wa Relatihe awiat wlsciti (翠) ㄒ = 4 42-9-3 86.9 m/s 280

At the Enit 2. ux ニー71.9-356.6 280 to: UC俾ー俾) ω- 356 ( 492.9+11.9 1(91) stagnatisy

at= (W) 트 ity3 드 /S9.FK tu here Vauial cunt Formala R:o 4た2

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