5. Combustion gases with k=1.35, Cp=1107 J/(kg.K) and R= 287 J/(kg.K) flow at stagnation pressure and stagnation temperature of 390kPa and 1150 K respectively, flow through a 90° IFR turbine to an exit static pressure of 100 kPa. The total to static efficiency is 80% and the flow leaves the stator choked (Mach Number=1). The relative velocity at the inlet to the rotor is radial and the flow leaves the turbine without a swirl. Find (a) the work delivered per unit flow rate, (b) the impeller tip velocity and (c) the flow angle at the inlet to the rotor. :-
5. Combustion gases with k=1.35, Cp=1107 J/(kg.K) and R= 287 J/(kg.K) flow at stagnation pressure and stagnation temperature of 390kPa and 1150 K respectively, flow through a 90° IFR turbine to an exit static pressure of 100 kPa. The total to static efficiency is 80% and the flow leaves the stator choked (Mach Number=1). The relative velocity at the inlet to the rotor is radial and the flow leaves the turbine without a swirl. Find (a) the work delivered per unit flow rate, (b) the impeller tip velocity and (c) the flow angle at the inlet to the rotor. :-
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
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Transcribed Image Text:5. Combustion gases with k=1.35, Cp=1107 J/(kg.K) and R= 287 J/(kg.K) flow at stagnation
pressure and stagnation temperature of 390kPa and 1150 K respectively, flow through a
90° IFR turbine to an exit static pressure of 100 kPa. The total to static efficiency is 80%
and the flow leaves the stator choked (Mach Number=1). The relative velocity at the inlet
to the rotor is radial and the flow leaves the turbine without a swirl. Find (a) the work
delivered per unit flow rate, (b) the impeller tip velocity and (c) the flow angle at the inlet
to the rotor. :-
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VIEWStep 2: Determine the static temperature at the exit and the velocity at the exit.
VIEWStep 3: Calculate the stagnation temperature at the exit
VIEWStep 4: Calculate the work delivered per unit flow rate:
VIEWStep 5: Calculate the impeller tip velocity:
VIEWStep 6: Calculate the flow angle of velocity at the rotor inlet:
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