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For the subsonic axial-flow air expander specified, calculate the stagnation and static pressures and temperatures and the Mach number at the rotor-inlet plane (figure). Also find the rotor rotational speed and the nozzle-inlet blade height for constant-outer-diameter blading. Sketch the form of the complete turbine expansion on an enthalpy-entropy chart. The axial velocity will be constant at this design point. Mass flow, m = 2 kg/s Nozzle-inlet stagnation temperature, Tol=400 °C. Absolute nozzle-inlet stagnation pressure, Po.ai = 3 bars(= 3 x 10³ N/m²) Mean diameter, dm = 0.25 m. Blade height at rotor entry, = 0.1d_(= 1/2{d, - dnl). Flow angle at nozzle exit, a₁ = 70° to axial direction. Drop in stagnation pressure in nozzle, Apo= 0.05 bar Rotor peripheral speed at mean diameter, = 0.5x (component of nozzle outlet velocity, C.).

For the subsonic axial-flow air expander specified, calculate the stagnation and static pressures and temperatures and the Mach number at the rotor-inlet plane (figure). Also find the rotor rotational speed and the nozzle-inlet blade height for constant-outer-diameter blading. Sketch the form of the complete turbine expansion on an enthalpy-entropy chart. The axial velocity will be constant at this design point. Mass flow, m = 2 kg/s Nozzle-inlet stagnation temperature, Tol=400 °C. Absolute nozzle-inlet stagnation pressure, Po.ai = 3 bars(= 3 x 10³ N/m²) Mean diameter, dm = 0.25 m. Blade height at rotor entry, = 0.1d_(= 1/2{d, - dnl). Flow angle at nozzle exit, a₁ = 70° to axial direction. Drop in stagnation pressure in nozzle, Apo= 0.05 bar Rotor peripheral speed at mean diameter, = 0.5x (component of nozzle outlet velocity, C.).

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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Can you solve neat and clean. Start with Given and find. After that start solve the problem. Before it solve right but it was not clear hard to read the variables.
For the subsonic axial-flow air expander specified, calculate the stagnation and static pressures and temperatures and the Mach number at the rotor-inlet plane (figure). Also find the rotor rotational speed and the nozzle-inlet blade height for constant-outer-diameter blading. Sketch the form of the complete turbine expansion on an enthalpy-entropy chart. The axial velocity will be constant at this design point. Mass flow, m = 2 kg/s Nozzle-inlet stagnation temperature, Tol=400 °C. Absolute nozzle-inlet stagnation pressure, Po.ai = 3 bars(= 3 × 10³ N/m²) Mean diameter, dm = 0.25 m. Blade height at rotor entry, I = 0.1d_(= 1/2{d, — dr]). Flow angle at nozzle exit, a₁ = 70° to axial direction. Drop in stagnation pressure in nozzle, App = 0.05 bar Rotor peripheral speed at mean diameter, "=0.5x (component of nozzle outlet velocity, Ca..). dsh dnb dm 0
Transcribed Image Text:For the subsonic axial-flow air expander specified, calculate the stagnation and static pressures and temperatures and the Mach number at the rotor-inlet plane (figure). Also find the rotor rotational speed and the nozzle-inlet blade height for constant-outer-diameter blading. Sketch the form of the complete turbine expansion on an enthalpy-entropy chart. The axial velocity will be constant at this design point. Mass flow, m = 2 kg/s Nozzle-inlet stagnation temperature, Tol=400 °C. Absolute nozzle-inlet stagnation pressure, Po.ai = 3 bars(= 3 × 10³ N/m²) Mean diameter, dm = 0.25 m. Blade height at rotor entry, I = 0.1d_(= 1/2{d, — dr]). Flow angle at nozzle exit, a₁ = 70° to axial direction. Drop in stagnation pressure in nozzle, App = 0.05 bar Rotor peripheral speed at mean diameter, "=0.5x (component of nozzle outlet velocity, Ca..). dsh dnb dm 0
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