5. 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 P2.5). 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, Tuni = 400 °C. Absolute nozzle-inlet stagnation pressure, Po,ni = 3 bars(= 3 x 105 N/m²) Mean diameter, dm = 0.25 m. Blade height at rotor entry, 1 = 0.1dm(= 1/2[ds - dn]). 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, um = 0.5x (component of nozzle outlet velocity, Ce,1).
5. 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 P2.5). 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, Tuni = 400 °C. Absolute nozzle-inlet stagnation pressure, Po,ni = 3 bars(= 3 x 105 N/m²) Mean diameter, dm = 0.25 m. Blade height at rotor entry, 1 = 0.1dm(= 1/2[ds - dn]). 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, um = 0.5x (component of nozzle outlet velocity, Ce,1).
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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Transcribed Image Text:Figure P2.5
dsh
dnb
dm
N
3
T
4
![5. 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 P2.5). 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, Tuni
= 400 °C.
Absolute nozzle-inlet stagnation pressure, Po,ni = 3 bars(= 3 x 105 N/m²)
Mean diameter, dm = 0.25 m.
Blade height at rotor entry, 1 = 0.1dm(= 1/2[ds - dn]).
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, um = 0.5x (component of nozzle outlet
velocity, Ce,1).](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fd7b9b716-1b90-48a7-9ec9-5173a2e757ce%2Fe79979db-61d8-4669-85ce-1a41d811a529%2Fct0gvkg_processed.png&w=3840&q=75)
Transcribed Image Text:5. 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 P2.5). 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, Tuni
= 400 °C.
Absolute nozzle-inlet stagnation pressure, Po,ni = 3 bars(= 3 x 105 N/m²)
Mean diameter, dm = 0.25 m.
Blade height at rotor entry, 1 = 0.1dm(= 1/2[ds - dn]).
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, um = 0.5x (component of nozzle outlet
velocity, Ce,1).
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