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
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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![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](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fc7559a47-bb34-494d-9e33-22c98791555e%2F233991f3-939e-4892-a80e-dbffab832d02%2F9nwk8_processed.jpeg&w=3840&q=75)
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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