6. The first stage of an axial flow compressor is designed for free vortex conditions, with no inlet guide vanes. The rotationalspeed is 13000 rpm, andstagnation temperature rise is 18°C. The hub-tip ratio is 0.6, the work donefactoris0.94, andisentropicefficiency of the stage is 0.91.Assumingthe inletvelocity is 150m/sand ambient conditions are 1 bar and 300 K. Compute (a) the tip radius and corresponding rotor angles, if the Mach number relative to the tip is limited to 0.91, (b) mass flow entering the stage (c) stage stagnation pressure ratio and power required and (d) rotor air angles at the root section.
6. The first stage of an axial flow compressor is designed for free vortex conditions, with no inlet guide vanes. The rotationalspeed is 13000 rpm, andstagnation temperature rise is 18°C. The hub-tip ratio is 0.6, the work donefactoris0.94, andisentropicefficiency of the stage is 0.91.Assumingthe inletvelocity is 150m/sand ambient conditions are 1 bar and 300 K. Compute (a) the tip radius and corresponding rotor angles, if the Mach number relative to the tip is limited to 0.91, (b) mass flow entering the stage (c) stage stagnation pressure ratio and power required and (d) rotor air angles at the root section.
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:6. The first stage of an axial flow compressor is designed for free vortex conditions, with no
inlet guide vanes. The rotationalspeedis 13000 rpm, andstagnation temperature rise
is 18°C. Thehub-tip ratio is 0.6, the work donefactoris0.94, andisentropicefficiency
of the stage is 0.91.Assumingtheinletvelocity is 150m/sand ambient conditions are 1
bar and 300 K. Compute (a) the tip radius and corresponding rotor angles, if the Mach
number relative to the tip is limited to 0.91, (b) mass flow entering the stage (c)
stage stagnation pressure ratio and power required and (d) rotor air angles at the
root section.
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