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In a certain axial-flow turbine stage, the axial velocity c is constant. The absolute velocities entering and leaving the stage are in the axial direction. If the flow coefficient c/U is 0.6 and the gas leaves the stator blades at 68.2° from the axial direction, calculate a. the stage loading factor, AW/U²; b. the flow angles relative to the rotor blades; c. the degree of reaction;

In a certain axial-flow turbine stage, the axial velocity c is constant. The absolute velocities entering and leaving the stage are in the axial direction. If the flow coefficient c/U is 0.6 and the gas leaves the stator blades at 68.2° from the axial direction, calculate a. the stage loading factor, AW/U²; b. the flow angles relative to the rotor blades; c. the degree of reaction;

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
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6. In a certain axial-flow turbine stage, the axial velocity cx is constant. The absolute velocities entering and leaving the stage are in the axial direction. If the flow coefficient c/U is 0.6 and the gas leaves the stator blades at 68.2° from the axial direction, calculate a. the stage loading factor, AW/U²; b. the flow angles relative to the rotor blades; c. the degree of reaction; d. the total-to-total and total-to-static efficiencies. The Soderberg loss correlation, Eq. (3.46), should be used.
Transcribed Image Text:6. In a certain axial-flow turbine stage, the axial velocity cx is constant. The absolute velocities entering and leaving the stage are in the axial direction. If the flow coefficient c/U is 0.6 and the gas leaves the stator blades at 68.2° from the axial direction, calculate a. the stage loading factor, AW/U²; b. the flow angles relative to the rotor blades; c. the degree of reaction; d. the total-to-total and total-to-static efficiencies. The Soderberg loss correlation, Eq. (3.46), should be used.
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According to Bartleby guideline we can solve only three subpart of a question at time. Please post other part separately.

Solving first three parts.

Thank you.

Given:

 The flow coefficient cxU=0.6

The absolute flow angle at the rotor inlet (α2)=68.2° 

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