Gas enters the nozzles of an axial flow turbine stage with uniform total pressure at a uniformvelocity c1 in the axial direction and leaves the nozzles at a constant flow angle α2 to theaxial direction. The absolute flow leaving the rotor c3 is completely axial at all radii. Using radialequilibrium theory and assuming no losses in total pressure show that where Um is the mean blade speed, cθm2 is the tangential velocity component at nozzle exit at themean radius r 1⁄4 rm. (Note: The approximate c3 1⁄4 c1 at r 1⁄4 rm is used to derive this expression.) Gas enters the nozzles of an axial flow turbine stage with uniform total pressure at a uniformvelocity c, in the axial direction and leaves the nozzles at a constant flow angle a, to theaxial direction. The absolute flow leaving the rotor c3 is completely axial at all radii. Using radialequilibrium theory and assuming no losses in total pressure show thatcos*az](G- G)/2 = UmCom2where Um is the mean blade speed, com2 is the tangential velocity component at nozzle exit at themean radius r=rm. (Note: The approximate c3 =c1 at r= rm is used to derive this expression.)

The flow angle is defined as a function of radius and the velocity component distribution is…

Answered: Gas enters the nozzles of an axial flow…

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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Gas enters the nozzles of an axial flow turbine stage with uniform total pressure at a uniform
velocity c1 in the axial direction and leaves the nozzles at a constant flow angle α2 to the
axial direction. The absolute flow leaving the rotor c3 is completely axial at all radii. Using radial
equilibrium theory and assuming no losses in total pressure show that where Um is the mean blade speed, cθm2 is the tangential velocity component at nozzle exit at themean radius r 1⁄4 rm. (Note: The approximate c3 1⁄4 c1 at r 1⁄4 rm is used to derive this expression.)

Gas enters the nozzles of an axial flow turbine stage with uniform total pressure at a uniform
velocity c, in the axial direction and leaves the nozzles at a constant flow angle a, to the
axial direction. The absolute flow leaving the rotor c3 is completely axial at all radii. Using radial
equilibrium theory and assuming no losses in total pressure show that
cos*az]
(G- G)/2 = UmCom2
where Um is the mean blade speed, com2 is the tangential velocity component at nozzle exit at the
mean radius r=rm. (Note: The approximate c3 =c1 at r= rm is used to derive this expression.)

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