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Axial Turbine - Turbomachinery Aerodynamics - Lecture Slides, Slides of Turbomachinery

Indian Institute of Tourism and Travel Management Turbomachinery

Some concept of Turbomachinery Aerodynamics are Axial Flow Compressors, Axial Turbine Design Considerations, Blade Performance, Engine Performance Significantly, Flows Through Axial Compresso. Main points of this lecture are: Axial Turbine, Turbine Rotor, Outlet Flow, Radial Equilibrium, Blade Loading, Loading Coefficient, Flow Inlet, Outlet Angles, Stage Exit, Nozzle Exit Velocity

Typology: Slides

2012/2013

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Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay

Lect 26

Exercise problems

1. (a) An axial turbine rotor is prescribed with rotor

inlet and outlet flow in radial equilibrium. The whirl

component of the flow is designed to vary radially

as : Cw1 = a.r –b/r ; and Cw2 = a.r+ b/r

Where, a and b are constants. Find the inlet and

outlet axial velocities (Ca1 and Ca2 ) from above.

[Ca2= K –2.a2[(r2-1)–2(b/a)lnr] & Ca1=Ca2 axially]

(b) It is prescribed that at mean radius = 0.3 m ,

axial velocity=150 m/s, degree of reaction Rx= 0.5,

blade loading coefficient,ψrotor=H0/Utip2. Rpm=7640

Hub/tip ratio of the rotor =0.5. At 80% rotor radius,

find the rotor relative flow inlet and outlet angles.

[43.20and 10.40]

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Exercise problems

(a) An axial turbine rotor is prescribed with rotor inlet and outlet flow in radial equilibrium. The whirl component of the flow is designed to vary radially

as : C w1 = a .r – b /r ; and C w2 = a .r+ b /r

Where, a and b are constants. Find the inlet and outlet axial velocities (C (^) a1 and C (^) a2 ) from above. [C (^) a^2 = K – 2. a^2 [(r 2 -1)– 2( b / a )lnr] & C (^) a1 =C (^) a2 axially] (b) It is prescribed that at mean radius = 0.3 m , axial velocity=150 m/s, degree of reaction R (^) x = 0.5,

blade loading coefficient,ψrotor =H 0 /Utip^2. Rpm=

Hub/tip ratio of the rotor =0.5. At 80% rotor radius, find the rotor relative flow inlet and outlet angles. [43.2 0 and 10.4 0 ]

Hot gas exits from a turbine stator-nozzle at a

radially constant angle, α 2. The gas is also

prescribed to be in radial equilibrium. Axial velocity variation at that station is given as :

For a turbine in which the axial velocity at radius 0.3m is 100 m/s. If the turbine, as stated above, is designed with constant α 2 = 45 0 , find the axial velocity at that station at 0.6 m radius. [70.7 m/s]

C .r^2 const

sin^2 α