By Edwin P. Alexander

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**Additional info for American locomotives: A pictorial record of steam power 1900-1950**

**Example text**

The resultant force R has components X and Y in the axial and 'tangential' directions respectively. Resolving forces, L = Y cos α + Χ sin a m m X cos a - Y sin a m m D With constant c (i) (ϋ) the axial force acting on one blade is x (iii) = (PX-P2)S The tangential force acting on one blade is, from the momentum equation, Y = pr s c (c 0 + c . ) = pr s c (tan a n + tan a j x y2 y l x 2 1 (iv) where p is a mean density through the c a s c a d e . With the 'incompressible' flow 1 2 approximation (for simplicity), p = p + — pc , then the total p r e s s u r e loss a c r o s s the cascade i s , Δ Ρ ΛΡ ο 1-ρ2 = P ol-po2 = = ΔΡ P rP2+P(VC22) ο 4P

5965/(1 - 0 . 5 3 2 9 2 / 0 . 96 The drag coefficient is defined, e q n s . ·. C m = - ( t a n a. 0219 The lift coefficient is defined for a compressor cascade, eqn. 0972 - 0 . 1. Show, for an axial flow turbine stage, that the relative stagnation enthalpy a c r o s s the rotor row does not change. Draw an enthalpy-entropy diagram for the stage labelling all salient points. Stage reaction for a turbine is defined as the ratio of the static enthalpy drop in the rotor to that in the stage. 0. Solution.

372 m . Using compressible flow analysis determine the axial velocity and the m a s s flow r a t e . Determine also the shaft power needed to drive the compressor when there a r e 6 stages and the mechanical efficiency is 0 . 9 9 . Solution. It is tactitly assumed that the flow preceding the first stage is deflected by inlet guide vanes to give an absolute flow angle a of 30 deg, the same as all the other s t a g e s . *. 1 kg/s S . L . ) yl' = U(U-2c x tanaj Γ = U 2 (l - 2 0 t a n a ) as the velocity triangles a r e similar for a reaction of 0 .