Abstract: The first stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and R set forth in Tables I and II, respectively, and second stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values set forth in Tables III and IV, respectively. The X, Y and R values are in millimeters. R represents distances along a radius from an axis of rotation of the turbine. For each airfoil, X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius at each distance R. The profile sections at the R distances for each airfoil are joined smoothly with one another to form the airfoil shape. The airfoil shapes given by the X, Y and R distances lie within envelopes of ±4.064 millimeters in a direction normal to any airfoil surface location therealong.

Abstract: The first stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and R set forth in Tables I and II, respectively, and second stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values set forth in Tables III and IV, respectively. The X, Y and R values are in millimeters. R represents distances along a radius from an axis of rotation of the turbine. For each airfoil, X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius at each distance R. The profile sections at the R distances for each airfoil are joined smoothly with one another to form the airfoil shape. The airfoil shapes given by the X, Y and R distances lie within envelopes of ±4.064 millimeters in a direction normal to any airfoil surface location therealong.

Abstract: The contour and dimensions of the radial-inflow turbine is obtained by an iteration process that includes calculating by use of a three dimensional fluid dynamic flow analysis the parameters that will produce the desired fluid flow velocities, pressures and other aerodynamic properties until the optimum configuration is obtained. The wrap distribution is obtained in accordance with the formulae:When 0.0<X<0.22135: .delta..theta./.delta..theta.(total)=0.0When 0.22135<X<1.00: .delta..theta./.delta..theta.(total)=A+B.times.X+C.times.X.sup.2 +D.times.X.sup.3 +E.times.X.sup.4 +F.times.X.sup.5 =0.0Where:.delta..theta./.delta..theta.(total)=local normalized wrap angleA=0.101596B=-1.007604C=2.672787D=-1.0125510E=0.713005F=-0.469075X=non-dimensional axial chord for a given configurationAdditional reduction in size and inertia is obtained by leaning and contouring the leading edge into an elliptical shape.