Abstract
The radial equilibrium of pseudo-axisymmetric flows in supersonic rotors which have no normal shock was considered and two examples were calculated with the following results.[1] The supersonic rotor blades which have flows with no turning and satisfying radial equilibrium conditions in the entire passages get thicker at the tip radius than at the hub.[2] If the deceleration combined with the appropriate turning through the supersonic rotor passage are taken into consideration, the constant absolute total pressure may be expected at the exit.The flow condition for which the radial equilibrium relations could be satisfied both before and behind the normal shock was described. An expression to establish the above was written by using three basic variables, which are the relative Mach number, the rotational Mach number of rotor (the ratio of rotational speed of rotor to sound velocity) and the relative flow angle, before the normal shock. In order to solve the equation, two variables or two equivalent conditions must be specified. The approach in this report seems to be useful in designing the rotor passage containing the normal shock.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
