Axisymmetric Supersonic Flow in Rotating Impellers
Abstract
General equations are developed for isentropic, frictionless, axisymmetric flow in rotating impellers with blade thickness taken into account and with blade forces eliminated in favor of the blade-surface function. It is shown that the total energy of the gas relative to the rotating coordinate system is dependent on the stream function only, and that, if the flow upstream of the impeller is vortex-free, a velocity-potential function of only the radial and axial distances exists in the impeller. The characteristic equations for supersonic flow are developed and used to investigate flows in several configurations in order to ascertain the effect of variations of the boundary conditions on the internal flow and the work input. Conditions varied are prerotation of the gas, blade turning rate; gas velocity at the blade tips, blade thickness, and sweep of the leading edge.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1951
- Accession Number
- ADA382494
Entities
People
- Aruthur W. Goldstein
Organizations
- National Aeronautics and Space Administration