An Analysis of Flow in Rotating Passage of Large Radial-Inlet Centrifugal Compressor at Tip Speed of 700 Feet Per Second
Abstract
An analysis was made of the flow in the rotating passages of a 48-inch diameter radial-inlet centrifugal impeller at a tip speed of 700 feet per second in order to provide more knowledge on the flow conditions within the impeller. This analysis indicated that the region of low efficiency generally existed along the trailing face as a result of a combination of shifting of low energy air toward the trailing face and losses arising from the decelerations along the trailing face. Because of comparatively large viscous losses along the trailing face, and with unloading of the blades, the velocity at the driving face tip was higher than at the trailing face tip. This velocity difference would be expected to result in mixing losses upon diffusion of the air. The experimental and theoretical distributions of torque on the blades were approximately the same. The theoretically predicted eddy on the driving face was not found experimentally. The modification of the theoretical entrance angle of flow for the first 15 percent of the passage gave fair agreement between the theoretical and experimental static pressures at off-design conditions except for the maximum flow conditions.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1951
- Accession Number
- ADA380470
Entities
People
- Donald J. Michel
- Vasily D. Prian
Organizations
- National Aeronautics and Space Administration