Actions for Performance of 1380 foot per second tip-speed axial-flow compressor rotor blade tip solidity of 1.5.

Email RIS file
Bookmark
Report an Issue

Performance of 1380 foot per second tip-speed axial-flow compressor rotor blade tip solidity of 1.5.

Author
Reid, L.
Published
Jan 1, 1972.
Physical Description
1 electronic document
Additional Creators
Janetzke, D. C. and Ball, C. L.
Online Version

Availability

I Want It
I Want It

Finding items...

Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
This presents the aerodynamic design parameters along with the overall and blade element performance of an axial-flow compressor rotor designed to study the effects of blade solidity on efficiency and stall margin. At design speed the peak efficiency was 0.892 and occurred at an equivalent weight flow of 65.0 lb/sec. The total pressure ratio was 1.83 and the total temperature ratio was 1.215. Design efficiency, weight flow, pressure ratio, and temperature ratio were 0.824, 65.3, 1.65, and 1.187, respectively. Stall margin for design speed was 10 percent based on the weight flow and pressure ratio values at peak efficiency and just prior to stall.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19720007339.
Accession ID: 72N14989.
NASA-TM-X-2379.
E-5723.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15947662