NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Effect of damper on overall and blade-element performance of a compressor rotor having a tip speed of 1151 feet per second and an aspect ratio of 3.6The overall and blade-element performance of two configurations of a moderately high aspect ratio transonic compressor rotor are presented. The subject rotor has conventional blade dampers. The performance is compared with a rotor utilizing dual wire friction dampers. At design speed the subject achieved a pressure ratio of 1.52 and efficiency of 0.89 at a near design weight flow of 72.1 pounds per second. The rotor with wire dampers gave consistently higher pressure ratios at each speed, but efficiencies for the two rotors were about the same. Stall margin for the subject rotor was 20.4 percent, but for the wire damped rotor only 4.0 percent.
Document ID
19740018135
Document Type
Technical Memorandum (TM)
Authors
Lewis, G. W.
(NASA Lewis Research Center Cleveland, OH, United States)
Hager, R. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-3041
E-7068
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

NameType 19740018135.pdf STI
No Preview Available