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Turbine for a low cost turbojet engine. 1 : Design and cold-air performance

Author
Kofskey, M. G.
Published
Jun 1, 1974.
Physical Description
1 electronic document
Additional Creators
Roelke, R. J.
Online Version

Availability

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
A 24.70-cm(9.72-in.) tip diameter single-stage, axial-flow turbine was designed for a turbojet engine. Cold-air tests were made over a range of speeds from 30 to 105 percent of design equivalent speed and over a range of total-pressure ratios from 1.30 to 2.66. Results are presented in terms of specific work, torque, mass flow, and efficiency.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19740018139.
Accession ID: 74N26252.
NASA-TN-D-7625.
E-7754.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15744473