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Effect of a reduction in blade thickness on performance of a single-stage 20.32-centimeter mean-diameter turbine / by William J. Nusbaum and Milton G. Kofskey.
- Format:
- Book
- Government document
- Author/Creator:
- Nusbaum, William J., author.
- Kofskey, Milton G., author.
- Series:
- NASA technical note ; D-7128.
- NASA/TN ; D-7128
- Language:
- English
- Subjects (All):
- Gas-turbines--Blades.
- Gas-turbines.
- Gas-turbines--Aerodynamics.
- Physical Description:
- 1 online resource (24 pages) : illustrations.
- Place of Publication:
- Washington, D.C. : National Aeronautics and Space Administration, February 1973.
- Summary:
- As part of a program to reduce the manufacturing costs of a small gas-turbine engine, the turbine blading was reduced in thickness to facilitate coining. Tests were made to determine the effect of this modification on turbine performance. The working fluid was air at nominal inlet total conditions of 535 deg F and 20.0 psia. Performance results are presented and compared for four stator-rotor combinations in terms of equivalent torque, mass flow, and efficiency at equivalent design speed and at inlet-total to exit-static pressure ratios of 1.8 to 3.8.
- Notes:
- "February 1973."
- Includes bibliographical references (page 11).
- Description based on online resource, PDF version; title from title page (NASA, viewed on July 2, 2021).
- Electronic reproduction. [Place of publication not identified]: HathiTrust Digital Library. 2024.
- OCLC:
- 23677387
- Access Restriction:
- Use copy Restrictions unspecified
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