Reynolds Number Effects on the Performance of a Turbofan Engine PUBLIC ACCESS

[+] Author Affiliations
Masao Kozu

Japan Defence Agency

Satoshi Yashima

Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan

Paper No. 89-GT-199, pp. V002T02A003; 7 pages
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7914-6
  • Copyright © 1989 by ASME


Reynolds Number effects on the matching performance of a small twin-spool turbofan engine were investigated through the altitude tests of the F3-30 engine which was developed to power the Japan Air Self Defence Force’s T-4 intermediate trainer.

Analyzing the test results made it clear that the change of the aerodynamic characteristics of the low pressure turbine due to Reynolds Number effects is as significant as these of fan and compressor, and it caused the difference between the predicted and measured engine performance at high altitudes.

Correlation factors on the Reynolds Number for each of the component characteristics (pressure ratio, airflow and efficiency of fan and compressor, and gas flow and efficiency of low pressure turbine) were obtained, and simulation of the engine performance using these factors coincided well with the test data which were obtained from the altitude tests of the F3-30 at Arnold Engineering Development Center of U. S. Air Force.

Copyright © 1989 by ASME
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