Transonic Fan/Compressor Rotor Design Study. Volume 5
Abstract
This volume describes the aerodynamic design details of the Phase IV rotor. The Phase IV rotor as well as the Phase III rotor described in detail in Volume IV of this report, was designed to have a steeper average suction surface angle in the supersonic region ahead of the shock than the baseline rotor. This results in a smaller cascade throat area in the outer 80% of the blade than the baseline rotor. While the throat areas of the Phase III and Phase IV rotors are essentially the same, the Phase IV blade has some what less external compression and some what more internal compression. As a result, the Phase IV blade has less suction surface (and meanline) curvatures in the region of the cascade mouth than does the Phase III rotor. The hub region was kept essentially the same as the baseline rotor. The location of maximum airfoil thickness is 70% of length at the tip and 56% at the hub which is the same as the baseline rotor.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1982
- Accession Number
- ADB069405
Entities
People
- D. E. Parker
- M. R. Simonson
Organizations
- General Electric