Accession Number:

ADA171058

Title:

Investigation of Blade Vibration T55-L-11C Compressor Stages 1 and 2,

Descriptive Note:

Corporate Author:

AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)

Personal Author(s):

Report Date:

1985-09-01

Pagination or Media Count:

29.0

Abstract:

A vibration survey of the first and second stage compressor blades on the T55-L-11C engine was conducted following the manufacturers warning that the proposed fitting of locally designed intake screens might lead to blade vibration problems. Vibration tests and a simple analysis indicated a possible resonance region. Special statistical methods for small samples were used to fully define tolerance limits for this region and establish confidence levels in the limits. Operators were initially advised to restrict operation in the potential resonance region. Subsequent intake flow tests demonstrated that the screens generated no abnormal excitation, so the restrictions could be discontinued. Author

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE