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

Abstract

A vibration survey of the first and second stage compressor blades on the T55-L-11C engine was conducted following the manufacturer's 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)

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1985
Accession Number
ADA171058

Entities

People

  • N. S. Swansson

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Aspect Ratio
  • Bending
  • Compressor Blades
  • Computer Programs
  • Department Of Defense
  • Engineering
  • Foreign Object Damage
  • Frequency
  • Mechanical Engineering
  • Normal Distribution
  • Probability
  • Resonant Frequency
  • Standards
  • Statistical Analysis
  • Test Methods
  • Vibration

Readers

  • Aerospace Engineering
  • Educational Psychology
  • Regression Analysis.