Research and Development Program for Flight Loads Assessment of Engine/Airframe Integration. Phase I

摘要

Obtaining a better understanding of critical turbine engine component behavior under actual flight conditions is essential to the development of improved component design life criteria and proper engine/airframe structural integration. Current airfoil vibratory response measurement techniques preclude obtaining airfoil vibratory data during engine development flight test. To obtain this needed data, this program is directed at developing a prototype flight engine blade vibration measurement system. This system was designed based on the application of noncontacting stationary sensors which will be located in the compressor casing to measure airfoil tip deflections and frequencies. This program consists of two phases. Phase I involves the design and ground test of a breadboard blade vibration measurement system. Phase II will accomplish the preliminary system design and flight application feasibility study. This document presents the interim techncial report of Phase I. Contained herein are explanations of the breadboard system design and the applied mechanics used for blade analyses. (Author)