A Reduced-Order Model for Transient Analysis of Bladed Disk Forced Response

[+] Author and Article Information
J. P. Ayers, D. M. Feiner, J. H. Griffin

Deppartment of Mechanical Engineering,  Carnegie Mellon University, 5000 Forbes Avenue, Pittsburgh, PA 15213

An eigenvalue is equal to the square of the natural frequency of a mode.

J. Turbomach 128(3), 466-473 (Feb 01, 2005) (8 pages) doi:10.1115/1.2185675 History: Received October 01, 2004; Revised February 01, 2005

A method for predicting the vibratory response of bladed disks under high engine acceleration rates is developed. The method is based on the Fundamental Mistuning Model, an existing reduced order model for predicting the steady-state vibratory response. In addition, a criterion is developed for a critical engine acceleration rate, above which transient effects play a large role in the response. It is shown that military engines operate at acceleration rates above this critical value and therefore transient effects are important in practice.

Copyright © 2006 by American Society of Mechanical Engineers
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Figure 4

Example of modal response used to calculate damping

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Figure 5

Time response from single blade test case, with overlaid response envelope

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Figure 6

Comparison of measurement with simulation for single blade

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Figure 7

Comparison of measurement with simulation for two representative blades from 18 blade test case

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Figure 8

Comparison of actual and perturbed steady-state response for 18 blade test case

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Figure 9

Comparison of measured, simulated, and perturbed response for two representative modes from the 18 blade test case

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Figure 10

Comparison of measured, simulated, and perturbed response for a representative blade from the 18 blade test case

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Figure 11

Expanded view of a 1–2s region of Fig. 1

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Figure 12

Comparison of steady-state and transient response for a representative mode at critical acceleration rate

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Figure 13

Transient behavior with realistic acceleration rate and damping level

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Figure 14

Square wave excitation

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Figure 15

Comparison of response to sine wave and square wave inputs

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Figure 1

Transient response from NASA spin pit test

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Figure 2

Single blade rotor

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Figure 3

Eighteen blade rotor



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