DMCA
Damage Propagation Modeling for Aircraft Engine Run-to-Failure Simulation (2008)
| Citations: | 30 - 2 self |
BibTeX
@MISC{Saxena08damagepropagation,
author = {Abhinav Saxena and et al.},
title = {Damage Propagation Modeling for Aircraft Engine Run-to-Failure Simulation},
year = {2008}
}
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Abstract
This paper describes how damage propagation can be modeled within the modules of aircraft gas turbine engines. To that end, response surfaces of all sensors are generated via a thermo-dynamical simulation model for the engine as a function of variations of flow and efficiency of the modules of interest. An exponential rate of change for flow and efficiency loss was imposed for each data set, starting at a randomly chosen initial deterioration set point. The rate of change of the flow and efficiency denotes an otherwise unspecified fault with increasingly worsening effect. The rates of change of the faults were constrained to an upper threshold but were otherwise chosen randomly. Damage propagation was allowed to continue until a failure criterion was reached. A health index was defined as the minimum of several superimposed operational margins at any given time instant
Keyphrases
aircraft engine run-to-failure simulation damage propagation modeling time instant failure criterion unspecified fault operational margin exponential rate health index data set upper threshold efficiency loss thermo-dynamical simulation model damage propagation initial deterioration response surface aircraft gas turbine engine
