Abstract
The article suggests the installation and methods of static tests for the limit working and fracture loads of acoustic panels of aircraft gas-turbine engines (GTE). It is not possible to perform the full scope of static tests on the engine as it is technically impossible to obtain the airflow pressures required by airworthiness standards. The required pressure in the proposed installation is created by the punch, which is the same shape as the panel to be tested. Flexible rubber sheets are used to equalize contact pressure on the panel surface. The similarity in the distribution of pressures on the surface of the acoustic panel created by the air flow as part of the GTE and the pressures created by the punch as part of the installation is confirmed by comparing the stresses and deformations obtained as a result of finite-element calculations. The article presents the results of certification static tests and flaw detection of a three-layer acoustic panel. Comparison of the results of finite-element calculations of stresses and displacements of the acoustic panel as a part of GTE and as a part of the installation has shown that in the latter case the estimations of static strength are conservative, which positively affects their safe operation.
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