| Abstract | Environmental particles (e.g., sand, volcanic ash and other airborne dust) ingested into a gas turbine engine can significantly reduce engine performance, and even lead to complete power loss. This is particularly true for helicopters during taking-off, hovering, and landing. To predict this degradation quantitatively, a novel particle rebound/deposition model has been developed based on measured particle rebound characteristics and non-dimensional parameter analysis from more than seventy particle deposition tests relevant to engine hot-sections.
The model was calibrated/validated with the experimental data, where sand particles impinged on square ceramic coupons at a velocity of 215 m/s and a temperature range of 1300–1580 K. Numerical simulations were carried out for these testing cases, and the particle impact rate on the coupon for each test case was obtained with a user defined function. With the particle impact rates on the coupon, the experimental particle deposition rates based on the total released particles, and the operating conditions, the coefficient of a defined model formulation was obtained. The calibrated rebound and deposition model was compiled and linked to the flow solver, and the predicted results were in good agreement with the experimental data. With added model functions, the distributions of deposited particle parameters on the coupon surface are provided. |
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