The inlet fogging effects on the stable range of a NASA transonic compressor stage, Stage 35, are numerically simulated and analyzed in this paper. The 3-D two-phase flow fields in the compressor stage are investigated under different operating flow conditions with varying levels of the injected water flow rates and the fogging droplets sizes. The special attention is given to the stall and the choking operating points to investigate changes in the stable operating range of the compressor stage as a result of different wet compression conditions. The preliminary results indicate that the inlet fogging has different effects on either the stall and/or the choking range. The change in the stable range of this transonic compressor stage depends on the fogging flowrate and droplets diameters.
- International Gas Turbine Institute
The Numerical Simulation of Inlet Fogging Effects on the Stable Range of a Transonic Compressor Stage
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Luo, M, Zheng, Q, Sun, L, Deng, Q, Li, S, Liu, C, & Bhargava, RK. "The Numerical Simulation of Inlet Fogging Effects on the Stable Range of a Transonic Compressor Stage." Proceedings of the ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. Volume 4: Cycle Innovations; Fans and Blowers; Industrial and Cogeneration; Manufacturing Materials and Metallurgy; Marine; Oil and Gas Applications. Vancouver, British Columbia, Canada. June 6–10, 2011. pp. 609-630. ASME. https://doi.org/10.1115/GT2011-46124
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