| The hovercraft gas turbine air intake system is to ensure that the inlet air satisfies theintake requirements of gas turbines driving the lifting fans and the pneumatic propellers onthe hovercraft; its structure and aerodynamic characteristics directly affect the performance ofthe entire power plant. Compared with displacement vessels, hovercraft gas turbine air intakesystem has characteristics such as smaller size, more complex structure and higher intakeresistance. When the hovercraft travels on land or sea, it would produce large amount ofcontaminant particles which make the working environment of intake system severe.Therefore, it is of significant importance to study the matching intake system.Hovercraft gas turbine intake system is generally comprised of the intake pipe device,intake filtration device and anti-icing device. This paper will take advantage of the numericalsimulation method to investigate the working performance of gas turbine intake system, themain work are as follows:1. Research of hovercraft gas turbine intake system numerical simulation method andmodel simplification method is conducted. A combination of suitable turbulence model andgrid is selected in order to improve the computational accuracy and efficiency of thenumerical simulation. Mirrored feasibility analysis and porous media model is used tosimulate air intake filter through-flow characteristics in order to obtain a simplified model.2. Operating characteristics of the intake system under Maximum ContinuousPower(MCP) working conditions, the seven cases of two identical gas turbines conditions andsix cases of two different gas turbines conditions are investigated. A comprehensive study ofthe hovercraft gas turbine intake system operating conditions is carried out and workingprecautions under practical operation and usage are pointed out.3. Numerical simulation of ninety-six simulation numerical examples which includes allthe combinations of sixteen cases of wind direction and six cases of wind speed. Theinfluence of change of environment wind speed and wind direction on the intake system’sintake air flow rate, intake resistance and the uniformity of compressor’s inlet flow field aremainly investigated from the perspective of numerical analysis.4. Performance of anti-icing device under Maximum Continuous Power(MCP) working condition is studied. Two hot air bleed air gear positions are set; and applicable ambienttemperature range as well as the anti-icing performance of these two gear positions isinvestigated. Variation principle of the original intake system is provided.5. Structural optimization of the intake system is conducted. The design is optimizedbased on the high intake resistance characteristics of the intake system. Using multi-leveloptimization theory and structural optimization software iSIGHT, global optimization of theintake system D-type filter and Z-bend space parameters is achieved. The intake resistance isreduced and optimization purposes are achieved. |
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