Reverse twist designing method of pre-deformation influence of moving blades of marine combustion engine gas compressor

Abstract

The invention belongs to the technical field of gas turbines, in particular to a reverse twist designing method of pre-deformation influence of moving blades of a marine combustion engine gas compressor. The method comprises the following steps: carrying out nonlinear static analysis on original pneumatic designed blade forms under a centrifugal force action so as to acquire initial prediction cold-state blade forms; then carrying out repeated iteration on fluid-solid coupling solution to acquire final transitional heat-state blade forms and corresponding cold-state processing blade forms; carrying out three-dimensional viscous flow field analysis solution on the whole working conditions of the whole gas compressor according to the final heat-state blade forms of the cold-state processingblade forms under different working conditions, and verifying a reverse twist design result. By using twist twist angle numerical values as a convergence condition, based on that, a reverse twist design process of the moving blades of the marine combustion engine gas compressor is built, and the pneumatic performance checking result of the whole gas compressor as a final judgement evidence of thereverse twist design, so that seamless connection between the reverse twist design and gas compressor engineering design is realized, the reverse twist design efficiency is improved, and the reverse twist designing method has an important engineering application values.

Description

Technical field: [0001] The invention belongs to the technical field of gas turbine equipment, and in particular relates to an anti-twist design method considering the influence of pre-deformation of moving blades of gas turbine compressors on ships. Background technique: [0002] The performance of the compressor directly determines the overall performance index of the marine gas turbine. With the continuous development of marine gas turbines, the compressor motor blades now have higher load capacity and tip tangential speed. For this reason, the moving blades of the compressor often adopt a relatively complex three-dimensional space configuration and a thinner blade thickness, which reduces the relative rigidity of the blade, and is prone to large deformation under the combined action of aerodynamic load and centrifugal load. The airfoil shape is the key element to determine the performance of the compressor. Ensuring that the airfoil shape is as close as possible to the ...

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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem of compressor performance attenuation caused by the deformation of the moving blades during the actual operation of the marine gas turbine compressor, and to provide a countermeasure that takes into account the influence of the pre-deformation of the moving blades of the marine gas turbine compressor. Torsion Design Method

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