Design And Optimization Of Adding A Stage For The Multistage Axial Compressor

With the development of science and technology,maritime traffic and transportation are more demanding on power economy and marine gas turbines need higher propulsion power.Therefore,the design of large-flow and high-pressure ratio compressors is becoming more and more urgent.However,there are many high-performance compressors that are still unable to meet new demands.Compressors based on sophisticated compressors that increase mass flow or increase pressure ratio through adding front stage design to meet new requirements can dramatically reduce design cycles and design costs.In this paper,the design method of pre-boost design for transonic compressor is mainly proposed and a multi-stage pre-compressor design scheme to meet the requirements of new gas turbine is proposed.The design and research process of this paper is mainly based on the automatic pneumatic design platform of Harbin Engineering University,which mainly includes three-dimensional simulation process of one-dimensional calculation,two-dimensional calculation,three-dimensional blade modeling and numerical simulation by commercial software.Firstly,by analyzing the results of one-dimensional characteristic calculation,the matching principle of pre-zeroing stage with the original compressor is discussed,and the constraints of the structure constraints are considered.Based on this,the twisting design rules of the transonic zero stage is studied by the adjusting the inlet pre whirl angle to adapt the load distribution of long blade.The transonic leaf design is generated by self-programming and the camber line is defined by a polynomial curve.In order to meet the design requirements,the transonic zero stage compressor needs to be optimized.By studying the influence of twisting rules and blade aspect ratio on the zero stage performance and overall performance,the optimal aspect ratio and twisting rules are selected.One variable inlet vane and four variable stators are designed to fit the change of flow flied at off-design condition of new compressor and the variable stator schedule is also discussed.The design results of the whole compressor after adding stage design are obtained by multistage CFD.The results show that the adding stage design method can meet the compressor performance requirements.After adding stage,the new multi-stage axial compressor design point flow increased by 21.4%,pressure ratio increased by 18.23%,and the isentropic efficiency reached 89.06% which higher 0.13% than the old compressor,the new compressor full condition surge margin is not less than 10%.