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To improve the performance of an electric assistant turbocharger in different backpressure environments, the compressor margin needed to be optimized individually. As an effective passive control method to improve the margin, the full-chord-covered pressure side tip winglet has been studied and applied for compressor and turbine rotors. The research on the effect of partial tip winglets, which can reduce added mass of winglet and the weight of the rotor, on the compressor margin has not been found in the available literature. Utilizing numerical simulation, this paper was focused on the research of a high-speed single-rotor compressor which the tip loading coefficient is 0.81. The shape of the pressure side tip winglet is optimized with the margin as the single objective. A database with 189 valid samples was generated using the Latin hypercube method. A self-developed ε-Support vector regression (SVR)-genetic algorithm (GA) optimization platform was applied to optimize the tip shape. The platform obtained a partial pressure side tip winglet shape. Compared with the CFD simulation results, the error of the ε-SVR-GA platform predicted the margin was 4.1%. The result obtained by the ε-SVR-GA platform was improved compared with the prototype margin by 25.36%. INTRODUCTION For the electrification process of vehicle power, regardless of electric vehicle battery technology or fuel cell technology, it is still difficult to compare it to the internal combustion engine in terms of cost control, difficulties with miniaturization, and technical reserve in a short time. Therefore, the development of energy-saving and low emission internal combustion engines to increase the proportion of electrification in the powertrain is still one of the key tasks for automotive power (HU et al. 2019). A serial electric auxiliary turbocharger (EAT) can be a reliable solution for turbo lag, which is caused by the non-instantaneous change of exhaust gas volume and temperature in the starting and transient stages, is mass-produced and equipped with an automotive engine, which is also favored by turbocharger manufacturers, OEM manufacturers and research institutions(Arnold et al. 2001; Katrašnik et al. 2003; Biwersi et al. 2012). Different from the exhaust gas-driven turbocharger, the EAT, which connects directly to the motor, is much more sensitive to the efficiency of the compressor rotor, when this increases, the driven motor output decreases. ZHAO et al. (2012) founded the improvement of the compressor rotor leads to the reduction of the output power demand of the motor. LIU et al. (2009) noticed that the rotational inertia of the compressor rotor limits acceleration ability and the time taken for the rotor to accelerate to the design speed also limits the performance of the EAT regarding the reduction of engine emissions and improvement of vehicle maneuverability. Due to the above problems, the research team proposed the idea of using low pressure ratio, low rotational inertia, and a high efficiency axial flow rotor for the design of an electrically assisted turbocharger rotor. Since the inertia and compressibility of intake gas, the intake gas will produce both inertia and wave effects inside the manifold (SONG et al. 2015). This dynamic effect, which is reflected in the upstream of the EAT, is the compressor rotor outlet pressure periodical change. Due to the limitations of this working environment, the stability margin of the EAT rotor must be optimized. In vehicle engine rooms with limited space, active control methods such as plasma excitation and low energy fluid suction cannot be applied practically. A tip winglet, as a passive control method, can increase the stability margin of the compressor rotor significantly while slightly reducing pressure ratio and efficiency. Studies about compressor tip winglets mostly focus on the action mechanism of tip winglets in plane cascade (HAN et al. 2012; SANG 2017; WU et al. 2017), the different effects of suction side winglets and pressure side winglets (WU 2018), and the influence of varying locations and different maximum widths on the effect of winglet (ZHONG et al. 2016). The design criteria for compressor winglets has not been studied. Different compressor blade tips have different loads, it is

Research on the Effect of Pressure Side Winglet Profile on the Performance of High-Loaded Compressor Rotor