Investigating a New Method-Based Internal Joint Operation Law for Optimizing the Performance of a Turbocharger Compressor

Abstract

A well-matched relationship between the compressor and turbine plays an important role in improving turbocharger and engine performance. However, in the matching of turbocharger and engine, the internal operation relationship between compressor and turbine is not considered comprehensively. In order to fill this gap, this paper proposed the internal joint operation law (IJOL) method based on the internal operating characteristics of the compressor and turbine using a combination of experimental and simulation methods. On this basis, the optimization method of the compressor was proposed. Firstly, according to the basic conditions of turbocharger, the compressor power consumption and the turbine effective power at a fixed speed were solved. Secondly, the power consumption curve of the compressor and the effective power curve of the turbine were coupled to obtain the power balance point of the turbocharger. Then, the internal joint operating point was solved and coupled to obtain the IJOL method. Finally, the IJOL method was used to optimize the blade number and the blade tip profile of the compressor. The simulation results showed that for the blade number, the 8-blade compressor had the best overall performance. For the blade tip profile, compared with the original compressor, the surge performance of the impeller inlet diameter reduced by 3.12% was better than that of the original compressor. In addition, in order to compare this to engine performance with different compressor structures, a 1D engine model was constructed using GT-Power. The simulation results showed that the maximum torque of the engine corresponding to the impeller designed by the IJOL method was 4.2% higher than that of the original engine, and the minimum brake specific fuel consumption was 3.1% lower. Therefore, compared with the traditional method, the IJOL method was reasonable and practical.

An Explainable Prediction Model for Aerodynamic Noise of an Engine Turbocharger Compressor Using an Ensemble Learning and Shapley Additive Explanations Approach

“…In the compressor noise experimental system, the PCB-SN152495 type microphone was used to measure the sound pressure level (SPL) of aerodynamic noise, the PCB-HT356B21 type vibration sensor was used to test the vibration acceleration on the surface of the compressor worm shell and the SPL and vibration signals were collected and analyzed by the SIEMENS signal acquisition method. A detailed description of turbocharger test bench can be found in the literature [39,40], and the turbocharger test bench and aerodynamic noise test instruments are shown in Table 1. As can be seen from Table 1, the turbocharger performance and noise test rig consisted of four parts, which were the compressor section, turbine section, intake and exhaust piping and components, and noise test section, respectively.…”

Experimental and Mechanism Study of Aerodynamic Noise Emission Characteristics from a Turbocharger Compressor of Heavy-Duty Diesel Engine Based on Full Operating Range

“…At low speeds, the experimental values matched well with the simulated values.For the pressure ratio and efficiency, the maximum errors were 4.89% and 3.92%, respectively, occurring at the 110,000 r/min speed line. This difference was attributed to the simplification of geometry's secondary features, the simulation's heat transfer parameter settings, and manufacturing errors[35][36][37].…”