It is difficult to simulate the strong interference and serious flow separation of Fenestron by the CFD method based on the widely used RANS equation,and the detailed experimental data,which could be used to validate ...It is difficult to simulate the strong interference and serious flow separation of Fenestron by the CFD method based on the widely used RANS equation,and the detailed experimental data,which could be used to validate the aerodynamic and noise numerical methods,is unavailable.The experimental investigation on the aerodynamic and noise characteristics of Fenestron is carried out.In view of the complex internal flow field in duct and the relative motion between the stationary duct and the rotating rotor,a comprehensive aerodynamics and pressure measurement scheme is designed based on the bottom support rig.In this measurement scheme,the thrust generated by the rotating rotor can be measured by the rotating shaft balance,the thrusts from Fenestron are measured by the external balance and the pressures on duct inner wall are monitored by a pressure measuring system.To fully capture the noise directionality of Fenestron,a series of noise observers located at an arc array are arranged.In terms of the Fenestron test models,the baseline model,the performance improvement model based on the high-performance tail rotor and the noise reduction model based on the non-uniform blade distribution are designed respectively.By the designed measurement scheme,aerodynamic forces and pressure distributions and noise were measured for the three different Fenestron models.The results show that the aerodynamic thrusts of the tail rotor and duct increase greatly and the noise increases slightly for the performance improvement model because of the larger aerodynamics.The rotor aerodynamic performance of the noise reduction model is reduced,but the modulation effect of the tail rotor improves the forces of the duct.The noise radiated by the noise reduction model is reduced and a good noise reduction result is obtained in frequency domain.展开更多
基金supported by the National Natural Science Foundation of China(No.11872211)the Priority Academic Program Development of Jiangsu Higher Education Institutions,China。
文摘It is difficult to simulate the strong interference and serious flow separation of Fenestron by the CFD method based on the widely used RANS equation,and the detailed experimental data,which could be used to validate the aerodynamic and noise numerical methods,is unavailable.The experimental investigation on the aerodynamic and noise characteristics of Fenestron is carried out.In view of the complex internal flow field in duct and the relative motion between the stationary duct and the rotating rotor,a comprehensive aerodynamics and pressure measurement scheme is designed based on the bottom support rig.In this measurement scheme,the thrust generated by the rotating rotor can be measured by the rotating shaft balance,the thrusts from Fenestron are measured by the external balance and the pressures on duct inner wall are monitored by a pressure measuring system.To fully capture the noise directionality of Fenestron,a series of noise observers located at an arc array are arranged.In terms of the Fenestron test models,the baseline model,the performance improvement model based on the high-performance tail rotor and the noise reduction model based on the non-uniform blade distribution are designed respectively.By the designed measurement scheme,aerodynamic forces and pressure distributions and noise were measured for the three different Fenestron models.The results show that the aerodynamic thrusts of the tail rotor and duct increase greatly and the noise increases slightly for the performance improvement model because of the larger aerodynamics.The rotor aerodynamic performance of the noise reduction model is reduced,but the modulation effect of the tail rotor improves the forces of the duct.The noise radiated by the noise reduction model is reduced and a good noise reduction result is obtained in frequency domain.
