This paper presents the design and verification of the dual-mode core driven fan stage(CDFS)and high-load compressor with a large flow regulation range.In view of the characteristics of large flow regulation range of ...This paper presents the design and verification of the dual-mode core driven fan stage(CDFS)and high-load compressor with a large flow regulation range.In view of the characteristics of large flow regulation range of the two modes and high average stage load coefficient,this paper investigates the design technology of the dual-mode high-efficiency compressor with a large flow regulation range and high-load compressor with an average stage load coefficient of 0.504.Building upon this research,the design of the dual-mode CDFS and four-stage compressor is completed,and three-dimensional numerical simulation of the two modes is carried out.Finally,performance experiment is conducted to verify the result of three-dimensional numerical simulation.The experiment results show that the compressor performance is improved for the whole working conditions by using the new design method,which realizes the complete fusion design of the CDFS and high-pressure compressor(HPC).The matching mechanism of stage characteristics of single and double bypass modes and the variation rule of different adjustment angles on performance are studied comprehensively.Furthermore,it effectively reduces the length and weight of compressor,and breaks through the key technologies such as high-load compressor with the average load factor of 0.504.These findings provide valuable data and a methodological foundation for the development of the next generation aeroengine.展开更多
A series of experiments and numerical simulations are carried out in a high-speed axial compressor to systematically investigate the influence and underlying flow mechanisms of micro tip injection on enhancing compres...A series of experiments and numerical simulations are carried out in a high-speed axial compressor to systematically investigate the influence and underlying flow mechanisms of micro tip injection on enhancing compressor stability.Different geometric structures of micro tip injection have been investigated,including the axial positions of injector port,injected mass flow rate and injector diameter.First,seven designed micro tip injection structures and one solid wall casing are tested in the compressor test rig to elucidate the influence of different micro tip injection parameters on the compressor stability.Then,numerical simulations are conducted to analyze the underlying flow mechanisms of micro tip injection with different design parameters on enhancing the compressor stability.The experimental and numerical investigation reveal that when the injection port is located upstream of the low-speed region,the compressor stability is significantly enhanced.The tip injection with larger injected mass flow can obtain higher stall margin improvement.Smaller injector diameter produces higher injection momentum and velocity,contributing to greater improvement on the compressor stability.展开更多
当风机进出口连接长管道时,其外部辐射噪声主要是内部非定常流动诱发蜗壳振动产生的振动噪声。风机壳体的振动噪声是典型的流固干涉噪声,通常基于非定常流场获得振动激励源。为了控制此类噪声,通过振动噪声数值计算方法,并结合试验设计...当风机进出口连接长管道时,其外部辐射噪声主要是内部非定常流动诱发蜗壳振动产生的振动噪声。风机壳体的振动噪声是典型的流固干涉噪声,通常基于非定常流场获得振动激励源。为了控制此类噪声,通过振动噪声数值计算方法,并结合试验设计方法(Design of Experiment, DOE),给出了一种以壳体各板块厚度(前板TF,侧板TS,后板TB)为设计变量、以壳体振动辐射声功率为目标函数的单目标优化方法。研究表明,当保持壳体质量不变时,优化后,壳体表面辐射声功率均有不同程度降低,壳体表面基频辐射声功率降幅最大,达到6.23 dB。展开更多
文摘This paper presents the design and verification of the dual-mode core driven fan stage(CDFS)and high-load compressor with a large flow regulation range.In view of the characteristics of large flow regulation range of the two modes and high average stage load coefficient,this paper investigates the design technology of the dual-mode high-efficiency compressor with a large flow regulation range and high-load compressor with an average stage load coefficient of 0.504.Building upon this research,the design of the dual-mode CDFS and four-stage compressor is completed,and three-dimensional numerical simulation of the two modes is carried out.Finally,performance experiment is conducted to verify the result of three-dimensional numerical simulation.The experiment results show that the compressor performance is improved for the whole working conditions by using the new design method,which realizes the complete fusion design of the CDFS and high-pressure compressor(HPC).The matching mechanism of stage characteristics of single and double bypass modes and the variation rule of different adjustment angles on performance are studied comprehensively.Furthermore,it effectively reduces the length and weight of compressor,and breaks through the key technologies such as high-load compressor with the average load factor of 0.504.These findings provide valuable data and a methodological foundation for the development of the next generation aeroengine.
基金supported by National Natural Science Foundation of China(No.52076179)National Science and Technology Major Projects of China(No.J2019-I-0011).
文摘A series of experiments and numerical simulations are carried out in a high-speed axial compressor to systematically investigate the influence and underlying flow mechanisms of micro tip injection on enhancing compressor stability.Different geometric structures of micro tip injection have been investigated,including the axial positions of injector port,injected mass flow rate and injector diameter.First,seven designed micro tip injection structures and one solid wall casing are tested in the compressor test rig to elucidate the influence of different micro tip injection parameters on the compressor stability.Then,numerical simulations are conducted to analyze the underlying flow mechanisms of micro tip injection with different design parameters on enhancing the compressor stability.The experimental and numerical investigation reveal that when the injection port is located upstream of the low-speed region,the compressor stability is significantly enhanced.The tip injection with larger injected mass flow can obtain higher stall margin improvement.Smaller injector diameter produces higher injection momentum and velocity,contributing to greater improvement on the compressor stability.
文摘当风机进出口连接长管道时,其外部辐射噪声主要是内部非定常流动诱发蜗壳振动产生的振动噪声。风机壳体的振动噪声是典型的流固干涉噪声,通常基于非定常流场获得振动激励源。为了控制此类噪声,通过振动噪声数值计算方法,并结合试验设计方法(Design of Experiment, DOE),给出了一种以壳体各板块厚度(前板TF,侧板TS,后板TB)为设计变量、以壳体振动辐射声功率为目标函数的单目标优化方法。研究表明,当保持壳体质量不变时,优化后,壳体表面辐射声功率均有不同程度降低,壳体表面基频辐射声功率降幅最大,达到6.23 dB。
