Abstract
To explore the flow mechanism and improve the performance of supersonic tandem rotor blades, the supersonic rotor Rotor37 is taken as the prototype and redesigned to an original supersonic tandem rotor. Then, based on the Kriging model, the physical programming method, and improved particle swarm optimization algorithm, a multi-objective optimization methodology is developed and applied to achieve the multi-objective optimization of the supersonic tandem rotor blades. Compared with Rotor37, the mass flow and surge margin of the original tandem rotor obviously increased. However, the efficiency of the original tandem rotor was slightly lower than Rotor37. After multi-objective optimization, compared with the original tandem rotor, the total pressure ratio and efficiency of the optimized tandem rotor significantly increased, and the efficiency increased by 1.6%. Further, the surge margin increased by 2.75%. The range and intensity of the high-loss region in the middle section of the optimized tandem rotor significantly decreased, and the range of the low-loss area in the middle region and tip region significantly increased, but the range and strength of the high-loss area in the tip region changed a little. The reason for the decrease of total pressure loss in the middle region and tip region is that the three-dimensional optimization of the blade significantly reduced the shock loss and boundary layer separation loss of the front blade. At the same time, the mixing loss between low energy fluid and the main flow in blade wake also reduced. Besides, the three-dimensional optimization of the blade had little impact on the leakage flow and the secondary flow generated by the mutual interference of the leakage flow and shock wave.
Highlights
The aerodynamic design of modern compressors faces more and more challenges with increasing performance requirements for compressors to realize higher efficiency, higher pressure ratios, and more extensive stability margins
Rotor37 was taken as the prototype, and five configuration parameters about the relative position of the front and rear blade were selected according to the design experience of the supersonic tandem cascade
It can be seen that compared with the front blade of the original tandem rotor, optimization, the turn angleangle of the segment of the front blade hub section after optimization, the turn of rear the rear segment of the front blade hub sectionwas wassmaller, smaller,and andthe the degree of precompression in the front segment of the middle section increased, which reduced the degree of precompression in the front segment of the middle section increased, which reduced the
Summary
The aerodynamic design of modern compressors faces more and more challenges with increasing performance requirements for compressors to realize higher efficiency, higher pressure ratios, and more extensive stability margins. As an effective high-load cascade of compressors, tandem cascades have some excellent performances in higher stage pressure ratios, fewer stages number, and higher stages’. In the 1970s, on its single-stage test rig, Pratt and Whitney carried out experimental studies on tandem blades under transonic and subsonic conditions [4,5,6,7,8]. The results showed that the performance of tandem rotors is not as good as that of conventional rotors under the condition of transonic velocity, but better than that of conventional rotors under the condition of subsonic velocity. Roy and Saha et al [10,11] studied the turning angle and relative position
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
