Abstract
Abstract Multidisciplinary design optimization of transonic rotors, especially focusing on improving the aeroacoustic performance, has received little attention. This article employs an automatic design optimization approach to reduce the shock-associated tone noise and to increase the adiabatic efficiency of NASA rotor 37. An evolutionary algorithm for multi-objective trade-offs searching is used to obtain the noise-efficiency Pareto front. Three-dimensional Reynolds-averaged Navier–Stokes simulations are directly applied in the optimization loop for aeroacoustic and aerodynamic analysis. Significant noise reduction and efficiency increase have been achieved. Two optimized designs corresponding to the endpoints of the Pareto front have been analyzed comprehensively from the perspectives of rotor characteristics, noise performance, and flow and acoustic fields, to understand the mechanisms responsible for performance improvements.
Highlights
On the route to environmentally friendly and climate neutral transport systems, a continued effort in optimisation of aircraft engines is required for a further reduction of carbon-dioxide and noise emissions of the aviation sector
The demands of high pressure ratio and high efficiency are consistently increasing for lighter weight and better fuel economy
A total power level (PWL) reduction of 3.5dB has been obtained for the “noise-optimal” design of the present optimisation, accompanied by a 1.5% relative decrease of the pressure ratio and a 1.1% relative decrease of the mass flow
Summary
On the route to environmentally friendly and climate neutral transport systems, a continued effort in optimisation of aircraft engines is required for a further reduction of carbon-dioxide and noise emissions of the aviation sector. Reducing the environmental footprint of aviation remains an essential target for aircraft engine manufacturers, . With all the achieved noise reductions over the past decades in modern high bypass ratio turbofan engines, the fan noise remains to have a major contribution to the overall engine noise at all operating conditions. There is a growing requirement to reduce the source level of the fan noise during the blade design phase. The demands of high pressure ratio and high efficiency are consistently increasing for lighter weight and better fuel economy
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.
