Abstract
The implementation of a three-dimensional viscous inverse design used for an axial compressor is introduced in this paper. The derivation process of the inverse design algorithm is also described in detail. Moreover, an improved blade update method and a modified relaxation factor are included to enhance the inverse design algorithm. The inverse design is built on an in-house inverse design module coupled with commercial Computational Fluid Dynamic (CFD) software NUMECATM. In contrast to analysis design, the pressure loading and the normal thickness distribution along the blade surfaces are prescribed during the process of inverse design. The numerical methods used to solve the flow field are verified using the experimental data of the transonic fan rotor NASA Rotor 67. A recovery test for the Rotor 67 is carried out to validate the developed three-dimensional inverse design tool. To explore the potential application of the inverse design system, it is then used to improve the aerodynamic performance of a transonic fan Rotor 67 and a multi-row compressor Stage 35 at a near peak efficiency point by reorganizing the pressure loading distribution on the blade surfaces.
Highlights
In traditional aerodynamic design methods, the blade profile is constructed according to the designed velocity diagrams, selected incidence angles, and deviation angles predicted by empirical equations
We develop an inverse design method which is built on characteristic propagations and the concept of virtual velocity by imposing the no-slip viscous condition
A three-dimensional inverse design system is implemented by linking the in-house inverse design module with the commercial Computational Fluid Dynamic (CFD) software NUMECATM
Summary
In traditional aerodynamic design methods, the blade profile is constructed according to the designed velocity diagrams, selected incidence angles, and deviation angles predicted by empirical equations. When the inverse design calculation was approaching convergence, the normal velocity on the blade surfaces would disappear and the local pressure loading would tend to the target loading along the blade surfaces On this basis, Qiu proposed an improved inverse design boundary condition which was shown to be more robust, especially in three-dimensional flows [8]. In the work of Van Rooij and Medd, the no-slip condition was included in their original inversed design method to calculate the virtual velocity on the blade surfaces [17] It was made fully consistent with viscous flow modeling and eliminated the difference in boundary conditions between the flow analysis and the inverse design calculation. The peak efficiencies respectively increase from 89.658% to 89.85% in the redesigned Rotor 67 and from 82.749% to 83.011% in the redesigned Stage 35
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.
