This paper presents the application of a viscous adjoint method to the multipoint design optimization of a rotor blade through blade profiling. The adjoint method requires about twice the computational effort of the flow solution to obtain the complete gradient information at each operating condition, regardless of the number of design parameters. NASA Rotor 67 is redesigned through blade profiling. A single point design optimization is first performed to verify the effectiveness and feasibility of the optimization method. Then in order to improve the performance for a wide range of operating conditions, the blade is redesigned at three operating conditions: near peak efficiency, near stall, and near choke. Entropy production through the blade row combined with the constraints of mass flow rate and total pressure ratio is used as the objective function. The design results are presented in detail and the effects of blade profiling on performance improvement and shock/tip-leakage interaction are examined.
Multipoint Design Optimization of a Transonic Compressor Blade by Using an Adjoint Method
University of California,
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received May 29, 2013; final manuscript received July 7, 2013; published online September 27, 2013. Editor: Ronald Bunker.
- Views Icon Views
- Share Icon Share
- Cite Icon Cite
- Search Site
Luo, J., Zhou, C., and Liu, F. (September 27, 2013). "Multipoint Design Optimization of a Transonic Compressor Blade by Using an Adjoint Method." ASME. J. Turbomach. May 2014; 136(5): 051005. https://doi.org/10.1115/1.4025164
Download citation file:
- Ris (Zotero)
- Reference Manager