Abstract
The present-day compressors development is a labor-intensive problem, because compressor structure should meet different requirements to the design characteristics. It’s reasonable to find optimal combination of compressor design parameters using the mathematical optimization resources. In this paper the multi-criteria optimization of the rotor and stator blades of the experimental compressor stage NASA Rotor 37 is carried out. The goal of this work is the analysis of different blade parameterization schemes and determination of optimum number of variable parameters for compressor stage aerodynamic characteristics improvement. As an optimization criterions efficiency of compressor stage was used. Flow rate and pressure ratio values should not exceed base values more than ±0.5%. In order to research an effect of the number of variables to the optimization results, the four parameterized models were created. The optimization of the NASA Rotor 37 was carried out using all created parametric models. The models are characterized by number of variables, which describe the blade pressure and suction sides. As a result of optimization the NASA Rotor 37 version was found, which provide the efficiency increasing by approximately 2% while all aerodynamic and requirements are satisfied. It was also found, that increasing of the blade profile number of variables more than 14 is not rational.
Highlights
In the design development of the compressor blade it’s necessary to meet different requirements for the aerodynamic, strength, and mass characteristics of the blade
It is essential to consider the design constraints and processing limits. To solve this problems in this work the unified automated parameterized model is used, which was specially developed for this work
This model allows researching of the blade different parameterization schemes for aerodynamic-optimal design
Summary
In the design development of the compressor blade it’s necessary to meet different requirements for the aerodynamic, strength, and mass characteristics of the blade. It is essential to consider the design constraints and processing limits. To solve this problems in this work the unified automated parameterized model is used, which was specially developed for this work. This model allows researching of the blade different parameterization schemes for aerodynamic-optimal design. For the optimization process researchers have to have parameterized blade models, which include all possible parameters, which describe the structure to be optimized. The geometric model specification and number of optimization parameters are depend on the result of this problem solving: the more number of parameters, the more complicated model
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have