Improvement of a preliminary design and optimization program for the evaluation of future aircraft projects

Author(s):  
D. Strohmeyer ◽  
R. Seubert
2018 ◽  
Vol 8 (11) ◽  
pp. 2038 ◽  
Author(s):  
Qing-Hua Deng ◽  
Shuai Shao ◽  
Lei Fu ◽  
Hai-Feng Luan ◽  
Zhen-Ping Feng

An integrated design and optimization approach was developed for radial inflow turbines, which consists of two modules, an automated preliminary design module, and a flexible three-dimensional multidisciplinary optimization module. In this paper, the first module about the automated preliminary design approach was presented in detail and validated by the experimental data. The approach employs a genetic algorithm to explore the design space defined by the loading coefficient, flow coefficient, and rotational speed. The aim is to obtain the best design scheme with high aerodynamic performance under specified constraints and to reduce the dependency on human experiences when designing a radial inflow turbine. The validation results show that the present approach is able to get the optimal design and alleviate the dependence on the designer’s expertise under specified constraints at the preliminary design stage. Furthermore, the optimization results indicate that using the present optimization approach the total-to-static efficiency of the optimized T-100 radial inflow turbine can be increased by 1.0% under design condition and the rotor weight can be decreased by 0.35 kg (26.7%) as compared with that of the original case.


2018 ◽  
Vol 148 ◽  
pp. 1191-1198 ◽  
Author(s):  
Paolo Di Giorgio ◽  
Pasquale Di Trolio ◽  
Elio Jannelli ◽  
Mariagiovanna Minutillo ◽  
Fiorentino Valerio Conte

Author(s):  
Simone Pazzi ◽  
Francesci Martelli ◽  
Vittorio Michelassi ◽  
Marco Giachi

An innovative procedure for the preliminary design and optimization of return channels for centrifugal compressors is explained. A typical configuration of bladed return channel for industrial centrifugal compressors is analyzed by means of a well-known commercial Navier-Stokes solver. A set of geometrical parameters groups is chosen in order to represent the most significant changes in geometry with respect to the base configuration. A series of new return channel configurations is obtained as the result of variations of one or more geometrical parameters. Each geometry obtained with this procedure is analyzed by the flow solver which returns a set of accurately chosen performance indices quantifying aerodynamic losses and distortions at the eye of the downstream impeller. The results thus obtained are used to train a simple one-layer Neural Network (NN) which is afterwards interrogated to compute some performance maps linking the performance indices to the three most relevant geometrical parameters. A further computation is carried out on some return channel configurations which have not been previously analyzed. The results confirm that the interpolator is able to predict the return channels performances with a good accuracy. The resulting performance maps, validated by some random tests, seem to be a valid tool for performance prediction of this kind of return channels.


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