Parametric Three Dimensional Model of the Small-Sized Gas Turbine Engine Centrifugal Compressor Impeller

Aeronautical and Space-Rocket Engineering


Аuthors

Danilov M. A.*, Besshapov P. P.**

Central Institute of Aviation Motors named after P.I. Baranov, Moscow, Russia

*e-mail: madanilov@ciam.ru
**e-mail: ppbesshapov@ciam.ru

Abstract

The authors developed an automated three-dimensional parametric model of a centrifugal compressor impeller. The said model converts the initial design data into the geometric parameters required to elaborate a three-dimensional model of the impeller blade.
To enhance stability, the model employs self-diagnostic tools both at the stage of the solid model parameters forming and during its modeling, automatically adjusting them to the acceptable values. 
The design process automation allows significant reduction in the labor intensity of the computational and design-technological models forming as well as reduce the number of errors in the data transfer through the single parametric model application. The existing parametric three-dimensional models of centrifugal compressors are characterized by the possibility of model “degeneracy” due to the parameters unacceptable combinations/values selection.
With a view to the above said, it is advisable to develop a specialized model while the centrifugal compressor impeller designing. This model should ensure:
- the “degeneracy” nonexistence in the maximally wide range of the acceptable parameters values (the variety of shapes of the object being modeled);
- scaling convenience of the shaped-up structure, allowing herewith performing maximally independent sub-models correction from the viewpoint of various disciplines.
The parametric three-dimensional model was being elaborated as an integral part of the automated design and computing complex for the centrifugal compressor characteristics. It includes a design model of the entire impeller, a disc sector with one blade, and blades with the adapted surface topology for building finite element computational models.
The model is being formed based on the nine blade and a single disc groups of parameters, which contain 50 parameters in the aggregate. Parameters division into the groups allows limiting the scroll of variable parameters according to the design stage or the discipline of follow-up and analysis.
At the initial data receiving, the model generates an initial list of all parameters necessary for the model development, with the possibility of correction by the designer according to the described parameterization schemes. The presented parameterization schemes are potentially applicable to centrifugal turbines as well.
The model demonstrates acceptable stability and is of a wide range of both impellers and blade shapes configurations. The model was tested both in the design of new centrifugal compressor impeller and for the parameters list selection for the existing prototype for parameterization while the development of prospective small-sized gas turbine engines at the Central Institute of Aviation Motors named after P.I. Baranov. The developed model application as part of automated design and computational systems significantly reduces labor intensity of the centrifugal compressors developing and modernizing, and link-up of the automatic optimization systems additionally ensures the opportunity to significantly increase the aerodynamic efficiency and improve mass characteristics while maintaining the required strength of blade machines.

Keywords:

centrifugal compressor impeller, automated three-dimensional parametric model

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