G. M. Popov – Engineer Department of Aircraft Engines, Samara State Aerospace University named after academician S. P. Korolyov (National Research University). E-mail: email@example.com
D. A. Kolmakova – Graduate Department of Aircraft Engines, Samara State Aerospace University, S. P. Korolyov (National Research University). E-mail: firstname.lastname@example.org
M. Yu. Kuprikov – Dr.Sc. (Eng.), Professor, Vice-Rector on Educational Work, Moscow Aviation Institute (National Research University)
D. N. Artemyev – Graduate Department of Aircraft Engines, Samara State Aerospace University, S. P. Korolyov (National Research University)
S. N. Vahneev – Deputy Dean of the Faculty № 9, Moscow Aviation Institute (National Research University)
N. M. Kuprikov – Junior Research Scientist, SEC «FNMST» of Moscow Aviation Institute (National Research University). E-mail: email@example.com
Lapping compressor turbine engine is a complex scientific and engineering problems. Especially important is the process of optimizing the system of collective salvation (SCS), as the use of more advanced compressor will reduce the weight of the aircraft and apply more advanced SCS. In the process optimization solutions in the system designer needs to consider SCS conflicting demands of gas-dynamic efficiency, reliability and lifetime. Typically, the process is iterative: Lapping is the basic design of a particular element, and assesses how this change will affect the efficiency of an engine assembly as a whole. However, in the real world because of the complexity of work processes in compressors GTE track these changes is not easy.
The rapid development of numerical methods to significantly speed up the process of developing and refining units GTE. Modern software CFD-modeling, such as NUMECA and ANSYS CFX, allow the numerical experiment to study the working fluid flow in blade machines. In this case, the gas flow with minimal assumptions described by the Navier-Stokes equations. Thanks to the development of computer technology these calculations occupy a relatively short period of time, which makes possible the use of optimization techniques in finishing compressor turbine engines. Modern methods and optimization programs, such as IOSO, allow the solution of the problem vary hundreds of variables to achieve high performance and reliability of the components of GTE as a whole.
This article provides an experience of the software package to optimize IOSO seven-stage compressor turbine engines. The aim was to improve the optimization of compressor efficiency at cruising through the optimization of geometrical parameters of vanes of the first three stages.
When optimizing HPC solved the following problems:
• calculation model built seven-speed high-pressure compressor;
• conducted research design workflow in HPC for the base model and the model with revised blades on the first three feet;
• The values of the angles of the blades on the adjustable, allowing the compressor to increase efficiency;
• The characteristics of the compressor for the base model and compared with experimental data;
• The characteristics of the compressor for the model with revised blades of the first three stages of the compressor.
Completed work is enabled to determine the optimal values of the angles of the vanes of the first three stages of a multistage compressor, which allowed for a design mode to increase the efficiency of the cascade of 0.3%. This gain in efficiency will allow more sophisticated SCS.