Abstract
Generalised research results that consider the upgradability of axial and centrifugal gas turbine engine compressors by means of gas-dynamic boundary layer control on bladed disks are demonstrated. Active and passive methods are used. Comparative analysis of the results has been carried out. The analysis is purposed to determine the influence of the flow circulation around the aerofoils on the performance of compressor single-row bladed disks with smooth blades and rough blades and under the condition that vortex generators are installed. An increase in the efficiency of aviation gas-turbine engines and in their gas-dynamic stability margin support leads to the enhancement of the parameters and performance of compressors: increase in loading of aerodynamic bladed disks, improvement of their economical efficiency, improvement of margin of the continuous flow around the compressor grids, etc. Airflow in the compressor grid is characterised by the flow region in the flow core and also by the flow regions in the wall boundary layers on the grid blades where shock waves, vortices, air swirls, and flow separation phenomena take place. The principle objective of the work is to research the possibilities of influence on the parameters of the elements of compressors and overall performance of gas-turbine engines via the methods of active and passive flow regulation. Active flow regulation is realised either by rendering the auxiliary gas mass to the blades boundary layer, or by suction (withdrawal) of the boundary layer (its part) from the surfaces of blades. Passive flow around regulation is characterised by influence on the boundary layer by means of energy redistribution in the flow itself. Santrauka Šiuo tyrimu siekiama nustatyti sparno profilio aptekejimo įtaką vienos eiles menčių kompresoriaus su lygiomis ir šiurkščiomis mentemis darbui, esant įdiegtiems sūkurio generatoriams. Pagrindinis darbo tikslas – ištirti kompresoriaus elementų ir bendro dujų turbininių variklių darbo įtaką parametrams, taikant pasyvų ir aktyvų srauto reguliavimo metodus. Padidinus dujų turbininių variklių našumą ir jų dujų dinamikos stabilumo ribas, pagereja kompresorių darbas ir parametrai: padideja aerodinaminių diskų su mentemis apkrova, jie tampa ekonomiškai našesni, padideja nepertraukiamo srauto riba aplink kompresoriaus plokšteles.
Highlights
Investigation of the aerodynamic performance of compressor grids along with boundary layer control has shown that by affecting the boundary layer the performance of grids can significantly be improved (Kamisti 2000; Schmidt, Mueller 1989; Tereshchenko, Mitrakhovich 1996; Tereshchenko 1979, 1987; Shlikhting 1969; Chzhen 1979) raising the efficiency of the gas-dynamic engine and the aircraft itself (Tishkunov et al 2008)
This work reveals the research results of axial and centrifugal compressor stages, where the extension of non-separated flow range about the bladed disks is provided by the application of passive and active control of the flow about the blades
The flow stability in the compressor single-row vaned diffuser is disturbed when rotational stall arises in the diffuser
Summary
Investigation of the aerodynamic performance of compressor grids along with boundary layer control has shown that by affecting the boundary layer the performance of grids can significantly be improved (Kamisti 2000; Schmidt, Mueller 1989; Tereshchenko, Mitrakhovich 1996; Tereshchenko 1979, 1987; Shlikhting 1969; Chzhen 1979) raising the efficiency of the gas-dynamic engine and the aircraft itself (Tishkunov et al 2008) This allows considering methods of active and passive control of the boundary layer on the surfaces of blades as a means of increasing aerodynamic loads on bladed disks in design modes and extending non-separated flow range in abnormal modes. This work reveals the research results of axial and centrifugal compressor stages, where the extension of non-separated flow range about the bladed disks is provided by the application of passive and active control of the flow about the blades
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