Enhancement of Efficiency of Operation of High-Speed Aircraft Engine Elements by Means of Separation Flow Controlling

摘要

Results of investigations of the mechanism of appearance and destruction of separation zones in supersonic gas flows are presented. Methods for controlling separation phenomena were developed to increase the operation efficiency of ducts combustors inlets and outlets of high-speed aircrafts. The main trends of investigations were: 1) Study of deceleration flows in ducts of various shapes with pseudoshock; 2) Development of non-traditional manners of spatial implementation of combustion in supersonic flows; 3) Computational analysis of optimum methods of energy supply in internal flows with separation zones; 4) Control of separation phenomena for increasing efficiency of power plant outlets. The following major results were obtained: For 1st trend: Features of the structure of the non-steady separation in the ducts with deceleration of the supersonic flow in the pseudoshock were determined. Methods for controlling the pseudoshock were developed. Conditions for forming separation zones under interference of various shear layers (vortex jet) generated ahead of the entrance and in ducts with the pseudoshock were studied. For 2nd trend: For the first time in the world practice the gasdynamic stabilizers of combustion were developed. Their principle of operation was based on artificial generation of free-hanging separation zones in the supersonic flow. Successful experimental try-out of some schemes of gasdynamic stabilizers was carried out at the TsAGI's hypersonic test rig T-131 at M=2.5 - 2.6. They permitted to obtain self-ignition and stable combustion of hydrogen:.