Mechanism Study Of Film Cooling Based On Tangential Injection

With the rapid development in aviation dynamics, as the device providing power,gas turbine has confront with challenge of higher performance. In order to fulfill highthrust and high efficiency in the design of gas turbine,the promotion of the turbine initialtemperature is inevitable.However,the development of materials technology can notmatch that of promoted turbine initial temperature,blade material can not bear such highturbine initial temperature.In a word,effective cooling technology must be used forretaining normal running and prolong service life of turbine.After the development over70years,cooling technology of turbine has been moremature.As a general cooling method used in turbine blade,research on film coolingbecome a research focus.However,current method of film cooling can not gain coolingeffectiveness without reducing aerodynamic performance, which results of mixingbetween cool air and main stream,impairing cooling effectiveness and aerodynamicperformance.In this paper, a new method of film cooling in tangential jet based on a newstructure will be researched so that aerodynamic performance of original fluid domaincan be reduced at a minimum extent,in the meantime higher cooling effectiveness can beobtained.In order to accomplish the research on new concept of tangential injection, thispaper will carry out research on three aspects.At the beginning,owing to test feasibility ofthe concept of tangential injection,multi-scheme of different angle injection will beresearched.After the comparison of aerodynamic effectiveness,cooling effectiveness andthe distribution of cool air on the blade,the ideal result occur in the30°project with thesituation that the location of changing contour is properly choosed.Then,the research ondifferent structure of cooling hole used in tangential injection is carried out,according tothe result cooling hole with expanding in lateral side is not proper to be used in tangential injection.Finally,the turbulence information in the downstream of cooling hole intangential injection is researched by DES.In this paper,the mission of changing contour for new structure based on tangentialinjection is fulfilled,which depend on self-programme of Matlab with higheffectiveness,at last two projects of changing contour are taken for computation.Themesh used for computation in this paper is all finished by ICEM,which is all structuredgrid with the function of saving computational sources.