ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Film cooling with compound angle holes in leading edge of twisted turbine blade
Received date: 2022-11-28
Revised date: 2022-12-13
Accepted date: 2023-02-10
Online published: 2023-02-17
Supported by
National Natural Science Foundation of China(U2241268);Innovation Capability Support Program of Shaanxi Province(2023-CX-TD-19)
An experiment employing Pressure Sensitive Paint （PSP） technique is conducted and the influence of Mass Flow rate Ratio （MFR） and Density Ratio （DR） on the film cooling characteristic of the twisted turbine blade leading edge is analyzed. Numerical simulation is performed to investigate the effect of shaped holes and hole arrangement on the film cooling characteristic of the leading edge. Results show that the variation of MFR has slight effect on film cooling effectiveness of the leading edge. However， the increase of the DR can increase the spanwise average film cooling effectiveness by 30%-60%， which is in good agreement with the numerical results. The improvement of the spanwise average film cooling effectiveness is more than 200% by directly expanding the hole diameter or applying the diffused film cooling hole. The overcooling and film lifting can be avoided at the leading edge with compound angle holes using the asymmetric cross holes arrangement， significantly improving the film cooling effectiveness.
Ming REN , Cunliang LIU , Kun DU , Li ZHANG , Huiren ZHU , Bolun ZHANG . Film cooling with compound angle holes in leading edge of twisted turbine blade[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(18) : 128315 -128315 . DOI: 10.7527/S1000-6893.2023.28315
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