带有加强肋的涡轮机匣排孔冲击连腔结构内部换热特性研究

In order to obtain the heat transfer coefficient distribution data on the internal surface of the turbine casing，transient liquid crystal （TLC）experiments were conducted on the structure of rows of holes impinging continuous cavities with high rib. The effects of jet Reynolds number（Re=5.1×10³~1.1×10⁴），impingement spacing ratio（2.5，5.0，7.5）and axial spacing ratio（4.0，9.0，14.0）on the Nusselt number of the target surface were investigated. The results show that increasing the jet Reynolds number has the most significant improvement on the area-averaged Nu of the target surface. With the increase of the impingement spacing ratio，the averaged heat transfer coefficient decreases monotonically，but this weakening effect is limited to the range of 2D~3D（D represents the diameter of impingement holes）from the stagnation point，and the changes in other regions are not significant. In the local area near the front and rear end walls，the surface Nu increases with the increase of the impingement spacing ratio. The variation of axial spacing ratio has no significant influence on the Nu of the target surface without outlet holes，for the target surface with outlet holes，the heat transfer coefficient will be the best if the axial spacing ratio is 9.0. Comparing with the axial spacing ratio of 4.0 and 14.0 structures，under the condition of Re=5.1×10³，the area-averaged Nu of the structure with an axial spacing ratio of 9.0 on the target surface with outflow holes increases by 5.7% and 8.1% respectively，and the increase is greater with increasing Reynolds number.