Research on the influence of the combination of hole shape and Hole compound angle on the temperature field of the actual turbine rotor blade

Using conjugate heat transfer methods, the effects of the combination of hole shapes and hole compound angles on the temperature field of actual turbine blades were studied. Four-hole shapes and three-hole compound angles were set on the GE-E3 1st turbine blades. The results show that changes in compound angles have different effects on blade temperature in different hole shapes, exhibiting distinct characteristics. For the cylinder hole configuration, regardless of whether it is the suction surface or the pressure surface, the compound angle of -45° case has the lowest regional average temperature, with a maximum decrease of 18.7 K. In the console hole configuration, the selection of the hole compound angle needs to consider the mainstream velocity components. This is mainly because in the console hole configuration, the coolant velocity is faster, and when the coolant's spanwise velocity component is aligned with the mainstream, it reduces the lift of the cooling air. For fan-shaped hole configuration, the case with a compound angle of -45° demonstrates the strongest ability to reduce wall temperature on both the suction surface and pressure surface, with a maximum reduction of 52 K. This is primarily because, in the -45° compound angle case, the coolant not only flows out along the hole but also a small portion flows out from the upper part of the hole, resulting in a larger overall coverage area. For the 7-7-7 shaped hole configuration, the overall trend is similar to that of the fan-shaped hole, especially on the pressure surface, where the -45° compound angle case also shows the strongest ability to reduce wall temperature, achieving a reduction of 44.7 K.