One dimensional approach to predict the performance of high pressure multi-stage axial turbine considering air cooling and diffuser performance

This paper provides an improved 1D mid-span program to quickly grasp the off-design characteristic of modern axial turbines. The improvements are mainly focused on cooling, diffuser and the calculation of choke condition. Disk cooling and blade cooling air mixing are considered in detail. A 1D diffuser model that considers the effects of area change, heat transfer, and friction is added so that a realistic boundary condition at the turbine outlet can be obtained. A choke routine that enables the assessment of choked flow up to limit load conditions is introduced to avoid the shortcoming that the calculation method fails to converge near or at the initial choking mass flow rate. Flexible modules for losses, deviation, and mixing models are built-in to increase the accuracy and versatility of the program. This work is of great value because few programs take cooling and diffuser into account in such detail when calculating turbine performance in the form of maps. The salient issues presented here deal first with the construction of the turbine performance prediction program. The validation of the code is first performed on public data for a five-stage low pressure turbine (LPT). The results show that the efficiency relative errors with the experimental value is in the range of −(0.11%−1.64%), which is within acceptable limits. Then, the performance of GE PG9351FA transonic axial turbine is estimated using this program. This industrial axial turbine is predicted for the first time in a form of turbine performance maps in open literature and the obtained performance map is very useful for the simulation of gas turbine.