New technologies are applied to improve the aerodynamic performance of impulse high pressure turbine stages based on the conventional impulse stage designs. The new three-dimensional stator blade profile, labyrinth brush seal design and optimized reaction degree distribution are used to redesign the conventional impulse three turbine stages for the high pressure cylinder. The aerodynamic characteristics of the redesigned impulse high pressure turbine stages are experimental measured and numerical simulated at different operational speeds. The aerodynamic parameters of the second stage of the impulse three stages for the high pressure turbines are obtained. The obtained results show that the aerodynamic efficiency of the redesigned impulse turbine stages improves compared to the conventional design. The detailed flow fields and corresponding flow mechanisms of the redesigned impulse stages and conventional design for the high pressure cylinder are also analyzed and discussed.
