Aerodynamic Design Of A Marine Compressor Operating In An Intercooled Cycle

As a kind of propulsion power plant for naval vessels,gas turbines have gained a wide application.The development of heavy-duty(over 30000 HP)gas turbines constitutes the main trend of gas turbines for use on board the naval vessels in various countries.To adopt a complex cycle and achieve an ever better performance through an improvement of the cycle is one of measures for enhancement of the performance of marine gas turbines.The gas turbines operating in the intercooled cycle form a new type of cycle for marine gas turbines,which is proposed on the basis of the research on intercooled recuperative cycles.They are unprecedented for the vessels of any country in the world.The authors have made a study of relevant aerodynamic design and research work necessary for the LP compressor of a type of gas turbine after the adoption of the ICR(intercooled recuperative)cycle.First,the specific features of the cycle in question were explored and investigated and its modeling analyzed.Moreover,a theoretical analysis has also been performed of the reduction in power consumption after the compressors have adopted the cycle in question.Secondly,a design of the LP compressor minus two stages was performed on the basis of an optimization design.As a result,a total of two schemes were proposed,i.e.the rotating blades additionally installed with outlet guide vanes(a single blade row)and both the rotating blades and guide vanes additionally installed with outlet guide vanes(two blade rows).Furthermore,the outlet guide vanes were designed in accordance with the corresponding schemes.With a consideration of the blades of the prototype machine adopting the original blade profile BC series,the blade modeling and design of the outlet guide vanes were performed by using BC6 original profile data with the conventional method being adopted.Subsequently,on the basis of the one-dimensional and three-dimensional analysis results.The results show that the blades designed by using the conventional method can meet the requirement for the aerodynamic performance.A comparison of the two schemes shows that the scheme of a single blade row has a slightly higher thermal efficiency than that of two blade rows.Therefore,the former shall be highly recommended.