Impact of Falling Blocks of High Pressure Turbine Rotor Blades With Squealer Tip on the Aerodynamic Performance and Vibration Characteristics

Abstract

ObjectivesThe operating state under the condition of high-pressure turbine damage will have a certain impact on the performance and vibration of the gas turbine. At present, the means to accurately assess whether the whole machine can continue to be in service was relatively lacking. Therefore, the research on the influence of the tip groove wear and block shedding of the high-pressure turbine rotor blade on the aerodynamic performance and vibration deformation had been carried out.MethodsUsing the three-dimensional numerical simulation method, based on the original tip groove structure of the blade, the influence of five different tip groove damage shapes on typical aerodynamic performance and vibration characteristics of the high pressure turbine was simulated and analyzed.ResultsThe damage of the blade tip groove on the pressure side with falling block, suction side with falling block, trailing edge with falling block, pressure side and trailing edge with falling blocks simultaneous, or pressure side, suction side and trailing edge with falling blocks simultaneous of rotor blades cause an efficiency decrease of 0.44%, 1.6%, 0.03%, 0.67%, and 3.2%, respectively. Different blade squealer tip shapes have a smaller impact on the vibration deformation of the rotor blade, while trailing edge with falling block reduces the deformation of the rotor blade.ConclusionsBased on the analysis results of comprehensive performance and vibration, rotor blades with falling blocks at pressure side, trailing edge, or both can continue to be used. However, it is not recommended to use rotor blades with falling blocks at suction side or pressure side, suction side and trailing edge.

Keywords

• gas turbine
• high pressure turbine
• leakage flow
• numerical simulation
• rotor tip
• vibration response