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Effect of Endwall Contouring on the Performance of a Three-Stage HP Turbine
This paper describes experimental investigations of a three - stage high pressure research turbine at various operating conditions. The experimental investigation is carried out in a three - stage turbine facility at the Turbomachinery Performance and Flow Research Laboratory (TPFL) at Texas A&M University. Its rotor includes non - axisymmetric endwall contouring on the first and second rotor row. Experimental data were obtained using interstage aerodynamic measurements at three measurement stations, namely, downstream of the first rotor row, the second stator row and the second rotor row. Measurements were conducted using five - hole probes traversed in both circumferential and radia l directions to create a measurement window. Performance measurements were carried out within a rotational speed range of 1800 to 3000 RPM. Interstage measurements were obtained at 300 0 rpm. Moreover, the impact of the purge flow injection on the aerodynamic and performance behaviour of the turbine for five coolant - to - mainstream mass flow ratios of 0.0%, 0.5%, 1.0% , 1.5% and 2.0% were investigated. Interstage results exhibit the evidence of the mitigation of secondary flow intensity due to endwall contouring
Effect of Endwall Contouring on the Performance of a Three-Stage HP Turbine
This paper describes experimental investigations of a three - stage high pressure research turbine at various operating conditions. The experimental investigation is carried out in a three - stage turbine facility at the Turbomachinery Performance and Flow Research Laboratory (TPFL) at Texas A&M University. Its rotor includes non - axisymmetric endwall contouring on the first and second rotor row. Experimental data were obtained using interstage aerodynamic measurements at three measurement stations, namely, downstream of the first rotor row, the second stator row and the second rotor row. Measurements were conducted using five - hole probes traversed in both circumferential and radia l directions to create a measurement window. Performance measurements were carried out within a rotational speed range of 1800 to 3000 RPM. Interstage measurements were obtained at 300 0 rpm. Moreover, the impact of the purge flow injection on the aerodynamic and performance behaviour of the turbine for five coolant - to - mainstream mass flow ratios of 0.0%, 0.5%, 1.0% , 1.5% and 2.0% were investigated. Interstage results exhibit the evidence of the mitigation of secondary flow intensity due to endwall contouring
Effect of Endwall Contouring on the Performance of a Three-Stage HP Turbine
Rezasoltani, Mohsen (author) / Schobeiri, Meinhard T (author)
2018-05-07
Conference paper
Electronic Resource
English
DDC:
690
Numerical study of heat and mass transfer analogy for a simulated turbine endwall
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