July 25, 2014 / Accepted： August 18, 2014 / Published： November 25, 2014 Abstract： This paper presents the measurement results of a l1/2 stage LPT （low pressure turbine） test rig at Graz University of Technology ...July 25, 2014 / Accepted： August 18, 2014 / Published： November 25, 2014 Abstract： This paper presents the measurement results of a l1/2 stage LPT （low pressure turbine） test rig at Graz University of Technology incorporating two different rotor geometries： one with a regular blade loading and the other with a highly loaded blade geometry. The test rig was designed in cooperation with MTU Aero Engines and represented the last 1.5 stages of a commercial aero engine. Considerable efforts were put on the adjustment of all relevant model parameters （Mach number, blade count ratio, airfoil aspect ratio, blade loading, etc.） to reproduce the full scale LPT situation. The rig diameter is approximately half of that of a commercial aero engine LPT. The number of blades and vanes for the two investigated stages as well as the pressure ratio and power output are identical, resulting in a decrease in rotational speed of the HSL （high stage loading） rotor. Measurement data from a FRAPP （fast response pressure probe） is used to compare the flow fields of the two different stages. The effect of the different stage designs can be seen when comparing the exit flow fields. The highly loaded stage shows a more pronounced tip leakage vortex compared to the datum stage. The highly loaded stage shows wider wakes with a lower total pressure deficit. The fluctuations of total pressure within the flow field are directly related to the upstream wake. If the measurement position is located within a stator wake, the fluctuations are significantly smaller than that out of the wake.展开更多
文摘July 25, 2014 / Accepted： August 18, 2014 / Published： November 25, 2014 Abstract： This paper presents the measurement results of a l1/2 stage LPT （low pressure turbine） test rig at Graz University of Technology incorporating two different rotor geometries： one with a regular blade loading and the other with a highly loaded blade geometry. The test rig was designed in cooperation with MTU Aero Engines and represented the last 1.5 stages of a commercial aero engine. Considerable efforts were put on the adjustment of all relevant model parameters （Mach number, blade count ratio, airfoil aspect ratio, blade loading, etc.） to reproduce the full scale LPT situation. The rig diameter is approximately half of that of a commercial aero engine LPT. The number of blades and vanes for the two investigated stages as well as the pressure ratio and power output are identical, resulting in a decrease in rotational speed of the HSL （high stage loading） rotor. Measurement data from a FRAPP （fast response pressure probe） is used to compare the flow fields of the two different stages. The effect of the different stage designs can be seen when comparing the exit flow fields. The highly loaded stage shows a more pronounced tip leakage vortex compared to the datum stage. The highly loaded stage shows wider wakes with a lower total pressure deficit. The fluctuations of total pressure within the flow field are directly related to the upstream wake. If the measurement position is located within a stator wake, the fluctuations are significantly smaller than that out of the wake.
