Coull, JD and Atkins, NR and Hodson, HP Winglets for Improved Aerothermal Performance of High Pressure Turbines. In: ASME Turbo Expo 2013, 3-6-2013 to 7-6-2013, San Antonio. (Unpublished)Full text not available from this repository.
This paper investigates the design of winglet tips for unshrouded high pressure turbine rotors, considering aerodynamic and thermal performance simultaneously. A novel parameterization method has been developed to alter the tip geometry of a rotor blade. A design survey of un-cooled, flat-tipped winglets is performed using RANS calculations for a single rotor at engine representative operating conditions. Compared to a plain tip, large efficiency gains can be realized by employing an overhang around the full perimeter of the blade, but the overall heat load rises significantly. By employing an overhang on only the early suction surface, significant efficiency improvements can be obtained without increasing the overall heat transfer to the blade. The flow physics are explored in detail to explain the results. For a plain tip, the leakage and passage vortices interact to create a three-dimensional impingement onto the blade suction surface, causing high heat transfer. The addition of an overhang on the early suction surface displaces the tip leakage vortex away from the blade, weakening the impingement effect and reducing the heat transfer on the blade. The winglets reduce the aerodynamic losses by unloading the tip section, reducing the leakage flow rate, turning the leakage flow in a more streamwise direction and reducing the interaction between the leakage fluid and endwall flows. Generally these effects are most effective close to the leading edge of the tip, where the leakage flow is subsonic.
|Item Type:||Conference or Workshop Item (UNSPECIFIED)|
|Divisions:||Div A > Turbomachinery|
|Depositing User:||Cron Job|
|Date Deposited:||11 Mar 2013 11:10|
|Last Modified:||18 Mar 2013 01:06|
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