Performance improvements to the Naval Postgraduate School Turbopropulsion Labs Transonic Axially Splittered Rrotor
Lehrfeld, Michael C.
Gannon, Anthony J.
Hobson, Garth V.
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Performance improvement investigations to the Naval Postgraduate School Turbo Propulsion Laboratorys (NPS TPL) Transonic Axially Splittered Rotor were investigated. Implementation of current NPS TPL design procedure that uses COTS software (MATLAB, SolidWorks, and ANSYS-CFX) for the geometric rendering and analysis was modified and documented. Numerical simulations were conducted and experimental data were collected at the NPS TPL utilizing the transonic compressor rig. This study advanced the understanding of casing tip gap, rotor-stator interaction, stator relative blade placement of a hybrid tandem/splittered design, and performance benefits. The reduction in rotor tip gap produced higher performance bench marks as predicted. The addition and analysis of multiple blade rows proved to be straight forward and the design methodology and in house procedure was further optimized. While other studies sought to affect the pressure surface of the lead blade, it was determined that using the trailing blade to influence the high momentum flow over suction surface of the lead blade produced better performance gains With tip gap closure and the addition of the stator stage, rotor alone performance was improved from experimentally measured peak total-to-total pressure ratio of 1.69 to 1.99 and the peak total-to-total isentropic efficiency from 72 to 77 percent at 100 percent design speed.
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