Impeller Flow Field Laser Velocimeter Measurements

L A Brozowski,T V Ferguson,L Rojas

doi:10.1155/s1023621x96000024

Abstract

Development of Computational Fluid Dynamics (CFD) computer codes for complex turbomachinery affords a complete three-dimensional (3-D) flow field description. While significant improvements in CFD have been made due to improvements in computers, numerical algorithms, and physical modeling, a limited experimental database for pump CFD code validation exists.Under contract (NAS8-38864) to the National Aeronautics and Space Administration (NASA) at Marshall Space Flight Center (MSFC) a test program was undertaken at Rocketdyne to obtain benchmark data for typical rocket engine pump geometry. Nonintrusive velocity data were obtained with a laser two-focus velocimeter. Extensive laser surveys at the inlet and discharge of a Rocketdyne-designed impeller were performed. Static pressures were measured at key locations to provide boundary conditions for CFD code validation.

Highlights

Under contract (NAS8-38864) to the National Aeronautics and Space Administration (NASA) at Marshall Space Flight Center (MSFC) a test program was undertaken at Rocketdyne to obtain benchmark data for typical rocket engine pump geometry
The objective of the test program undertaken was to obtain benchmark quality data, flow velocity and angle at key locations in a generic pump operating at the impeller design flow rate
The test article was a Rocketdyne-designed shrouded impeller that met the operational requirements for the Space Transportation Main Engine (STME) fuel pump and designated the "Consortium baseline impeller." Table summarizes the impeller geometry and test conditions

Summary

Introduction

Under contract (NAS8-38864) to the National Aeronautics and Space Administration (NASA) at Marshall Space Flight Center (MSFC) a test program was undertaken at Rocketdyne to obtain benchmark data for typical rocket engine pump geometry. The impeller inlet static pressure tap plane was located a nondimensional axial length of 0.0766 downstream of the laser survey plane. Identification of circumferential variations at the impeller discharge was accommodated by three static pressure taps located around the tester circumference in a plane midway between the two impeller discharge laser survey planes. A differential static pressure measurement between the lowest radial impeller.discharge survey plane and the tester inlet provided redundancy.

Results

Conclusion