Simulations of the Unsteady Flow Through the Fastrac Supersonic Turbine
Author:
Griffin Lisa W.1, Dorney Daniel J.2
Affiliation:
1. Fluid Dynamics Analysis Branch, National Aeronautics and Space Administration, George C. Marshall Space Flight Center, Marshall Space Flight Center, AL 35802 2. Department of Mechanical Engineering, Virginia Commonwealth University, Richmond, VA 23113
Abstract
Analysis of the unsteady aerodynamic environment in the Fastrac supersonic turbine is presented. Modal analysis of the turbine blades indicated possible resonance in crucial operating ranges of the turbopump. Unsteady computational fluid dynamics (CFD) analysis was conducted to support the aerodynamic and structural dynamic assessments of the turbine. Before beginning the analysis, two major problems with current unsteady analytical capabilities had to be addressed: modeling a straight centerline nozzle with the turbine blades and exit guide vanes (EGVs), and reducing run times significantly while maintaining physical accuracy. Modifications were made to the CFD code used in this study to allow the coupled nozzle/blade/EGV analysis and to incorporate Message Passing Interface (MPI) software. Because unsteadiness is a key issue for the Fastrac turbine [and future rocket engine turbines such as the Reusable Launch Vehicle (RLV)], calculations were performed for two nozzle-to-blade axial gaps. Calculations were also performed for the nozzle alone, and the results were imposed as an inlet boundary condition for a blade/EGV calculation for the large gap case. These results are compared to the nozzle/blade/EGV results. [S0889-504X(00)02902-0]
Publisher
ASME International
Subject
Mechanical Engineering
Reference10 articles.
1. Rangwalla, A. A., Madavan, N. K., and Johnson, P. D., 1992, “Application of an Unsteady Navier–Stokes Solver to Transonic Turbine Design,” J. Propul. Power, 8, No. 5, pp. 1079–1086. 2. Griffin, L. W., and Nesman, T., 1996, “Prediction of the Unsteady Aerodynamic Environment in the RRTT Turbine,” presented at the 14th Workshop for Fluid Dynamic Applications in Rocket Propulsion and Launch Vehicle Technology, NASA/Marshall Space Flight Center, Apr. 23–25. 3. Baldwin, B. S., and Lomax, H., 1978, “Thin Layer Approximation and Algebraic Model for Separated Turbulent Flow,” AIAA Paper No. 78-257. 4. Roe, P. L.
, 1981, “Approximate Riemann Solvers, Parameter Vectors, and Difference Schemes,” J. Comput. Phys., 43, pp. 357–372. 5. Dorney, D. J., Davis, R. L., Edwards, D. E., and Madavan, N. K., 1992, “Unsteady Analysis of Hot Streak Migration in a Turbine Stage,” J. Propul. Power, 8, No. 2, pp. 520–529.
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