The design and characteristic analysis of the single-stage centrifugal compressor were performed to meet the requirements of the integral performance of a certain solid propellant air turbo rocket (SPATR). Based on the limitation of the geometry and aerodynamic demands, the impeller and diffuser were designed and optimized by considering the disc friction loss and the flow quality. A theoretical approach was applied to evaluate feasibility and primary aerodynamic performance of the compressor. Focused on the operation performance of the compressor, the detailed flow structure in the compressor was investigated by using numerical simulation. The results show that the total pressure ratio and isentropic efficiency of the compressor in design point are 3.5 and 0.78 respectively, which meets the design demands. The compressor has excellent aerodynamic characteristics during the starting procedure or under the partial loading condition. The position of flow separation and the reason of flow loss are analyzed to conduct further optimization.
[1]
John A. Bossard,et al.
CUSTOMIZED TURBOMACHINERY FOR SOLID-PROPELLANT AIR TURBO ROCKETS
,
1997
.
[2]
Yang Liu,et al.
Turbocharged Solid Propellant Ramjet for Tactical Missile
,
2012
.
[3]
Yosuke Shimada,et al.
Technology Demonstration of ATR with a Ramjet Test Facility
,
2004
.
[4]
R. E. Nece,et al.
Chamber Dimension Effects on Induced Flow and Frictional Resistance of Enclosed Rotating Disks
,
1960
.
[5]
Matthew E. Thomas,et al.
Monorotor turbomachinery for air-turbo-rocket propulsion
,
1995
.
[6]
H. N. Michael.
Centrifugal and axial flow pumps: by A. J. Stepanoff. 428 pages, illustrations, diagrams, 15 × 24 cm. New York, John Wiley & Sons, Inc., 1948. Price, $7.50
,
1948
.