Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
-
Chao Fu
Collaborative Innovation Center of Advanced Aero-Engine, National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, Beijing 100191, China.
,
Zhengping Zou
Collaborative Innovation Center of Advanced Aero-Engine, National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, Beijing 100191, China.
,
Qingguo Kong
Collaborative Innovation Center of Advanced Aero-Engine, National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, Beijing 100191, China.
Sino-European Institute of Aviation Engineering, Civil Aviation University of China, Tianjin 300300, China.
Beijing Aerospace Technology Institute, Beijing 100074, China.
Collaborative Innovation Center of Advanced Aero-Engine, National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, Beijing 100191, China.
Abstract
Supersonic turbine is widely used in the turbo pump of modern rocket. A preliminary design method for supersonic turbine has been developed considering the coupling effects of turbine and nozzle. Numerical simulation has been proceeded to validate the feasibility of the design method. As the strong shockwave reflected on the mixing plane, additional numerical simulated error would be produced by the mixing plane model in the steady CFD. So unsteady CFD is employed to investigate the aerodynamic performance of the turbine and flow field in passage. Results showed that the preliminary design method developed in this paper is suitable for designing supersonic turbine. This periodical variation of complex shockwave system influences the development of secondary flow, wake and shock-boundary layer interaction, which obviously affect the secondary loss in vane passage. The periodical variation also influences the strength of reflecting shockwave, which affects the profile loss in vane passage. Besides, high circumferential velocity at vane outlet and short blade lead to high radial pressure gradient, which makes the low kinetic energy fluid moves towards hub region and produces additional loss.
About the authors
Collaborative Innovation Center of Advanced Aero-Engine, National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, Beijing 100191, China.
Collaborative Innovation Center of Advanced Aero-Engine, National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, Beijing 100191, China.
Collaborative Innovation Center of Advanced Aero-Engine, National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, Beijing 100191, China.
Sino-European Institute of Aviation Engineering, Civil Aviation University of China, Tianjin 300300, China.
Beijing Aerospace Technology Institute, Beijing 100074, China.
Collaborative Innovation Center of Advanced Aero-Engine, National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, Beijing 100191, China.
Nomenclature
total loss coefficient for a blade row
profile loss coefficient
secondary loss coefficient
energy loss coefficient of shockwave
pressure loss coefficient
velocity
rotor velocity
density
pressure
Temperature, period
axial velocity ratio,
stage loading coefficient,
flow coefficient,
reaction,
total-to-total efficiency of turbine
stagnation pressure recovery coefficient
circulation loss coefficient
radius
specific heat ratio
specific gas constant
characteristic Mach number,
total-to-static efficiency of turbine nozzle system
height of blade
flow angle in stationary
stagnation pressure loss coefficient
- ΔS
entropy increment
- t
time
- Ma
Mach number
- Cx
normalized axial chord
Subscripts
- 0
at 1st vane inlet
- 1
at rotor inlet
- 2
at rotor outlet
- 3
at 2nd vane outlet
- u
in tangential direction
- a
in axial direction
- in
at nozzle inlet
- out
at nozzle outlet
- is
isentropic
Superscripts
- ¯
averaged quantity
- *
stagnation quantity
Acknowledgments
The authors would like to thank DITDP for funding this work.
References
1. Moffitt TP. Design and experimental investigation of a single-stage turbine with a rotor entering relative Mach number of 2, NACA report no. RM E58F20a, 1958.Suche in Google Scholar
2. Goldman LJ. Analytical investigation of supersonic turbomachinery blading-analysis of impulse turbineblade sections, NASA technical note no. TN D-4422, 1968.Suche in Google Scholar
3. Grönman A, Turunen-Saaresti T. Design and off-design performance of a supersonic axial flow turbine with different stator–rotor axial gaps. Proc Inst Mech Eng Part A J Power Energy 2011;225:497–503.10.1177/0957650910396417Suche in Google Scholar
4. Smith S. A simple correlation of turbine efficiency. J Roy Aeronaut Soc 1969;69:467–70.10.1017/S0001924000059108Suche in Google Scholar
5. Kacker S, Okapuu U. A mean line prediction method for axial flow turbine efficiency. J Eng Power 1982;104:111–19.10.1115/1.3227240Suche in Google Scholar
6. Macchi E, Perdichizzi A. Efficiency prediction for axial-flow turbines operating with nonconventional fluids. J Eng Power 1981;103:718–24.10.1115/1.3230794Suche in Google Scholar
7. Craig H, Cox H. Performance estimation of axial flow turbines. Proc Inst Mech Eng 1970;185:407–24.10.1243/PIME_PROC_1970_185_048_02Suche in Google Scholar
8. Fu C, Zhou ZP, Liu HX, Li W, Zhou Y. Turbine aerodynamic design criteria of versatile core. J Propul Technol 2011;32:165–74.Suche in Google Scholar
9. Dorney DJ, Griffin LW, Gundy-Burlet KL. Simulations of the flow in supersonic turbines with straight centerline nozzles. J Propul Power 2000;16:370–4.10.2514/6.1999-1054Suche in Google Scholar
10. Griffin LW, Dorney DJ. Simulations of the unsteady flow through the fastrac supersonic turbine. J Turbomach 2000;122:225–33.10.1115/99-GT-156Suche in Google Scholar
11. Dorney DJ, Griffin LW, Huber FW. A study of the effects of tip clearance in a supersonic turbine. J Turbomach 2000;122:674–83.10.1115/2000-GT-0447Suche in Google Scholar
12. Jeong E, Park PG, Kang SH, Kim J. Effect of nozzle-rotor clearance on turbine performance, 2006. ASME paper no. FEDSM2006–98388.10.1115/FEDSM2006-98388Suche in Google Scholar
13. Ainley D, Mathieson G. An examination of the flow and pressure losses in blade rows of axial-flow turbines, A.R.C. technical report no. 2891, 1951.Suche in Google Scholar
14. Zhao YS. Theory of torpedo turbine engine. Xi’an: Northwestern Polytechnical University Press, 2002. ISBN 7561213972.Suche in Google Scholar
15. Menter FR. Zonal two equation k-ω turbulence models for aerodynamic flows, 1993. AIAA paper no. AIAA 93-2906.10.2514/6.1993-2906Suche in Google Scholar
16. Bardina JE, Huang PG, Coakley TJ. Turbulence modeling validation, testing and development. NASA technical memorandum no. 110446, 1997.Suche in Google Scholar
17. Qi L. Investigations of unsteady interaction mechanism and flow control in the turbine endwall regions. PhD thesis, Beihang University, Beijing, 2010.Suche in Google Scholar
18. Torre D, Vázques R, Blanco ER, Hodson HP, New A. Alternative for reduction in secondary flows in low pressure turbines. J Turbomach 2011;133:1–10.10.1115/GT2006-91002Suche in Google Scholar
19. Anker JE, Mayer JF, Casey MV. The impact of rotor labyrinth seal leakage flow on the loss generation in an axial turbine. Proc Inst Mech Eng Part A: J Power Energy 2005;219:481–90.10.1243/095765005X31081Suche in Google Scholar
20. Natkaniec CK, Kammeyer J, Seume JR. Secondary flow structures and losses in a radial turbine nozzle. ASME paper no. GT2011-46753, 2011.10.1115/GT2011-46753Suche in Google Scholar
21. Sirakov BT, Tan CS, Effect of upstream unsteady flow conditions on rotor tip leakage flow. ASME paper no. GT2002-30358, 2002.10.1115/GT2002-30358Suche in Google Scholar
22. Mailach R, Lehmann I, Vogeler K. Periodical unsteady flow within a rotor blade row of an axial compressor Part II: wake-tip clearance vortex interaction. ASME paper no. GT2007-27211, 2007.10.1115/GT2007-27211Suche in Google Scholar
23. Zhang WH, Zou ZP, Li W, Luo JQ, Pan SN. Unsteady numerical simulation investigation of effect of blade profile deviation on turbine performance. Acta Aeronaut Astronaut Sin 2010;31:2130–8.Suche in Google Scholar
©2016 by De Gruyter
Artikel in diesem Heft
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
- Effect of Inlet Clearance on the Aerodynamic Performance of a Centrifugal Blower
- Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
- Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
- Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
- Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
Artikel in diesem Heft
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
- Effect of Inlet Clearance on the Aerodynamic Performance of a Centrifugal Blower
- Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
- Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
- Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
- Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
