基于动态边界的跨声速压气机过渡态三维模拟方法
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摘要
针对航空涡轮发动机部件的过渡态,提出了一种基于压气机部件三维模型的过渡态性能计算方法,采用动态边界条件,以转速和出口静压为过渡过程的控制参数,二阶向后欧拉法求解三维非定常雷诺平均Navier-Stokes方程组,通过三维非定常模拟获得压气机的过渡态性能和内部非定常流场特征。以NASA跨声速压气机Rotor 67转子为模型,采用该方法模拟了压气机从60%设计转速加速至100%设计转速的过渡过程,获得了压气机过渡态性能及转子内部详细的激波结构与演变过程。对比通用特性结果,在整个过渡曲线上,总压比相对误差最大值小于6%,绝热效率相对误差最大值小于2%,验证了该方法的可靠性。结论表明:基于动态边界的三维非定常模拟方法能够准确模拟压气机的过渡态性能,并反映出过渡态的非定常流场详细信息。
A transient simulation method based on three-dimensional models of compressor componentswas developed,focusing on the transient state of aviation turbine engines components. The dynamic boundarieswere used to set rotational speed and static pressure at outlet as the controlling parameters of transient process.The second-order backward Euler scheme was used to calculate the three-dimensional unsteady Reynolds aver-age Navier-Stokes equations. The transient performance and internal unsteady flow field characteristics of a com-pressor were obtained through three-dimensional unsteady simulation. Using a transonic compressor rotor,NASARotor 67,as a model,this method was applied to simulate the transient process accelerating from 60% design ro-tational speed to 100% design rotational speed,and the transient performance of the compressor and detailedshock structure and its evolution process inside the compressor were obtained. The reliability of the method wasverified by comparing with the results calculated by the general characteristic calculation method,as the maximalrelative error of total pressure ratio was less than 6% and the maximal relative error of adiabatic efficiency wasless than 2% on the whole transient line. The results show that the three-dimensional unsteady simulation methodbased on dynamic boundaries can accurately simulate the transient performance of compressors and reflect the detailed information of unsteady flow field in transient process.
A transient simulation method based on three-dimensional models of compressor componentswas developed,focusing on the transient state of aviation turbine engines components. The dynamic boundarieswere used to set rotational speed and static pressure at outlet as the controlling parameters of transient process.The second-order backward Euler scheme was used to calculate the three-dimensional unsteady Reynolds aver-age Navier-Stokes equations. The transient performance and internal unsteady flow field characteristics of a com-pressor were obtained through three-dimensional unsteady simulation. Using a transonic compressor rotor,NASARotor 67,as a model,this method was applied to simulate the transient process accelerating from 60% design ro-tational speed to 100% design rotational speed,and the transient performance of the compressor and detailedshock structure and its evolution process inside the compressor were obtained. The reliability of the method wasverified by comparing with the results calculated by the general characteristic calculation method,as the maximalrelative error of total pressure ratio was less than 6% and the maximal relative error of adiabatic efficiency wasless than 2% on the whole transient line. The results show that the three-dimensional unsteady simulation methodbased on dynamic boundaries can accurately simulate the transient performance of compressors and reflect the detailed information of unsteady flow field in transient process.
引文
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[19]于龙江,朴英.基于双时间步法的航空发动机过渡态仿真[J].推进技术,2009,30(6):730-734.(YU Long-jiang,PIAO Ying. Dual Time Step Method in Transient Simulation of Aero Engine[J]. Journal of Propulsion Technology,2009,30(6):730-734.)
[20]唐世建,童万军.基于容积法的某涡扇发动机动态建模方法[J].航空动力学报,2013,28(3):709-713.
[21] Strazisar A J,Wood J R,Hathaway M D,et al. Laser Anemometer Measurements in a Transonic Axial Flow Fan Rotor[R]. NASA-TP-2879.
[22] ANSYS CFX. User’s Guide-14[M]. New York:ANSYS Inc,2012.
[23]廉筱纯.航空发动机原理[M].西安:西北工业大学出版社,2005.
[24] Wang S,Li S,Song X. Investigations on Static Aeroelastic Problems of Transonic Fans Based on Fluid-Structure Interaction Method[J]. Proceedings of the Institution of Mechanical Engineers Part A:Journal of Power&Energy,2016,230(7):685-695.
[25]单鹏.多维气体动力学基础[M].北京:北京航空航天大学出版社,2008.
[2] Csank J,Zinnecker A M. Application of the Tool for Turbine Engine Closed-Loop Transient Analysis(TTECTrA)for Dynamic Systems Analysis[C]. Cleveland:50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference,2014.
[3] Miller B A,Szuch J R,Gaugler R E,et al. A Perspective on Future Directions in Aerospace Propulsion System Simulation[R]. NASA-TM-102038.
[4] Mckinney J S. Simulation of Turbofan Engine,Part 1:.Description of Method and Balancing Technique[R].AFAPL-TR-67-125-PT-1.
[5] Sellers J F,Daniele C J. DYNGEN:A Program for Calculating Steady-State and Transient Performance of Turbojet and Turbofan Engines[R]. NASA-TN-D-7901.
[6] Koenig R W,Fishbach L H. GENENG:A Program for Calculating Design and Off-Design Performance for Turbojet and Turbofan Engines[R]. NASA-TN D-6552.
[7] Fishbach L H,Koenig R W. GENENG II:A Program for Calculating Design and Off-Design Performance of Twoand Three Spool Turbofans with as Many as Three Nozzles[R]. NASA-TN D-6553.
[8] Palmer J R,Cheng-Zhong Y. TURBOTRANS—ΑProgramming Language for the Performance Simulation of Arbitrary Gas Turbine Engines with Arbitrary Control Systems[J]. International Journal of Turbo and Jet Engines,1985,2(1):19-28.
[9] Chappell M A,McLaughlin P W. Approach to Modeling Continuous Turbine Engine Operation from Startup to Shutdown[J]. Journal of Propulsion and Power,1993,9(3):466-471.
[10] Garrard G D. ATEC:The Aerodynamic Turbine Engine Code for the Analysis of Transient and Dynamic Gas Turbine Engine System Operations,Part 2:Numerical Simulations[C]. Birmingham:ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition,1996.
[11] Venturini M. Simulation of Compressor Transient Behavior Through Recurrent Neural Network Models[J]. Journal of Turbomachinery,2006,128(3):444-454.
[12] Ferlauto M,Marsilio R. Simulation of Jet Engine Transient by a CFD Method[C]. California:42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference&Exhibit,2006.
[13] Chin J C,Csank J T,Haller W J,et al. An Introduction to Transient Engine Applications Using the Numerical Propulsion System Simulation(NPSS)and MATLAB[R]. NASA-TM-2016-218922.
[14] Csank J T,Zinnecker A M. Tool for Turbine Engine Closed-Loop Transient Analysis(TTECTrA)User’s Guide[R]. NASA-TM-2014-216663.
[15] Kurzke J. GasTurb 12:A Program to Calculate Design and Off-Design Performance of Gas Turbines. User’s Manual[M]. Aachen:Gasturb Inc,2012.
[16]屠秋野,唐狄毅.涡扇发动机起动模型及起动控制规律的研究[J].推进技术,1999,20(2):21-24.(TU Qiu-ye,TANG Di-yi. Study on Startup Model and Startup Control Law of Turbofan Engine[J]. Journal of Propulsion Technology,1999,20(2):21-24.)
[17]苏三买,廉筱纯.涡扇发动机过渡态性能实时仿真研究[C].温州:中国航空学会发动机自动控制学术讨论会,2002.
[18]唐宏刚,蔡元虎.某型涡扇发动机起动和加速过程数值模拟[J].推进技术,2007,28(3):264-268.(TANG Hong-gang,CAI Yuan-hu. Modeling Turbofan Engine Starting and Accelerating Condition Based on Component Matching Principles[J]. Journal of Propulsion Technology,2007,28(3):264-268.)
[19]于龙江,朴英.基于双时间步法的航空发动机过渡态仿真[J].推进技术,2009,30(6):730-734.(YU Long-jiang,PIAO Ying. Dual Time Step Method in Transient Simulation of Aero Engine[J]. Journal of Propulsion Technology,2009,30(6):730-734.)
[20]唐世建,童万军.基于容积法的某涡扇发动机动态建模方法[J].航空动力学报,2013,28(3):709-713.
[21] Strazisar A J,Wood J R,Hathaway M D,et al. Laser Anemometer Measurements in a Transonic Axial Flow Fan Rotor[R]. NASA-TP-2879.
[22] ANSYS CFX. User’s Guide-14[M]. New York:ANSYS Inc,2012.
[23]廉筱纯.航空发动机原理[M].西安:西北工业大学出版社,2005.
[24] Wang S,Li S,Song X. Investigations on Static Aeroelastic Problems of Transonic Fans Based on Fluid-Structure Interaction Method[J]. Proceedings of the Institution of Mechanical Engineers Part A:Journal of Power&Energy,2016,230(7):685-695.
[25]单鹏.多维气体动力学基础[M].北京:北京航空航天大学出版社,2008.