空水共用涡轮机气动设计与数值仿真

doi:10.12382/bgxb.2021.0691

摘要/Abstract

摘要： 跨介质航行器是一种具备远程快速打击、重复出入水以及高效突防能力的新概念航行器，而其中涡轮发动机在跨介质航行器不同航行阶段的工作参数差别很大。为解决水下、空中及起飞工况下的空水共用涡轮机的气动设计，结合损失模型的方法提出一种空水共用涡轮机设计方法，通过数值仿真方法验证气动设计方法的合理性以及起飞工况的可行性。研究结果表明：在不同工况下，数值仿真结果与一维气动设计结果的相对误差均在2%以内；使用数值损失分解方法进一步分析了涡轮机的各部分损失，发现叶型损失为空水共用涡轮机的主要损失；水下工况时流场内存在激波和分离涡，部分进气度很小，损失较大；空中工况则流动更为均匀，损失较小；起飞工况时涡轮机工作在非设计点，此时主要依靠水下喷管做功，空中喷管则会产生负功率。该方法可为空水共用涡轮机的优化设计和试验提供参考。

关键词: 空水共用涡轮机, 跨界质航行器, 部分进气, 设计方法, 损失分解

Abstract: Trans-media vehicles are an innovative aircraft with long-range rapid striking, repeated entry, and efficient penetration capabilities. However, the turbine working parameters of trans-media vehicles at different stages differ significantly. To realize the aerodynamic design of shared turbines for underwater, in-flight, and takeoff conditions, loss model is integrated to come up with an air-water shared turbine design. Numerical method is used to verify the accuracy of mean-line design method and the feasibility of takeoff conditions. The results show that the relative error between the numerical results and mean-line design results is within 2% under various working conditions. The numerical loss breakdown method is then used to further analyze the turbine losses and reveal that profile loss is the main loss of the air-water shared turbine. The shock waves and separation vortices are found in the passage under underwater conditions. In addition, the partial admission ratio is also very low, resulting in a relatively high loss. During flight, the flow is more uniform and hence the loss is smaller. During takeoff, the turbine works at an off-design point. The output power relies on the underwater nozzle, while air nozzle generates negative power. This study can provide a reference for the optimal design and experiment of air-water shared turbines.

Key words: air-watersharedturbine, trans-mediavehicle, partialadmission, designmethod, lossbreakdown

中图分类号:

TJ630.1

王瀚伟，罗凯，黄闯，秦侃. 空水共用涡轮机气动设计与数值仿真[J]. 兵工学报, 2022, 43(12): 3151-3161.

WANG Hanwei, LUO Kai, HUANG Chuang, QIN Kan. Aerodynamic Design and Numerical Simulation of Air-water Shared Turbines[J]. Acta Armamentarii, 2022, 43(12): 3151-3161.

参考文献

［1］杨兴帮, 梁建宏, 文力, 等.水空两栖跨介质无人飞行器研究现状[J].机器人, 2018, 40(1):102-114.
YANG X B, LIANG J H, WEN L, et al. Research status of water-air amphibious trans-media unmanned vehicle[J].Robot, 2018, 40(1):102-114. (in Chinese)
[2] 冯金富, 胡俊华, 齐铎. 水空跨介质航行器发展需求及其关键技术[J].空军工程大学学报(自然科学版), 2019, 20(3): 8-13.
FENG J F, HU J H, QI D. Study on development needs and key technologies of air-water trans-media vehicle[J]. Journal of Air Force Engineering University (Natural Science Edition), 2019, 20(3): 8-13. (in Chinese)
[3] WEBER A, SCHREIBER H, FUCHS R, et al. 3D Transonic flow in a compressor cascade with shock-induced corner stall[J].Journal of Turbomachinery, 2002, 124(3): 358-366.
[4] KIELY D H, MOORE J T. Hydrocarbon fueled uuv power systems[C]∥Proceedings of the 2002 Workshop on Autonomous Underwater Vehicles. San Antonio, TX, US:IEEE, 2002: 121-128.
[5] WATERS D F, CADOU C P, EAGLE W E. Quantifying unmanned undersea vehicle range improvement enabled by aluminum-water power system[J]. Journal of Propulsion & Power, 2013, 29(3): 675-685.
[6] 郭兆元, 曹浩, 赵卫兵.纯冲动式鱼雷涡轮机动叶栅超音速流动数值仿真[J].鱼雷技术, 2013, 21(1): 43-47.
GUO Z Y, CAO H, ZHAO W B. Numerical simulation of supersonic flow field in rotor blade cascade for impulse torpedo turbine[J]. Torpedo Technology, 2013, 21(1): 43-47. (in Chinese)
[7] 张睿刚.超高膨胀比涡轮机气动性能研究[D].哈尔滨:哈尔滨工业大学, 2014.
ZHANG R G. Aerodynamic performance research on ultra high expansion ratio turbine[D].Harbin: Harbin Institute of Technology, 2014. (in Chinese)
[8] 伊进宝, 赵卫兵, 师海潮.水下航行体燃气涡轮机工作特性数值研究[J]. 鱼雷技术, 2010, 18(5): 376-380.
YI J B, ZHAO W B, SHI H C. Numerical investigation to gas turbine performance of underwater vehicle[J]. Torpedo Technology, 2010, 18(5):376-380. (in Chinese)
[9] 蒋彬, 罗凯, 高爱军, 等.一种微型部分进气冲动式涡轮机设计方法[J].鱼雷技术, 2015, 23(5): 353-358.
JIANG B, LUO K, GAO A J, et al. A design approach of micro partial admission impusle turbine[J].Torpedo Technology, 2015, 23(5): 353-358. (in Chinese)
[10] QIN K, WANG H W, WANG X R, et al. Thermodynamic and experimental investigation of a metal fuelled steam rankine cycle for unmanned underwater vehicles[J].Energy Conversion and Management, 2020, 223: 113281.
[11] WANG H W, CHAO Y, TANG T, et al.A comparison of partial admission axial and radial inflow turbines for underwater vehicles[J]. Energies, 2021, 14(5): 1514.
[12] TOURNIER J M, EL-GENK M S. Axial flow, multi-stage turbine and compressor models[J].Energy Conversion & Management, 2010, 51(1):16-29.
[13] TSUJITA H. Influence of blade profile on secondary flow in ultra-highly loaded turbine cascades at off-design incidence[C]∥Proceedings of the ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. San Antonio, TX, US: ASME, 2013: V06AT36A028.
[14] ALMELDEIN A Z, EL-SAYED A F, SALEM G B, et al. Turbine based combined cycle engine selection for hypersonic civil transport[C]∥Proceedings of the 21st International Society for Air Breathing Engines Conference. Busan, Korea: AIAA, 2013: ISABE-2013-1657.
[15] SCHOBEIRI M. Improving the efficiency of gas turbines during off-design operation by adjusting the turbine and compressor blade stagger angles[J]. Journal of Applied Mechanical Engineering, 2018, 7(1): 1000302.
[16] GHOREYSHI S M, SCHOBEIRI M T. The ultra-high efficiency gas turbine engine, UHEGT, part I: design and numerical analysis of the multistage system[J].Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2020, 235 (5): 974-990.
[17] 谭春青, 张华良, 陈海生, 等.弯叶片对大转角平面涡轮叶栅气动性能影响的实验研究[J].燃气涡轮试验与研究, 2009, 22(1): 8-12.
TAN C Q, ZHANG H L, CHEN H S, et al. Experimental investigation of the aerodynamic performance of bowed blades in high-turning linear turbine cascades[J]. Gas Turbine Experiment and Research, 2009, 22(1): 8-12. (in Chinese)
[18] 陈巍, 杜发荣, 丁水汀, 等.某微型涡喷发动机总体结构设计[J].航空动力学报, 2010, 25(1):169-174.
CHEN W, DU F R, DING S T, et al. General-structural design study of a micro turbojet engine[J]. Journal of Aerospace Power, 2010, 25(1): 169-174. (in Chinese)
[19] 刘壮, 阚晓旭, 陆华伟, 等.跨音速涡轮平面叶栅气动性能试验研究[J].大连海事大学学报, 2013, 39(2): 123-127.
LIU Z, KAN X X, LU H W, et al. Experimental investigation of aerodynamic parameters in transonic turbine linear cascade[J]. Journal of Dalian Maritime University, 2013, 39(2): 123-127. (in Chinese)
[20] 卢少鹏, 温风波, 梁晨, 等.多级涡轮气动设计与优化的研究[J].推进技术, 2012, 33(6): 888-896.
LU S P, WEN F B, LIANG C, et al. Investigation on multi-stage turbine aerodynamic design and optimization[J]. Journal of Propulsion Technology, 2012, 33(6): 888-896. (in Chinese)
[21] ZHU Y L, LUO J Q, LIU F. Influence of blade lean together with blade clocking on the overall aerodynamic performance of a multi-stage turbine[J]. Aerospace Science and Technology, 2018, 80: 329-336.
[22] 高双林, 查柏林.航空发动机及其部件工作原理[M].北京: 北京航空航天大学出版社, 2019.
GAO S L, ZHA B L. Working principle of aero-engine and its components [M].Beijing: Beihang University Press, 2019. (in Chinese)

[1]	易力力，杨文翰，王时龙. 多股螺旋弹簧加工参数优化方法研究[J]. 兵工学报, 2020, 41(1): 202-208.
[2]	李胜，胡维礼. 一类非完整系统镇定控制器的递推设计方法[J]. 兵工学报, 2009, 30(9): 1276-1280.
[3]	1:陈凤熹;2:李良巧，刘英,姬广振. 稳定变应力作用下疲劳强度可靠性设计方法[J]. 兵工学报, 2003, 24(2): 216-218.
[4]	张运. 论制导回路设计的方法[J]. 兵工学报, 1994, 15(2): 38-41.