航空学报 > 2025, Vol. 46 Issue (14): 131436-131436   doi: 10.7527/S1000-6893.2024.31436

含失稳模拟的高通流双变循环发动机动态模型

周晗, 陈芊, 汪虹余, 史昊蓝, 魏鹏轩, 李嘉诚, 张天宏, 盛汉霖()   

  1. 南京航空航天大学 能源与动力学院,南京 210016
  • 收稿日期:2024-10-23 修回日期:2024-11-12 接受日期:2024-12-06 出版日期:2024-12-18 发布日期:2024-12-18
  • 通讯作者: 盛汉霖 E-mail:dreamshl@nuaa.edu.cn
  • 基金资助:
    航空发动机及燃气轮机基础科学中心重点项目(P2023-B-V-001-001);中国航空发动机产学研合作项目(HFZL2023CXY012);国家自然科学基金面上项目(52176009);国家博士后创新人才支持计划项目(BX20240481)

A high flux dual variable cycle engine model coupled with instability simulation

Han ZHOU, Qian CHEN, Hongyu WANG, Haolan SHI, Pengxuan WEI, Jiacheng LI, Tianhong ZHANG, Hanlin SHENG()   

  1. College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
  • Received:2024-10-23 Revised:2024-11-12 Accepted:2024-12-06 Online:2024-12-18 Published:2024-12-18
  • Contact: Hanlin SHENG E-mail:dreamshl@nuaa.edu.cn
  • Supported by:
    Science Center for Gas Turbine Project(P2023-B-V-001-001);Aviation Industry Corporation of China Industry-Academia-Research Cooperation Project(HFZL2023CXY012);National Natural Science Foundation of China(52176009);Postdoctoral Innovation Talent Support Program of China(BX20240481)

摘要:

高通流双变循环发动机(High Flow Dual Variable Cycle Engine, HFDVCE)以全速域大流量、高节流比、涵道比和增压比同步组合调节以及高涡轮前温度等气动热力方案来获得高性能工作能力,满足低速经济性和高速大推力的需求。相比于常规发动机,HFDVCE在全包线范围内及模式切换时具有更加突出的气动稳定性问题。因此,本研究致力于开展HFDVCE的气动稳定性研究,针对当前研究中整机失稳模拟的缺失与多工况下各子模型间参数不匹配等问题,提出了一种含失稳模拟的HFDVCE模型。首先,基于部件法建立高精度发动机非线性模型,获得压缩部件气动参数。然后,提出了一种压缩部件气动失稳动力学建模方法。通过引入扭矩项表征转速对失稳模型特性的影响,建立含失速、喘振两类不稳定工况的失稳模型,避免了定转速假设,解决了多失稳子模型间系数不匹配的问题。进一步,厘清压缩部件失稳模型与发动机非线性模型之间的耦合关系,通过失稳系数表征压缩系统气动失稳对发动机整机性能的影响,建立了含失稳模拟的HFDVCE模型,实现了整机失稳的动态模拟。最后,开展了4种HFDVCE典型失稳模式的仿真实验,验证了该模型的有效性,为主动稳定性控制设计提供了仿真平台。

关键词: 部件级模型, 压气机失稳动力学, 高通流双变循环发动机, 失速与喘振, 失稳模拟

Abstract:

The High Flow Dual Variable Cycle Engine (HFDVCE) achieves high performance by the aerodynamic and thermodynamic schemes such as synchronous combination of high flow rate, high throttle ratio, bypass ratio, and boost ratio regulation in the full speed range, as well as high turbine front temperature, meeting the requirements of low-speed economy and high-speed high thrust. Compared to conventional engines, HFDVCE has more prominent aerodynamic stability issues within the full range and mode switching. This article conducts research on the aerodynamic stability of HFDVCE, and proposes an HFDVCE model with instability simulation to address the lack of overall instability simulation and parameter mismatch between sub-models under multiple operating conditions. Firstly, a high-precision nonlinear model of the engine was established based on the component method to obtain the aerodynamic parameters of compression components. Then, a dynamic modeling method for aerodynamic instability of compression components was proposed. By introducing a torque term to characterize the influence of rotational speed on the characteristics of the instability model, an instability model with two types of unstable conditions, stall and surge, was established to avoid the assumption of constant rotational speed and solve the problem of coefficient mismatch between multiple instability sub-models. Furthermore, the coupling relationship between the instability model of compression components and the nonlinear model of the engine was clarified. The impact of aerodynamic instability of the compression system on the overall performance of the engine was characterized by the instability coefficient, and an HFDVCE model with instability simulation was established to achieve dynamic simulation of overall instability. Finally, simulation experiments were conducted on four typical instability modes of HFDVCE, verifying the effectiveness of the model and providing a simulation platform for active stability control design.

Key words: component level model, compressor instability dynamics, high flow dual variable cycle engine, stall and surge, instability simulation

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