火箭推进

为了研究预冷空气涡轮火箭发动机(PATR发动机)在最大推力状态下的部件匹配规律和系统性能特点,建立了PATR发动机的非线性变工况模型,确定了一种能充分发挥发动机推力性能和使其能安全稳定工作的控制规律,并研究了基于该控制规律的PATR发动机典型工况点的速度和高度特性。数值计算表明:保持氦涡轮转速和入口温度为最大允许值,确保主燃室余气系数不大于1.6和外涵冲压燃烧室余气系数不小于1.5,并使尾喷管喉部开度和空气压气机换算流量保持一定的关系时,PATR发动机处于最大推力状态,并能够在安全边界内工作; 在控制规律的约束下,飞行条件的变化使得发动机工作状态点在确定的工作线上移动,决定发动机工作状态的重要参数按照一定的规律变化,因此控制量必须进行相应的调节以实现对发动机工作状态的控制。

In order to study the component matching rule and system performance characteristics of the pre-cooling air turbo rocket engine(PATR)under the maximum thrust condition, a nonlinear variable condition model of PATR engine was established, and a control law which can maximize the engine's thrust performance and make it work safely and stably was determined.Also, the velocity and height characteristics of PATR engine at typical operating conditions based on the control law were studied.The numerical calculation shows that the PATR engine is in the maximum thrust state and can work within the safety boundary when the helium turbine speed and inlet temperature are the maximum allowable values, the excess air coefficient of main combustion chamber is not more than 1.6 and the excess air coefficient of external ramjet combustor is not less than 1.5, and the opening of nozzle throat is kept in a certain relationship with the conversion flow rate of air compressor conversion.Under the constraint of the control law, the change of flight conditions makes the engine operating state point move on the determined working line, and the important parameters affecting the engine operating state change according to a certain law.Therefore, the control variables must be adjusted accordingly to control the engine operating state.

引言
1 PATR发动机系统分析
2 基于控制规律的PATR速度特性
3 基于控制规律的PATR高度特性
4 结论

图1 PATR发动机系统原理图<br/>Fig.1 Schematic diagram of PATR engine

图1 PATR发动机系统原理图
Fig.1 Schematic diagram of PATR engine

图2 飞行动压和进气道参数及捕获空气流量随马赫数的变化<br/>Fig.2 Variation of flight dynamic pressure, inlet parameters and captured air flow with Mach number

图2 飞行动压和进气道参数及捕获空气流量随马赫数的变化
Fig.2 Variation of flight dynamic pressure, inlet parameters and captured air flow with Mach number

图3 涡轮机械工作参数随马赫数的变化<br/>Fig.3 Variation of working parameters of turbomachinery with Mach number

图3 涡轮机械工作参数随马赫数的变化
Fig.3 Variation of working parameters of turbomachinery with Mach number

图4 主燃室参数随马赫数的变化<br/>Fig.4 Variation of main combustor parameters with Mach number

图4 主燃室参数随马赫数的变化
Fig.4 Variation of main combustor parameters with Mach number

图5 预燃室参数随马赫数的变化<br/>Fig.5 Variation of preburner parameters with Mach number

图5 预燃室参数随马赫数的变化
Fig.5 Variation of preburner parameters with Mach number

图6 外涵燃烧室参数随马赫数的变化<br/>Fig.6 Variation of parameters for external ramjet combustor with Mach number

图6 外涵燃烧室参数随马赫数的变化
Fig.6 Variation of parameters for external ramjet combustor with Mach number

图7 发动机推力和单位推力随马赫数的变化<br/>Fig.7 Variation of engine thrust and specific thrust with Mach number

图7 发动机推力和单位推力随马赫数的变化
Fig.7 Variation of engine thrust and specific thrust with Mach number

图8 飞行动压和进气道参数及捕获空气流量随高度的变化<br/>Fig.8 Variation of flight dynamic pressure, inlet parameters and captured air flow with height

图8 飞行动压和进气道参数及捕获空气流量随高度的变化
Fig.8 Variation of flight dynamic pressure, inlet parameters and captured air flow with height

图9 涡轮机械工作参数随高度的变化<br/>Fig.9 Variation of working parameters of turbomachinery with height

图9 涡轮机械工作参数随高度的变化
Fig.9 Variation of working parameters of turbomachinery with height

图10 主燃室参数随高度的变化<br/>Fig.10 Variation of main combustor parameters with height

图10 主燃室参数随高度的变化
Fig.10 Variation of main combustor parameters with height

图11 预燃室参数随高度的变化<br/>Fig.11 Variation of preburner parameters with height

图11 预燃室参数随高度的变化
Fig.11 Variation of preburner parameters with height

图12 外涵燃烧室参数随高度的变化<br/>Fig.12 Variation of parameters for external ramjet combustor with height

图12 外涵燃烧室参数随高度的变化
Fig.12 Variation of parameters for external ramjet combustor with height

图13 发动机推力和单位推力随高度的变化<br/>Fig.13 Variation of engine thrust and specific thrust with height

图13 发动机推力和单位推力随高度的变化
Fig.13 Variation of engine thrust and specific thrust with height

[1] 邹正平,王一帆,额日其太,等.高超声速强预冷航空发动机技术研究进展[J].航空发动机,2021,47(4):8-21.
[2] 马晓秋.预冷吸气组合发动机研究进展与关键技术分析[J].科技导报,2020,38(12):85-95.
[3] 陈操斌,郑日恒,马同玲,等.带有闭式布雷顿循环的预冷发动机特性研究[J].推进技术,2021,42(8):1749-1760.
[4] 姚尧,王占学,张晓博,等.液氢预冷吸气式发动机建模与循环特性分析[J].推进技术,2022,43(4):26-36.
[5] 唐靖博,杨庆春,徐旭.预冷组合循环发动机吸气式模态建模与性能分析[J].推进技术,2022,43(9):20-33.
[6] 董芃呈,唐海龙,陈敏.高超声速预冷发动机总体性能研究[J].航空动力,2020(3):23-26.
[7] VARVILLR,BOND A.The SKYLON spaceplane[EB/OL].https://docshare.tips/saber-stol-space-plane_5750b8d2b6 d87f4fa28b4a55.html,2004.
[8] MURRAY J,GUHA A,BOND A.Overview of the development of heat exchangers for use in air-breathing propulsion pre-coolers[J].Acta Astronautica,1997,41(11):723-729.
[9] WILCOX E,TROUT A M.Analysis of thrust augmentation of turbojet engines by water injection at compressor inlet including charts for calculating compression processes with water injection[R].NACA-TR-1006.
[10] WILLENS D.Liquid injection on turbojet engines for high speed aircraft[R].R-139.
[11] SOHN R L.Theoretical and experimental studies of precompressor evaporative cooling for application to the turbojet engine in high altitude supersonic flight[R].WADC-TR-56-477.
[12] TANATSUGU N,SATO T,BALEPIN V,et al.Development study on ATREX engine[C]//Space Plane and Hypersonic Systems and Technology Conference.Reston,Virigina:AIAA,1996.
[13] SATO T,KOBAYASHI H,TANATSUGU N,et al.Development study of theprecooler of the ATREX engine[C]//12th AIAA International Space Planes and Hypersonic Systems and Technologies.Reston,Virginia:AIAA,2003.
[14] 张蒙正,南向谊,刘典多.预冷空气涡轮火箭组合动力系统原理与实现途径[J].火箭推进,2016,42(1):6-12.
[15] 张蒙正,刘典多,马海波,等.PATR发动机关键技术与性能提升途径初探[J].推进技术,2018,39(9):1921-1927.
[16] 朱岩,马元,张蒙正.预冷空气涡轮火箭发动机氦循环系统的参数特性[J].航空动力学报,2018,33(8):2016-2024.
[17] 罗佳茂,杨顺华,母忠强,等.预冷型组合循环发动机技术[J].空气动力学学报,2022,40(1):190-207.
[18] 吴弈臻,马元,黄乐萍,等.预冷组合发动机中波瓣混流器对氢气/空气掺混性能影响[J].火箭推进,2021,47(6):76-85.
[19] 玉选斐.预冷吸气式组合推进系统热力循环及控制规律研究[D].哈尔滨:哈尔滨工业大学,2020.
[20] 陆国栋,周强泰,田茂诚,等.空气横掠顺列螺旋槽管和光管管束的传热特性[J].动力工程,2005,25(1):44-49.
[21] 胡骏.航空叶片机原理[M].2版.北京:国防工业出版社,2014.

备注

引言

1 PATR发动机系统分析

2 基于控制规律的PATR速度特性

3 基于控制规律的PATR高度特性

4 结论

期刊信息