火箭推进

以双通道涡轮/冲压组合发动机为例,在不影响涡轮通道工作状况条件下,研究了低速段冲压通道富余气流处理方式对发动机阻力特性影响。采用动量定理与壁面积分两种方法对比了冲压通道开启与关闭两种方案下发动机总体受力情况,提出了一种冲压通道冷态尾喷管节流减阻措施。研究表明:两种受力分析方法结果一致,均能准确评估发动机受力; 相比于冲压通道关闭、气流高速绕过发动机的情况,冲压通道开启状态下,进气道溢流阻力小,即富余高速气流经冲压通道减速后,直接排出发动机所产生的阻力更低,且来流马赫数越低,两种方案的阻力差距越大; 此外,合理控制冲压通道下游尾喷管喉道面积,降低冲压通道内的流速对发动机总体有明显减阻效果, Ma∞=0.8、1.0时减阻最为明显,最高减阻54.0。

The effect of excess flow on drag characteristics of turbine based combined cycle engine was studied at low speeds, when the working conditions of the turbine channel were not affected.Both momentum theorem and wall force integral method were adopted to analyze the overall forces of an engine.By comparing the schemes of opening and closing ramjet channel, a drag reduction approach by adjusting the ramjet nozzle throat area in cold state was presented.The study indicates that the two analytical methods have consistent results, evaluating the force of engine accurately.The spillage drag is lower when the ramjet channel keeps open than closed.The drag will be further reduced when the high-speed surplus air was decelerated passing through ramjet channel, and the drag disparity between two schemes becomes greater when the incoming Mach number decreases.In addition, there are also significant drag reduction effect by controlling the downstream nozzle throat area and slowing down theair speed in ramjet channel.A maximum drag reduction of 54 was achieved at freestream Mach number 0.8 and 1.0.

引言
1 发动机进气道设计及低马赫数下气流走向
2 数值模拟方法
3 计算结果及数据分析
4 结论

图1 Ma∞=2.0状态气动型面<br/>Fig.1 Aerodynamic configuration of Ma∞=2.0

图1 Ma∞=2.0状态气动型面
Fig.1 Aerodynamic configuration of Ma∞=2.0

图2 变几何调节原理<br/>Fig.2 Principle of variable geometry

图2 变几何调节原理
Fig.2 Principle of variable geometry

图3 CFD计算域<br/>Fig.3 Computational domain

图3 CFD计算域
Fig.3 Computational domain

图4 近壁面网格加密示意图<br/>Fig.4 The densed near-wall meshs

图4 近壁面网格加密示意图
Fig.4 The densed near-wall meshs

表1 计算来流条件<br/>Tab.1 Free stream condition of numerical simulation

表1 计算来流条件
Tab.1 Free stream condition of numerical simulation

图5 轴对称进气道模型(单位:in)<br/>Fig.5 Model of an axisymmetric inlet(unit:in)

图5 轴对称进气道模型(单位:in)
Fig.5 Model of an axisymmetric inlet(unit:in)

图6 数值计算与实验结果对比<br/>Fig.6 Comparison between numerical and experimental results

图6 数值计算与实验结果对比
Fig.6 Comparison between numerical and experimental results

图7 喉道总压恢复系数随总网格量变化规律<br/>Fig.7 The relationship between total pressure recovery coefficient and mesh quantity

图7 喉道总压恢复系数随总网格量变化规律
Fig.7 The relationship between total pressure recovery coefficient and mesh quantity

图8 冲压通道开启/关闭状态下进气道流场图(左:工况1; 右:工况2)<br/>Fig.8 Mach number contours of 2 cases at different free stream Mach number(left:case 1; right:case 2)

图8 冲压通道开启/关闭状态下进气道流场图(左:工况1; 右:工况2)
Fig.8 Mach number contours of 2 cases at different free stream Mach number(left:case 1; right:case 2)

图9 冲压通道开启/关闭状态下涡轮通道出口性能参数对比<br/>Fig.9 Comparison of turbine channel exit performance under different conditions

图9 冲压通道开启/关闭状态下涡轮通道出口性能参数对比
Fig.9 Comparison of turbine channel exit performance under different conditions

图10 发动机流管控制体<br/>Fig.10 Stream control volume of engine

图10 发动机流管控制体
Fig.10 Stream control volume of engine

表2 两种受力分析方式计算结果对比<br/>Tab.2 Comparison of two force analyses

表2 两种受力分析方式计算结果对比
Tab.2 Comparison of two force analyses

图11 开启/关闭冲压通道发动机受力系数对比<br/>Fig.11 Force coefficient of 2 cases at different free stream Mach number

图11 开启/关闭冲压通道发动机受力系数对比
Fig.11 Force coefficient of 2 cases at different free stream Mach number

图12 冲压通道下游节流流场<br/>Fig.12 Flow fields of ramjet channel at different free stream Mach number

图12 冲压通道下游节流流场
Fig.12 Flow fields of ramjet channel at different free stream Mach number

表3 不同来流马赫数下喷管喉道面积<br/>Tab.3 Nozzle throat area at different free stream Mach number

表3 不同来流马赫数下喷管喉道面积
Tab.3 Nozzle throat area at different free stream Mach number

图13 冲压通道下游节流前后受力对比<br/>Fig.13 Force coefficient of downstream throttling at different free stream Mach number

图13 冲压通道下游节流前后受力对比
Fig.13 Force coefficient of downstream throttling at different free stream Mach number

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备注

引言

1 发动机进气道设计及低马赫数下气流走向

2 数值模拟方法

3 计算结果及数据分析

4 结论

期刊信息