非对称来流条件下超燃冲压发动机隔离段气动特性研究
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摘要
隔离段是超燃冲压发动机的一个重要气动部件。超声、高超声速进气道/隔离段一体化设计必须考虑进气道出口流场的影响,隔离段的气动特性研究应该在真实的、或者模拟的进气道出口流场下进行。
本文采用试验研究、数值模拟和理论分析相结合的方法对非对称超声速来流条件下隔离段流动进行了研究,设计了针对非对称超声来流矩形隔离段流场研究的直联式试验风洞,在模拟进气道出口流场的各种非对称进口条件下进行了吹风试验。以试验研究、基础性分析为主,辅以 CFD 数值模拟,利用获得的实验数据,对隔离段内流场进行了分析。对非对称进口条件下和对称进口条件下的隔离段流动状态进行了比较;研究了非对称进口条件下隔离段的设计方法;探索了非对称进口条件下提高隔离段耐受反压能力的措施以及在相同的反压和出口参数下,缩短隔离段长度的方法;最后还研究了在相同截面当量直径的前提下,不同截面形状对隔离段内激波串形状、长度的影响。
研究结果表明:随隔离段进口流动非对称程度的增加,激波串长度增加、隔离段耐受反压的能力下降,出口截面总压分布、马赫数分布也随之发生变化。在考虑隔离段进口流动非对称影响的基础上,对 Waltrup 的公式进行了改进,提高了激波串长度预测的精确程度。在隔离段进口非对称来流条件下,采用弯曲隔板,在不降低承受反压能力的条件下,可以将隔离段长度缩短 1/3左右,隔板的上弯高度随隔离段进口底板附面层厚度的增加而增加。对于非轴对称发动机内流通道,八边形隔离段是一个较好的选择,它可以缓解矩形隔离段角流区所造成的低速区影响,既缩短了隔离段长度,又没有增加管内的总压损失。
In order to simulate the actual flowfield at the exit of supersonic/hypersonic inlet, the flow in scramjet isolator is investigated under asymmetric incoming flow.
A wind tunnel is designed under asymmetric incoming flow and the compression fields in the isolator have been investigated using wall static and pitot pressure measurements, schlieren photography. Three incoming Mach numbers are considered, Mach 1.5, Mach 1.8 and Mach 2. To understand further the test data, the numerical simulations are performed with the Reynolds-averaged Navier-Stokes solver using the SST k ?ω turbulence model. The flow characteristics under asymmetric incoming flow are compared with that under symmetric incoming flow. The studies on the design method and length reduction of the isolator under asymmetric incoming flow are conducted. In the end, the geometric effects of cross-sectional shape on shock train in constant area isolators are analyzed.
The results indicate that the asymmetric velocity distribution at isolator entrance induces significant asymmetric shock structure in isolator and non-uniform flowfield at the isolator exit. The increase of the asymmetry of the flow at isolator entrance will lead to the increase of the shock train length in isolator for a given pressure ratio. Based on an analysis of flow asymmetry effect at isolator entrance on shock train length, a modified correlation is proposed to calculate the length of shock train. The predicted results of the proposed correlation show good agreement with experimental results. By using the curve spacer in isolator, the overall length of the isolator could be reduced by 33 per cent without loss in static and total pressure recovery when the lower wall boundary layer thickness δ/Η is equal to 0.24 and the upper wall boundary layer thickness δ/Η is zero at the isolator entrance. For those non-axisymmetric engine flowpaths of airbreathing vehicles, the octangular isolator is a good choice, which reduces the isolator length without the increase of total pressure loss. The octagon cross section reduces successfully the low-momentum flow area in the corners found in the rectangular cross section.
本文采用试验研究、数值模拟和理论分析相结合的方法对非对称超声速来流条件下隔离段流动进行了研究,设计了针对非对称超声来流矩形隔离段流场研究的直联式试验风洞,在模拟进气道出口流场的各种非对称进口条件下进行了吹风试验。以试验研究、基础性分析为主,辅以 CFD 数值模拟,利用获得的实验数据,对隔离段内流场进行了分析。对非对称进口条件下和对称进口条件下的隔离段流动状态进行了比较;研究了非对称进口条件下隔离段的设计方法;探索了非对称进口条件下提高隔离段耐受反压能力的措施以及在相同的反压和出口参数下,缩短隔离段长度的方法;最后还研究了在相同截面当量直径的前提下,不同截面形状对隔离段内激波串形状、长度的影响。
研究结果表明:随隔离段进口流动非对称程度的增加,激波串长度增加、隔离段耐受反压的能力下降,出口截面总压分布、马赫数分布也随之发生变化。在考虑隔离段进口流动非对称影响的基础上,对 Waltrup 的公式进行了改进,提高了激波串长度预测的精确程度。在隔离段进口非对称来流条件下,采用弯曲隔板,在不降低承受反压能力的条件下,可以将隔离段长度缩短 1/3左右,隔板的上弯高度随隔离段进口底板附面层厚度的增加而增加。对于非轴对称发动机内流通道,八边形隔离段是一个较好的选择,它可以缓解矩形隔离段角流区所造成的低速区影响,既缩短了隔离段长度,又没有增加管内的总压损失。
In order to simulate the actual flowfield at the exit of supersonic/hypersonic inlet, the flow in scramjet isolator is investigated under asymmetric incoming flow.
A wind tunnel is designed under asymmetric incoming flow and the compression fields in the isolator have been investigated using wall static and pitot pressure measurements, schlieren photography. Three incoming Mach numbers are considered, Mach 1.5, Mach 1.8 and Mach 2. To understand further the test data, the numerical simulations are performed with the Reynolds-averaged Navier-Stokes solver using the SST k ?ω turbulence model. The flow characteristics under asymmetric incoming flow are compared with that under symmetric incoming flow. The studies on the design method and length reduction of the isolator under asymmetric incoming flow are conducted. In the end, the geometric effects of cross-sectional shape on shock train in constant area isolators are analyzed.
The results indicate that the asymmetric velocity distribution at isolator entrance induces significant asymmetric shock structure in isolator and non-uniform flowfield at the isolator exit. The increase of the asymmetry of the flow at isolator entrance will lead to the increase of the shock train length in isolator for a given pressure ratio. Based on an analysis of flow asymmetry effect at isolator entrance on shock train length, a modified correlation is proposed to calculate the length of shock train. The predicted results of the proposed correlation show good agreement with experimental results. By using the curve spacer in isolator, the overall length of the isolator could be reduced by 33 per cent without loss in static and total pressure recovery when the lower wall boundary layer thickness δ/Η is equal to 0.24 and the upper wall boundary layer thickness δ/Η is zero at the isolator entrance. For those non-axisymmetric engine flowpaths of airbreathing vehicles, the octangular isolator is a good choice, which reduces the isolator length without the increase of total pressure loss. The octagon cross section reduces successfully the low-momentum flow area in the corners found in the rectangular cross section.
引文
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