XTER内收缩组合进气道设计理念及气动特性

蔡泽君; 胡占仓; 余联郴; 洪唐宝; 朱呈祥; 尤延铖

doi:10.7638/kqdlxxb-2021.0393

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XTER内收缩组合进气道设计理念及气动特性

专栏——吸气式组合动力 | 更新时间：2026-05-28

- XTER内收缩组合进气道设计理念及气动特性
- Design concept and aerodynamic characteristics of XTER TBCC inlet
- 空气动力学学报 2022年40卷第1期页码：218-231
- 作者机构：
  
  厦门大学航空航天学院,厦门,361000
- 作者简介：
  
  蔡泽君（1997-），男，福建泉州人，硕士研究生，研究方向：高超声速进气道设计. E-mail：zejuncai@stu.xmu.edu.cn
  尤延铖*，教授，博导，研究方向：高超声速空气动力学，内流流体力学，高超声速进气道设计，复杂湍流数值模拟（LES/DES），CFD计算数值方法研究等. E-mail：yancheng.you@xmu.edu.cn
- 基金信息：
  
  国家自然科学基金（U20A3069，U21B6003）
- DOI：10.7638/kqdlxxb-2021.0393
  中图分类号： V236
- 纸质出版：2022
- 稿件说明：
移动端阅览
蔡泽君, 胡占仓, 余联郴, 等. XTER内收缩组合进气道设计理念及气动特性[J]. 空气动力学学报, 2022, 40(1): 218−231.

CAI Zejun, HU Zhancang, YU Lianchen, et al. Design concept and aerodynamic characteristics of XTER TBCC inlet[J]. 2022, 40(1): 218-231.
蔡泽君, 胡占仓, 余联郴, 等. XTER内收缩组合进气道设计理念及气动特性[J]. 空气动力学学报, 2022, 40(1): 218−231. DOI： 10.7638/kqdlxxb-2021.0393

CAI Zejun, HU Zhancang, YU Lianchen, et al. Design concept and aerodynamic characteristics of XTER TBCC inlet[J]. 2022, 40(1): 218-231. DOI： 10.7638/kqdlxxb-2021.0393.

摘要

组合循环发动机的进气道特性是决定整体方案可行性的关键因素之一。本文针对XTER（Xiamen Turbine Ejector Ramjet）组合动力总体需求，详细梳理了XTER内收缩组合进气道的设计理念及设计要素，在此基础上重点分析了该组合进气道的流动结构及特性规律。结果表明，XTER组合进气道各设计要素及设计约束相互耦合，分流调节机构是组合进气道设计的核心，其设计难度高且使设计要素的相互制约问题更为突出。在全速域马赫数0～6范围内，XTER内收缩组合进气道的流动结构差异显著，但总流量系数均维持在0.75以上，有效保障了组合发动机的流量捕获，且分流调节机构能够实现模态转换过程中流量的平稳过渡。在马赫数2.5涡轮-引射亚燃模态转换过程中，引射亚燃通道及超燃通道总压恢复均稳定上升，在模态转换完成时总压恢复均接近或超过0.85。在区间马赫数3～4.5的引射亚燃-超燃模态转换过程中，进气道总流量系数由0.81提升至0.90，引射亚燃通道在前62.5%的进程中保持较高的总压恢复性能，表明该通道在前半程的模态转换过程中仍具有较强的工作能力。综合来看，XTER内收缩组合进气道的气动特性能够满足动力方案总体需求，全速域范围内流量系数变化缓和，模态转换过程中通道性能过渡平稳，具备宽速域连续正常工作能力。

Abstract

The performance of inlets is critical to combined cycle engines. Aiming at the overall demand of Xiamen Turbine Ejector Ramjet (XTER)

the design concept and design elements of the inward-turning Turbine Based Combined Cycle (TBCC) inlet for XTER are reviewed in detail. On this basis

flow structures and characteristics of the inlet are analyzed. Results show that either design elements or design constraints of the XTER inlet are coupled with each other

and the mass modulation mechanism is the core element

which is

however

difficult to design and makes the mutual restriction among design elements more complicated. Flow structures in the XTER inlet vary significantly with the increase of Mach number from 0 to 6. Nevertheless

the total mass flow rate remaines above 0.75

which meets the mass flow demand. The mass distribution mechanism also helps the flow mass varies smoothly during mode transitions. During the turbine-to-ejector transition at Mach 2.5

the total-pressure recovery coefficients of the ejector and scramjet increase steadily. Once the transition ends

the total-pressure recovery coefficient is close to or above 0.85. As to the ejector-to-scramjet transition at Mach 3-4.5

the mass flow rate of the inlet increases from 0.81 to 0.90. Moreover

the ejector tunnel maintains a high total-pressure recovery coefficient in the first 62.5% process

indicating that this tunnel still performs properly in the first half of mode transition process. Taken together

the XTER inlet it is capable of continuous normal operation in a wide speed range since its aerodynamic characteristics meet the demand of power system

i.e.

the mass flow rate varies moderately in the full speed range and the tunnel performance transits smoothly in the mode transition process.

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