等截面超-超引射器流场结构及引射性能

为考察超声速引射器直接引射超声速二次流时的性能,采用纹影技术和压力测量手段对一等截面超-超引射器的流场结构及其引射性能进行了实验研究。研究结果表明:一、二次流交汇后在混合室前段形成了复杂的超声速流场结构。根据二次流在混合室入口流动状态的不同,可将超-超引射划分为非饱和超-超引射和饱和超-超引射两种工作状态;二次流在混合室入口处产生的激波提高了引射器的压力匹配性能;在给定的引射系数下,引射器的增压性能随二次流马赫数的增大而降低,而引射马赫数对引射器压力恢复性能的影响不大。     

二维超-超引射器混合室流场特性

搭建了二维超-超引射器实验系统,进行了二次喉道型式引射器启动特性和负载特性实验,获得了引射器混合室内流场纹影图,结果表明:超声速引射器临界启动状态下,混合室内存在反压引起的激波系;引射器完全启动状态下,主激波系可始于混合室后段,无需被完全吞入二次喉道内;二次流对引射器启动有助推效果,可使混合室内激波系后移;一次流对二次流有压缩作用,且一次流工作压力越高,压缩作用越强;一次流、二次流之间会形成明显的混合层,当一次流、二次流静压不匹配时,一次流喷管出口内端壁处将形成较强斜激波,其在固壁与混合层之间反射、交叉,并向下游延伸,会降低一次流引射性能。     

引射喷管工作特性计算方法

一、前言 引射喷管可看成是一个截短的引射器,其原理相仿,故理论可互相借鉴。关于引射喷管或引射器的理论很多,但尚有未尽之争:(1)多数文献(包括三元流特性线法)假设初始段内次流等熵,但试验发现有很多情况堵塞状态下次流总压P_s~*小于环境压力P_H及该     

变截面超-超引射器启动特性数值研究

为研究不同结构参数与来流参数下变截面超-超引射器的启动特性,用于指导超-超引射器设计与工况调试,采用二维雷诺平均Naiver-Stokes方程,数值研究了引射器混合室不同收缩比、一次流和二次流的不同总压比、总温比下超-超引射器的启动规律,并定义了“启动系数”来判别超-超引射流场是否建立。研究结果表明:随着收缩比（范围0.7～0.9）的增加,超-超引射器启动的临界总压比、总温比均先降低后升高,收缩比0.8时,存在最佳总压比5.88,最佳总温比0.21。结构参数一定,超-超引射器随总温比升高启动难度增加。当超-超引射器处于启动状态下,室压不随总温比、总压比变化而变化,引入的启动系数较引射系数可不依赖具体工况而直接判别超-超引射器是否启动。     

两段式喷嘴对CO_2两相流引射制冷系统性能的影响

文章对采用两段式喷嘴的引射器及其两相流引射制冷系统在不同工况、不同几何尺寸条件下进行了实验研究。实验结果表明,在实验工况固定的条件下,采用两段式喷嘴的CO_2两相流引射制冷系统的COP随引射器第一喉部直径的增大而增大,引射比随第一喉部直径的增大而减小;系统COP和引射比随引射器中间连接直径的增大而减小。对于固定几何尺寸的引射器,系统COP随气冷器出口压力的升高而增大,引射比随气冷器出口压力的升高先减小后增大,在9MPa时引射比最小。与传统的CO_2制冷系统相比,采用两段式喷嘴的CO2两相流引射制冷系统的COP在不同工况的条件下均高于传统系统的COP,最大可提高约15%。     

直排型DF/HF化学激光器双喷管模型启动特性

 建立了一套直排型DF/HF化学激光器气流通道双喷管小型实验装置,通过选择不同副气流总压（模拟燃烧室气流）进行实验,研究了副气流总压对双喷管实验装置启动特性的影响。实验结果表明：随着副气流总压的增大,装置的启动压力降低,盲腔条件下的启动压力明显高于有副气流时的启动压力。因此,先通入燃烧室气流,再开通引射气流,对直排型连续波DF/HF化学激光器的启动是有利的。采用1维处理方法,建立了从引射气流喷管入口、副气流喷管入口到扩压器出口的理论模型,得到了与实验一致的规律。由于1维理论中采用了一些近似处理,实际启动压力比理论数据高20%～31%。     

改进的CO_2两相流引射制冷系统性能实验研究

为了进一步优化系统,提升引射比,重新设计并制造了汽液分离器,将其增设于系统引射器之前,测试了不同工况下引射器及系统的性能,并将实验结果与传统系统进行了比较。实验证实,系统增设初级汽液分离器后可使引射效果得到提升,使主引射流以近乎单相流的状态进入引射器,从而使引射比增大,使制冷量和COP得到提高。当系统在只改变蒸发温度的工况下正常运行时,引射比可得到约22.4%～66.4%的提高,在蒸发温度为-2℃～3℃范围内,COP提高了约2%～26.9%;当系统在只改变气冷器出口温度的工况下正常运行时,系统COP可提高约1%～19%,在气冷器出口压力约为8.75 MPa时,系统性能达到最佳且引射比最大。     

单级超声气体引射器

对中心引射式单级超声气体引射器的主要结构参数,进行调节,即可获得较佳的引射性能;在本实验所采用的各种喷管中,当=1.3-2.17,=3-5时,高真空度的引射性能较好,改变一、二次气流温度,n θ~(1/2)基本保持为常数,并联引射器可以保持单个引射器的性能。     

CO_2两相流引射循环制冷系统性能的数值模拟

对引射器内部简化热力学模型进行了改进,建立了CO2两相流制冷系统的数学模型。利用MATLAB语言编写程序对该系统性能进行了模拟计算,分析了工况参数及引射比对引射循环系统性能的影响。模拟结果表明:CO2两相流引射循环制冷系统在较低的引射比条件下,就可以实现稳定运行,系统COP对气冷器出口温度的变化比较敏感,同时存在最优高压侧压力使系统COP达到最大;对于不同工况条件,CO2两相流引射循环制冷系统的COP比同工况条件下的传统系统的COP,理论上分别提高了11%～18%。     

两段式喷嘴引射器制冷循环系统性能的实验研究

使用两段式喷嘴的引射器可以将喷嘴中较大的制冷剂液滴破碎,从而有效提高两相流引射器及制冷系统的效率。以R134a为工质,对采用两段式喷嘴引射器的两相流引射制冷系统进行了实验研究,重点分析了固定工况下喷嘴的几何尺寸对引射比及系统性能的影响。结果表明,随着引射器喷嘴第一喉部面积的增加,其引射比逐渐增大,系统COP整体上呈上升趋势;随着引射器喷嘴第二喉部面积的增加,引射比也逐渐增大,而系统COP先升高后降低,在第二喉部面积为2.83mm2时达到最大值;较小的第一段喷嘴扩张角可显著提高引射器的引射比。     

Visualization of secondary flow choking phenomena in a supersonic air ejector

The present study deals with the visualization of the air flow inside a supersonic ejector. Our attention is more precisely focused on the choked flow phenomenon which occurs along the mixing chamber of the secondary nozzle and which can be visualized by CFD. Laser tomography visualizations are used to validate the CFD model. The evolution of flow configuration in the ejector with the primary stagnation pressure is examined both in the case of zero secondary flow and in the case of free entrainment of induced air.     

Supersonic diffuser for pressure recovery in SCOIL system

Classical supersonic chemical oxygen iodine laser (SCOIL) systems operate under a low total pressure of nearly 18 Torr (2400 Pa) with cavity pressure being in the range 3 Torr (400 Pa) and Mach number of 1.7. These systems handle high flow rates and hence an efficient supersonic diffuser (SD) is a critical first step towards an open-cycle operation, which may be followed by a multi-stage ejector system. The present study discusses the various aspects in the design of a supersonic diffuser for a twin 10 kW COIL module source which employs flow rates of 100 gs⁻¹ in each module. The results of computational studies based on 3-D, viscos compressible flow, k-ε turbulence formulation for the supersonic diffuser geometry have also been discussed. The experimental results from a single-module test of the supersonic diffuser show that a total recovered pressure of nearly 7 Torr is achieved at the diffuser exit.     

等压混合引射器设计与实验研究

 采用1维处理方法，建立了便于设计人员使用的等压混合引射器性能计算分析与工程设计方法，并详细分析了等压混合引射器各主要参数对性能的影响。该分析方法基于气体焓的变化，因此可应用于各种引射气体与被引射气体。为了控制尺寸，还首次将多喷嘴引射方式与等压混合结合起来。实验结果验证了等压混合引射器性能计算分析与工程设计方法的可靠性以及多喷嘴引射方式应用于等压混合引射器的可行性。     

Realization of an advanced nozzle concept for compact chemical oxygen iodine laser

Conventional supersonic chemical oxygen–iodine lasers (SCOIL) are not only low-pressure systems, with cavity pressure of 2–3 Torr and Mach number of approximately 1.5, but also are high-throughput systems with a typical laser power per unit evacuation capacity of nearly 1 J/l, thus demanding high capacity vacuum systems which mainly determine the compactness of the system. These conventional nozzle-based systems usually require a minimum of a two-stage ejector system for realization of atmospheric pressure recovery in a SCOIL. Typically for a 500 W class SCOIL, a first stage requires a motive gas flow (air) of 120 gm/s to entrain a laser gas flow of 3 g/s and is capable of achieving the pressure recovery in the range of 60–80 Torr. On the other hand, the second stage ejector requires 4.5 kg/s of motive gas (air) to achieve atmospheric pressure recovery. An advanced nozzle, also known as ejector nozzle, suitable for a 500 W-class SCOIL employing an active medium flow of nearly 12 g/s, has been developed and used instead of a conventional slit nozzle. The nozzle has been tested in both cold as well as hot run conditions of SCOIL, achieving a typical cavity pressure of nearly 10 Torr, stagnation pressure of approximately 85 Torr and a cavity Mach number of 2.5. The present study details the gas dynamic aspects of this ejector nozzle and highlights its potential as a SCOIL pressure recovery device. This nozzle in conjunction with a diffuser is capable of achieving pressure recovery equivalent to a more cumbersome first stage of the pressure recovery system used in the case of a conventional slit nozzle-based system. Thus, use of this nozzle in place of a conventional slit nozzle can achieve atmospheric discharge using a single stage ejector system, thereby making the pressure recovery system quite compact.     

The surface roughness effect on the performance of supersonic ejectors

The paper presents the numerical simulation results of the surface roughness influence on gas-dynamic processes inside flow parts of a supersonic ejector. These simulations are performed using two commercial CFD solvers (Star- CCM+ and Fluent). The results are compared to each other and verified by a full-scale experiment in terms of global flow parameters (the entrainment ratio: the ratio between secondary to primary mass flow rate - ER hereafter) and local flow parameters distribution (the static pressure distribution along the mixing chamber and diffuser walls). A detailed comparative study of the employed methods and approaches in both CFD packages is carried out in order to estimate the roughness effect on the logarithmic law velocity distribution inside the boundary layer. Influence of the surface roughness is compared with the influence of the backpressure (static pressure at the ejector outlet). It has been found out that increasing either the ejector backpressure or the surface roughness height, the shock position displaces upstream. Moreover, the numerical simulation results of an ejector with rough walls in the both CFD solvers are well quantitatively agreed with each other in terms of the mean ER and well qualitatively agree in terms of the local flow parameters distribution. It is found out that in the case of exceeding the “critical roughness height” for the given boundary conditions and ejector’s geometry, the ejector switches to the “off-design” mode and its performance decreases considerably.     

超声速转子叶片非定常引射器流场特性数值模拟

采用计算流体力学方法,结合适当的边界条件,对超声速转子叶片非定常引射器进行了模拟。从结果可以看出:此类引射器内流态复杂,主气流出口斜激波干扰现象明显,叶片设计参数对引射器性能影响很大。叶片尾部的膨胀波有效诱导了被引射气流,在短距离内增强了气流混合,湍流效应对引射器性能的影响较小;叶片可维持自旋转,提升叶片转速可增强引射效率。最后,对引射器内的流动机理进行了探讨。     

Ejectors for pressure recovery systems of supersonic chemical lasers

Results of a numerical study of performance characteristics of supersonic ejectors with nozzles of different types are reported. The work was carried out with the aim of developing a high-performance ejector for pressure recovery systems of supersonic chemical lasers. A specific feature of the operation of ejectors in pressure recovery systems consists in that, in this case, the ejecting and ejected gases, as they undergo mixing, have different thermodynamic properties, and the ejection coefficient depends on the ratio between the temperatures of the gases and on the ratio of their molecular masses. Since the operation of an ejector is based on the mixing process, the task consisted in intensification of this process using nozzles of special geometries. The performance of ejectors was judged considering an integral parameter, the product of induction by compression ratio. The calculations of the 3D viscous gas flow in the ejector channel were performed using ANSYS software. In verifying the numerical model, a comparison with experimental data obtained earlier on a model ejector facility and during tests of real pressure recovery systems in operation with supersonic chemical lasers was performed.