混合工质充注量/配比对自复叠制冷循环特性影响

混合工质充注量、混合工质配比以及外界环境温度是自复叠制冷循环工作特性重要影响因素.本文提出新的定密度法研究变工况下自复叠制冷循环的工作特性.建立了组成系统部件热力学数学模型,分析了混合工质充注量、混合工质配比以及外界环境温度等参数对自行复叠制冷循环的工作特性影响,并得出有指导意义结论.     

换热器预冷的空气涡轮火箭性能分析研究

为了准确地分析以不同燃料为冷质的换热器预冷空气涡轮火箭发动机的性能,本文建立了可考虑工质组分化学平衡与工质热物性随温度和压力变化的热力循环模型。利用该模型分析了以LH2、LCH4和煤油为燃料的发动机循环性能,研究了预热温度、燃气发生器和主燃室出口温度对循环性能的影响。结果表明,换热器预冷能够降低压气机进口温度,减小相同增压比下的压缩功,提高燃料温度,减小推进剂流量,从而减小燃空比,增加比冲;燃料预热温度的提高可减小燃气发生器氧燃比,进而减小燃空比、增大比冲;较低的燃气发生器和主燃烧室出口温度可降低燃空比,提高比冲,但会造成单位推力的下降。同时,研究结果还表明,与LCH4和煤油相比,LH2的比热容与热值的比值最大,采用LH2预冷的发动机的飞行速度和比冲的增幅也最大,说明比热容与热值的比值越大,相应的预冷效果越好,即可依据燃料比热容与热值的比值定性衡量发动机的预冷效果。     

非共沸混合工质分凝式双温制冷系统间歇运行特性的实验研究

在传统串联式双温制冷系统的基础上,本文借助非共沸混合工质分凝时的组分偏移特性,引入了混合工质中间分凝式双温制冷循环。搭建了自然非共沸混合工质分凝式双温循环系统的实验台,选用R290/R600a混合物作为制冷工质,通过实验的方法研究了自然非共沸混合工质分凝式双温制冷系统在实际工况下的开停机间歇运行特性,探讨了制冷剂充注量、制冷剂组分、环境温度等参数对系统性能的影响规律。结果表明压缩机开机阶段的平均功率随着制冷剂的充注量增加而升高,其在开停机间歇性运行周期内的开机率随充注量的增加而先下降后升高;充注量为300 g且R600a的配比为50%时压缩机耗电量达到最小值1.60 k Wh·d^-1;环境温度的升高会影响冷凝器的换热效果还会造成系统中间室的热负荷增加,压缩机的开机率和耗电量均会明显升高。     

基于粒子群算法的跨临界有机朗肯循环性能优化及工质筛选

本文针对跨临界有机朗肯循环进行了热力计算,并根据工质的热物性与环保性能以及对应循环的热力学性能等因素,经过一系列筛选过程最终优选出了10种综合性能较好的跨临界有机朗肯循环工质。热力计算结果表明,部分有机工质对应的跨临界朗肯循环的效率随膨胀机进口温度或蒸发压力的变化存在最优值。基于此,本文进一步采用粒子群算法(Particle Swarm Optimization,PSO)对所选有机工质的跨临界朗肯循环性能进行了优化分析。优化结果表明,在所筛选的10种跨临界有机朗肯循环工质中非制冷剂工质propylene的综合性能最好,propane次之;而制冷剂工质中R143a的综合性能较好。     

基于AR功率谱的振荡热管循环运行特性分析

本文可视化实验观测了振荡热管在准稳定运行状态下管内工质的循环运行模式,并引入现代自回归(AR)模型功率谱分析方法分析了两种工质循环运行模式下振荡热管壁温振荡信号的频谱特性。研究表明:不同循环运行模式下振荡热管各工作段壁温的时域振荡信号各具特征,其AR功率谱密度图能够有效反映振荡热管循环运行的频谱特性并提取壁温时域振荡信号中的主频信息,它可以成为辨识振荡热管内工质循环运行模式的有效工具。     

混合工质内复叠节流制冷机的分析及初步实验研究

本文对采用多元非共沸混合物工质的内复叠节流制冷循环进行了热力分析.采用分析的方法对制冷循环各部件进行了分析,同时比较了混合工质一次节流循环和内复叠循环热力性能.同时文章报道了混合工质内复叠节流制冷机的初步整机性能测试实验结果.     

自复叠制冷循环中混合工质泄漏性能的研究

尽管自复叠制冷循环越来越广泛的用于深冷及普冷领域,对于循环中工质泄漏特性的研究却较少。以非共沸混合工质两相区的等温泄漏为基础,分析了在自复叠循环装置中各部件的泄漏对工质组成的影响,其中发生在冷凝器出口处、气液分离器和蒸发器出口处的泄漏对工质组成影响较大。以采用非共沸混合工质R600 a/CO2的自复叠低温冷冻箱为例,研究了不同泄漏点不同泄漏率的泄漏特性。结果说明当工质泄漏时混合工质组成和循环性能发生变化,在蒸发器出口处的泄漏对循环性能影响最大;当泄漏引起循环工质组成发生较大变化时,压缩机变容量和变压力比调节能力明显降低,此时系统不能满足设计工况的要求,工作性能变差。     

二元环保型混合工质一次分凝循环性能优化

应用定循环运行压比优化方法,对采用环保型二元混合工质的单级压缩一次分凝循环,进行了-60℃温度位的循环性能数值优化。计算结果表明,影响循环COP的因素有混合工质成分(工质组元、工质浓度)和循环压力位(循环低压和循环压比),必须综合考虑进行优化。不可燃混合工质R23/R134a、R23/R227ea和R23/R236ea中,R23摩尔浓度为0.55和0.6的R23/R236ea循环在压比为7和10时,分别有最大的COP;自然混合工质R170/R290、R170/R600a和R170/R600中,R170摩尔浓度为0.65和0.7的R170/R600循环在压比为7和10时,分别有最大的COP。     

不可逆自旋量子制冷循环参数的优化设计

基于量子主方程和半群逼近方法，研究以许多无相互作用的自旋-1/2系统为工质的、由两个绝热和两个等磁场过程组成的不可逆量子制冷循环的一般性能特性。导出循环的性能系数、制冷率和输入功率等重要性能参数的表达式。应用数值求解，对受有限循环时间约束的制冷率进行了优化，计算了最大制冷率和相应的最佳性能参数，确定了性能系数的最佳区域和工质温度及两个等磁场过程时间的优化范围。进而详细分析了高温下循环的优化性能，所得结果被进一步推广，以致可直接用来描述由自旋-J系统为工质的量子制冷循环的性能。     

低温热能有机朗肯循环工质选择及性能分析

工质的性能是影响有机朗肯循环性能的重要因素之一。基于工质热力性质、环保性等要求,选择R123、R600a、R601a、R245fa、R236ea、R245ca、R142b及R601作为循环工质,在不同的蒸发温度下,对其热力循环性能进行计算分析,从热效率、系统净输出功、效率等方面进行比较。结果表明:R123是适合低温热能有机朗肯循环系统的循环工质。同时研究分析了膨胀机进口温度和进口压力对系统性能的影响,发现工质以饱和蒸汽状态进入膨胀机膨胀做功,可以使系统性能达到最佳。     

Thrust characteristics of an airbreathing pulse detonation engine in supersonic flight at various altitudes

The main thrust characteristics, such as thrust force, specific impulse, specific fuel consumption, and specific thrust, of a pulse detonation engine (PDE) with an air intake and nozzle in conditions of flight at a Mach number of 3 and various altitudes (from 8 to 28 km above sea level) are for the first time calculated with consideration given to the physicochemical characteristics of the oxidation and combustion of hydro-carbon fuel (propane), finite time of turbulent flame acceleration, and deflagration-to-detonation transition (DDT). In addition, a parametric analysis of the influence of the operation mode and design parameters of the PDE on its thrust characteristics in flight at a Mach number of 3 and an altitude of 16 km is performed, and the characteristics of engines with direct initiation of detonation and fast deflagration are compared. It is shown that a PDE of this design greatly exceeds an ideal ramjet engine in specific thrust, whereas regarding the specific impulse and specific fuel consumption, it is not inferior to the ideal ramjet.     

Performance of a two-state quantum engine improved by the superposition effect

The performance of a two-state quantum engine under different conditions is analyzed.It is shown that the efficiency of the quantum engine can be enhanced by superposing the eigenstates at the beginning of the cycle.By employing the finite-time movement of the potential wall,the power output of the quantum engine as well as the efficiency at the maximum power output(EMP) can be obtained.A generalized potential is adopted to describe a class of two-level quantum engines in a unified way.The results obtained show clearly that the performances of these engines depend on the external potential,the geometric configuration of the quantum engines,and the superposition effect.Moreover,it is found that the superposition effect will enlarge the optimally operating region of quantum engines.     

斜爆轰发动机流动机理分析

为了研究高Mach数超燃冲压发动机和斜爆轰发动机的内流场燃烧流动机理，首先用CJ爆轰理论对超燃冲压发动机的内流场特性进行了理论分析，给出了燃烧室流场的气动规律，理论分析结果与现有实验结果吻合得非常好.其次，根据理论分析结果，提出了高Mach数超燃冲压发动机和斜爆轰发动机的气动设计原则.最后，根据提出的气动设计原则，设计了高Mach数斜爆轰发动机，飞行Mach数为9，对斜激波诱导燃烧机理开展了二维数值模拟研究.数值模拟结果表明，在高Mach数下，斜爆轰发动机燃烧室内可以得到稳定的燃烧流场.      

带有Dzyaloshinski-Mariya相互作用的两比特纠缠量子Otto热机和量子Stirling热机

研究了以带有Dzyaloshinski-Mariya(DM)相互作用的两比特自旋体系为工质的量子纠缠Otto热机和量子Stirling热机.两种不同热机在各自的循环过程中,通过保持其他参量不变,只有DM相互作用发生改变,从而分析热机循环中DM相互作用与热传递、做功以及效率等热力学量之间的关系.研究结果表明:DM相互作用对两种热机的基本量子热力学量都具有重要的影响,但量子Stirling热机由于回热器的使用,其循环效率会大于量子Otto纠缠热机的效率,甚至会超过Carnot效率;得到了量子Otto纠缠热机和量子Stirling热机做正功的条件.因此,在这两个纠缠体系中,热力学第二定律都依然成立.     

工质变比热条件下内燃机循环普适特性

用有限时间热力学的方法分析空气标准不可逆内燃机循环,导出了考虑工质变比热情况下,存在摩擦及传热损失时,由两个加热过程、两个放热过程和两个绝热过程组成的普适的空气标准不可逆内燃机循环的功率与压缩比、效率与压缩比以及功率和效率的最佳特性关系,同时由数值计算分析了工质变比热和循环过程对循环性能的影响特点,比较了工质恒、变比热时循环性能差异。所得结果包含了不可逆往复式Diesel、Otto、Brayton、Atkinson、Dual和Miller 循环的性能特性。     

Numerical simulation of the operation process and thrust performance of an air-breathing pulse detonation engine in supersonic flight conditions

Multidimensional simulations of the unsteady gasdynamic flow in the duct of an air-breathing pulse detonation engine (ABPDE) operating on propane gas and the flow around it in supersonic flight at Mach numbers M of 3.0 and an altitude of 9.3 and 16 km are performed. It is shown that, at a length and diameter of the duct of 2.12 m and 83 mm, respectively, an ABPDE with an air intake and a nozzle can operate in a cyclic mode at a repetition frequency of 48 Hz, with a rapid deflagration-to-detonation transition (DDT) occurring at a distance of 5–6 combustion chamber diameters. To determine the thrust performance of the ABPDE in flight conditions, a series of working cycles were simulated with consideration given to the external flow around the engine. Calculations showed that the specific impulse of the ABPDE is approximately 1700 s. This value is much higher than the specific impulse typical of ramjet engines operating on conventional combustion (1200–1500 s) and substantially lower than the specific impulse obtained for the atmospheric conditions at sea level at zero flight velocity (∼2500 s).     

超声速气流中的爆震推进理论与研究进展

爆震燃烧近似为等容燃烧,理论上其热循环效率高于基于等压燃烧的爆燃燃烧,在超声速推进系统中具有潜在的应用价值.通过总结超声速气流中的爆震推进理论与研究进展,分析其需要解决的关键科学与技术问题,指导未来高超声速发动机的基础研究.文章重点总结了适用于高超声速飞行的斜爆震发动机、超声速脉冲爆震冲压发动机的基础研究进展.其中对斜爆震发动机的应用模式、相关实验研究思路及方法、数值仿真现状进行了总结分析.对超声速脉冲爆震冲压发动机的基础理论研究现状和目前研究的难点进行了梳理.基于爆震燃烧的超燃冲压发动机具有推进系统自增压、燃烧效率高、推力性能好、推进效率高、燃烧室长度短、结构重量轻等优势,文章总结了该发动机当前的发展进程和最新的研究进展,并对其未来的发展方向以及存在的技术问题进行了分析.      

热声热机和斯特林热机振荡现象的网络描述

热力学循环的实质是一种非等熵的循环 ,热声热机和斯特林热机振荡现象在满足热力学循环一般规律的同时 ,而各有其特殊性 ,故其各自的振荡本质是有差异的 ,用于描述两者的网络模型也必然有差异。     

The performance analysis of a micro-/nanoscaled quantum heat engine

A new model of micro-/nanoscaled heat engines consisting of two thin long tubes with the same length but different sizes of cross section, which are filled up with ideal quantum gases and operated between two heat reservoirs, is put forward. The working fluid of the heat engine cycle goes through four processes, which include two isothermal processes and two isobaric processes with constant longitudinal pressure. General expressions for the power output and efficiency of the cycle are derived, based on the thermodynamic properties of confined ideal quantum gases. The influence of the size effect on the power output and efficiency is discussed. The differences between the heat engines working with the ideal Bose gas and Fermi gas are revealed. The performance of the heat engines operating at weak gas degeneracy and high temperatures is further analyzed. The results obtained are more general and significant than those in the current literature.     

Quantum Heat Engines with Complex Working Media,Complete Otto Cycles and Heuristics

Quantum thermal machines make use of non-classical thermodynamic resources, one of which include interactions between elements of the quantum working medium. In this paper, we examine the performance of a quasi-static quantum Otto engine based on two spins of arbitrary magnitudes subject to an external magnetic field and coupled via an isotropic Heisenberg exchange interaction. It has been shown earlier that the said interaction provides an enhancement of cycle efficiency, with an upper bound that is tighter than the Carnot efficiency. However, the necessary conditions governing engine performance and the relevant upper bound for efficiency are unknown for the general case of arbitrary spin magnitudes. By analyzing extreme case scenarios, we formulate heuristics to infer the necessary conditions for an engine with uncoupled as well as coupled spin model. These conditions lead us to a connection between performance of quantum heat engines and the notion of majorization. Furthermore, the study of complete Otto cycles inherent in the average cycle also yields interesting insights into the average performance.