飛機(jī)異常結(jié)冰的過冷凝固機(jī)理及理論研究
發(fā)布時(shí)間：2019-06-01 16:59
【摘要】：在航空活動(dòng)廣泛普及的今天,飛機(jī)結(jié)冰仍然是飛行安全的重大威脅,近二十年來造成了多起災(zāi)難性事故。自1994年以來,人們在一系列嚴(yán)重結(jié)冰事故發(fā)現(xiàn)了危險(xiǎn)的異常結(jié)冰現(xiàn)象:防冰系統(tǒng)后產(chǎn)生了冰脊以致無法正常除冰,以及超出當(dāng)時(shí)結(jié)冰適航條例范圍(FAR 25.1419和附錄C)的過冷大粒徑水滴(SLD)環(huán)境。說明原有的飛機(jī)防除冰手段難以保證結(jié)冰飛行安全。經(jīng)過二十年的研究,美國聯(lián)邦航空局(FAA)推出了最新的結(jié)冰適航條款(FAR 25.1420和附錄O),初步提出了SLD環(huán)境中的結(jié)冰適航要求。但現(xiàn)在仍然缺乏可靠的結(jié)冰預(yù)測和防護(hù)手段,這是由于產(chǎn)生異常結(jié)冰的機(jī)理還未得到很好的解釋。研究現(xiàn)狀表明,現(xiàn)有的飛機(jī)SLD結(jié)冰研究聚焦在于水滴動(dòng)力學(xué)方面,未深入研究冰生長的機(jī)理。而對過冷水性質(zhì)的研究進(jìn)展則揭示了傳統(tǒng)飛機(jī)結(jié)冰理論的不足。這要求更深入的研究過冷水結(jié)冰機(jī)理,建立可解釋異常結(jié)冰的飛機(jī)結(jié)冰理論,支持結(jié)冰預(yù)測、防護(hù)及適航性驗(yàn)證等方面的研究。這項(xiàng)研究將對我國民機(jī)結(jié)冰適航有直接的支持,并且對過冷水物理、傳熱、凝固相關(guān)交叉學(xué)科研究有推動(dòng)作用。本文圍繞解釋飛機(jī)異常結(jié)冰的目標(biāo),以過冷水結(jié)冰物理特性為切入點(diǎn),開展結(jié)冰機(jī)理,飛機(jī)結(jié)冰理論和結(jié)冰預(yù)測應(yīng)用三部分研究:1、研究大粒徑過冷水滴的破碎形式產(chǎn)生條件和碰撞結(jié)冰的過程,得到水滴的多因素破碎機(jī)理和碰撞非定常傳熱機(jī)理認(rèn)識(shí);研究飛機(jī)表面過冷水生長的基本物理過程,得到過冷水層中結(jié)冰速率和形態(tài)演化的機(jī)理認(rèn)識(shí)。2、研究飛機(jī)表面過冷水層結(jié)冰的演化理論和過冷水滴碰撞耦合結(jié)冰演化理論,提出反映過冷水結(jié)冰物理特性和水滴粒徑效應(yīng)的耦合結(jié)冰演化理論,3、研究飛機(jī)異常結(jié)冰數(shù)值預(yù)測算法,提出了水滴多因素破碎模型,過冷水滴碰撞模型和多階段過冷結(jié)冰模型。對異常結(jié)冰特征的產(chǎn)生過程和條件進(jìn)行了研究,為飛機(jī)結(jié)冰預(yù)測、防除冰設(shè)計(jì)和適航驗(yàn)證做準(zhǔn)備。本文具體研究過程為:1、通過理論分析和兩相流數(shù)值模擬研究了不同水滴破碎形式發(fā)生的條件、破碎的子液滴粒徑和破碎發(fā)生的位置,掌握水滴不同破碎形式的發(fā)生機(jī)理,得到水滴的兩類破碎形式發(fā)生的判據(jù);通過風(fēng)洞實(shí)驗(yàn)研究了過冷水滴碰撞結(jié)冰的過程,通過對水滴碰撞結(jié)冰過程和冰形狀特征的分析,得到了過冷水滴碰撞產(chǎn)生的流動(dòng)、張力影響和傳熱的耦合關(guān)系,對過冷水滴碰撞壁面結(jié)冰的運(yùn)動(dòng)和非定常傳熱過程進(jìn)行了理論分析,得到兩者耦合機(jī)理的認(rèn)識(shí)。2、通過機(jī)理實(shí)驗(yàn)研究了壁面上過冷水結(jié)冰過程,發(fā)現(xiàn)三階段的冰生長現(xiàn)象,研究了其中冰生長速率和形態(tài)變化的規(guī)律,并研究了材料性質(zhì)對冰生長的影響。通過理論分析得到了結(jié)冰演化過程的機(jī)理解釋,以及非定常狀態(tài)下凝固界面的穩(wěn)定性判據(jù)。通過Lattice Boltzmann-相場方法對流動(dòng)環(huán)境中冰枝的生長過程進(jìn)行了研究,得到冰枝在流動(dòng)環(huán)境中的生長規(guī)律,補(bǔ)充實(shí)驗(yàn)和理論的不足。3、通過理論分析研究了過冷水層中多階段結(jié)冰演化過程,包括冰在水層連續(xù)和間斷時(shí)的生長階段演化理論;研究了大過冷水滴破碎和碰撞結(jié)冰過程,包括水滴破碎過程影響水滴粒徑分布和碰撞位置的理論,水滴的碰撞運(yùn)動(dòng)、非定常傳熱與影響冰表面穩(wěn)定性的理論。得到了飛機(jī)上過冷水的耦合結(jié)冰演化理論。4、通過飛機(jī)的二維結(jié)冰數(shù)值方法,研究并校驗(yàn)了水滴多因素破碎模型、水滴碰撞非定常傳熱模型、多階段過冷結(jié)冰模型,并且同經(jīng)典Messinger結(jié)冰模型進(jìn)行結(jié)冰對比研究,得到異常結(jié)冰的特征認(rèn)識(shí):在穩(wěn)態(tài)結(jié)冰時(shí),過冷水中冰枝的生長速度和溫度的關(guān)系為冪函數(shù),能產(chǎn)生比經(jīng)典Messinger結(jié)冰模型預(yù)測更快的結(jié)冰速率和更強(qiáng)的溢流冰;在非定常結(jié)冰時(shí),模型中結(jié)冰形態(tài)的轉(zhuǎn)換會(huì)帶來結(jié)冰速率的突變;大粒徑水滴的碰撞會(huì)影響結(jié)冰形態(tài),也會(huì)導(dǎo)致異常的結(jié)冰速率產(chǎn)生。這些效應(yīng)在冰型上體現(xiàn)為明顯的溢流臺(tái)階冰,是異常結(jié)冰的主要特征之一。本文的創(chuàng)新點(diǎn)為:在理論上,發(fā)現(xiàn)了過冷水壁面結(jié)冰的演化機(jī)理并提出飛機(jī)結(jié)冰的基礎(chǔ)理論,給出了非定常結(jié)冰時(shí)的冰界面穩(wěn)定性判據(jù);在實(shí)驗(yàn)方法上,通過嚴(yán)格控制過冷水/水滴的條件得到了可靠的過冷水結(jié)冰機(jī)理認(rèn)識(shí);在應(yīng)用上,建立了能有效模擬SLD結(jié)冰特征的飛機(jī)結(jié)冰數(shù)值模型和算法。
[Abstract]:Aircraft icing is still a major threat to flight safety today, which has caused many catastrophic accidents in the past two decades. Since 1994, there has been a risk of abnormal ice-freezing in a series of serious ice-icing incidents: the ice-prevention system has developed an ice ridge so that it is unable to de-ice, and the subcooled large-diameter water drop (SLD) environment beyond that of the ice-worthiness regulations at that time (FAR 25.1419 and Appendix C). It is difficult to ensure the safety of icing flight by the conventional method for preventing and controlling the ice. After two decades of research, the FAA has introduced the latest icing and airworthiness provisions (FAR 25.1420 and Appendix O), which initially proposed the icing requirements in the SLD environment. However, there is still a lack of reliable forecasting and protection means, which is not well explained due to the mechanism of abnormal icing. The research status shows that the research focus on the existing aircraft SLD ice is the water drop dynamics, and the mechanism of ice growth is not in-depth study. The research progress on the cold water property reveals the deficiency of the traditional aircraft icing theory. This requires a more in-depth study of the mechanism of cold water icing, to establish an aircraft icing theory that can explain the abnormal icing, to support research on the aspects of icing prediction, protection and airworthiness verification. This study will provide a direct support for the ice-worthiness of the civil aircraft in our country, and it has an impelling effect on the cross-disciplinary research related to the physical, heat transfer and solidification of cold water. In this paper, a three-part study of the freezing mechanism, the icing theory of the aircraft and the application of the icing prediction is carried out on the basis of the objective of explaining the abnormal icing of the aircraft, the freezing mechanism, the icing theory of the aircraft and the application of the icing prediction are studied in three parts:1. The conditions of the crushing of the supercooled water droplets with large particle size and the process of collision and freezing are studied. The mechanism of multi-factor crushing and the mechanism of the unsteady heat transfer of the water drop are recognized; the basic physical process of the overcold water growth on the surface of the aircraft is studied, and the mechanism of the freezing rate and the form evolution in the cold water layer is obtained. In this paper, the evolution theory of the surface overcold water layer on the surface of the aircraft and the theory of supercooled water drop collision coupled ice evolution are studied, and the coupled icing evolution theory, which reflects the physical characteristics of the cold water and the particle size effect of the water droplets, is put forward, and the numerical prediction algorithm for the abnormal icing of the aircraft is studied. A water-drop multi-factor crushing model, a supercooled water drop collision model and a multi-stage supercooled ice model are proposed. The production process and conditions of the abnormal icing characteristics are studied, and the preparation of the aircraft icing prediction, the control of the ice design and the airworthiness verification is carried out. The specific research process of this paper is as follows:1. The conditions, the size of the broken sub-droplets and the location of the break-up are studied by the theoretical analysis and the numerical simulation of two-phase flow, and the occurrence mechanism of the different breaking forms of the water droplets is mastered. The criterion of the two types of crushing forms of the water drops is obtained, the process of the super-cooled water drop collision and freezing is studied through the wind tunnel experiment, the flow, the tension effect and the coupling relation of the heat transfer are obtained through the analysis of the water drop collision freezing process and the ice shape characteristic, In this paper, a theoretical analysis of the motion and the unsteady heat transfer process of the supercooled water drop collision wall surface is carried out, and the coupling mechanism of the two is obtained.2. The ice formation process of the cold water on the wall surface is studied by the mechanism experiment, and the ice growth phenomenon of the three stages is found. The law of the rate of ice growth and the change of morphology was studied, and the effect of the properties of the material on the growth of ice was studied. The mechanism of the freezing evolution process and the stability criterion of the solidification interface under the unsteady state are obtained through the theoretical analysis. In this paper, the growth process of ice branches in the flowing environment was studied by the Lattice Boltzmann-phase field method, and the growth rule of the ice branches in the flowing environment was obtained. comprises the theory of the evolution of the growth phase of the ice in the continuous and intermittent water layer, The theory of unsteady heat transfer and the stability of ice surface. Based on the two-dimensional icing numerical method of the aircraft, a multi-factor crushing model, a water drop collision unsteady heat transfer model and a multi-stage supercooled ice model were studied and verified by the two-dimensional icing numerical method of the aircraft. and compared with the classical Messinger icing model, the characteristics of the abnormal ice formation are obtained: when the steady-state ice is frozen, the relationship between the growth speed and the temperature of the ice branches in the over-water is a power function, and the icing rate and the stronger overflow ice can be predicted more quickly than the classical Messinger icing model; In the case of unsteady ice formation, the transformation of the ice form in the model results in a sudden change in the freezing rate; the impact of the large-particle-size water droplets will affect the formation of the ice, which can also lead to an abnormal rate of ice formation. The effect of these effects on the ice form is the obvious overflow step ice, which is one of the main characteristics of the abnormal ice formation. The innovation point of this paper is that, in theory, the evolution mechanism of the freezing of the cold water wall is found and the basic theory of the icing of the aircraft is put forward, and the stability criterion of the ice interface during the unsteady ice formation is given; and in the experimental method, By strictly controlling the condition of the over-water/ water drop, it is recognized that the freezing mechanism of the cold water is reliable. In the application, the numerical model and the algorithm of the icing of the aircraft with the characteristics of the SLD icing can be effectively simulated.
【學(xué)位授予單位】：上海交通大學(xué)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2015
【分類號(hào)】：V244.15
本文編號(hào)：2490435
[Abstract]:Aircraft icing is still a major threat to flight safety today, which has caused many catastrophic accidents in the past two decades. Since 1994, there has been a risk of abnormal ice-freezing in a series of serious ice-icing incidents: the ice-prevention system has developed an ice ridge so that it is unable to de-ice, and the subcooled large-diameter water drop (SLD) environment beyond that of the ice-worthiness regulations at that time (FAR 25.1419 and Appendix C). It is difficult to ensure the safety of icing flight by the conventional method for preventing and controlling the ice. After two decades of research, the FAA has introduced the latest icing and airworthiness provisions (FAR 25.1420 and Appendix O), which initially proposed the icing requirements in the SLD environment. However, there is still a lack of reliable forecasting and protection means, which is not well explained due to the mechanism of abnormal icing. The research status shows that the research focus on the existing aircraft SLD ice is the water drop dynamics, and the mechanism of ice growth is not in-depth study. The research progress on the cold water property reveals the deficiency of the traditional aircraft icing theory. This requires a more in-depth study of the mechanism of cold water icing, to establish an aircraft icing theory that can explain the abnormal icing, to support research on the aspects of icing prediction, protection and airworthiness verification. This study will provide a direct support for the ice-worthiness of the civil aircraft in our country, and it has an impelling effect on the cross-disciplinary research related to the physical, heat transfer and solidification of cold water. In this paper, a three-part study of the freezing mechanism, the icing theory of the aircraft and the application of the icing prediction is carried out on the basis of the objective of explaining the abnormal icing of the aircraft, the freezing mechanism, the icing theory of the aircraft and the application of the icing prediction are studied in three parts:1. The conditions of the crushing of the supercooled water droplets with large particle size and the process of collision and freezing are studied. The mechanism of multi-factor crushing and the mechanism of the unsteady heat transfer of the water drop are recognized; the basic physical process of the overcold water growth on the surface of the aircraft is studied, and the mechanism of the freezing rate and the form evolution in the cold water layer is obtained. In this paper, the evolution theory of the surface overcold water layer on the surface of the aircraft and the theory of supercooled water drop collision coupled ice evolution are studied, and the coupled icing evolution theory, which reflects the physical characteristics of the cold water and the particle size effect of the water droplets, is put forward, and the numerical prediction algorithm for the abnormal icing of the aircraft is studied. A water-drop multi-factor crushing model, a supercooled water drop collision model and a multi-stage supercooled ice model are proposed. The production process and conditions of the abnormal icing characteristics are studied, and the preparation of the aircraft icing prediction, the control of the ice design and the airworthiness verification is carried out. The specific research process of this paper is as follows:1. The conditions, the size of the broken sub-droplets and the location of the break-up are studied by the theoretical analysis and the numerical simulation of two-phase flow, and the occurrence mechanism of the different breaking forms of the water droplets is mastered. The criterion of the two types of crushing forms of the water drops is obtained, the process of the super-cooled water drop collision and freezing is studied through the wind tunnel experiment, the flow, the tension effect and the coupling relation of the heat transfer are obtained through the analysis of the water drop collision freezing process and the ice shape characteristic, In this paper, a theoretical analysis of the motion and the unsteady heat transfer process of the supercooled water drop collision wall surface is carried out, and the coupling mechanism of the two is obtained.2. The ice formation process of the cold water on the wall surface is studied by the mechanism experiment, and the ice growth phenomenon of the three stages is found. The law of the rate of ice growth and the change of morphology was studied, and the effect of the properties of the material on the growth of ice was studied. The mechanism of the freezing evolution process and the stability criterion of the solidification interface under the unsteady state are obtained through the theoretical analysis. In this paper, the growth process of ice branches in the flowing environment was studied by the Lattice Boltzmann-phase field method, and the growth rule of the ice branches in the flowing environment was obtained. comprises the theory of the evolution of the growth phase of the ice in the continuous and intermittent water layer, The theory of unsteady heat transfer and the stability of ice surface. Based on the two-dimensional icing numerical method of the aircraft, a multi-factor crushing model, a water drop collision unsteady heat transfer model and a multi-stage supercooled ice model were studied and verified by the two-dimensional icing numerical method of the aircraft. and compared with the classical Messinger icing model, the characteristics of the abnormal ice formation are obtained: when the steady-state ice is frozen, the relationship between the growth speed and the temperature of the ice branches in the over-water is a power function, and the icing rate and the stronger overflow ice can be predicted more quickly than the classical Messinger icing model; In the case of unsteady ice formation, the transformation of the ice form in the model results in a sudden change in the freezing rate; the impact of the large-particle-size water droplets will affect the formation of the ice, which can also lead to an abnormal rate of ice formation. The effect of these effects on the ice form is the obvious overflow step ice, which is one of the main characteristics of the abnormal ice formation. The innovation point of this paper is that, in theory, the evolution mechanism of the freezing of the cold water wall is found and the basic theory of the icing of the aircraft is put forward, and the stability criterion of the ice interface during the unsteady ice formation is given; and in the experimental method, By strictly controlling the condition of the over-water/ water drop, it is recognized that the freezing mechanism of the cold water is reliable. In the application, the numerical model and the algorithm of the icing of the aircraft with the characteristics of the SLD icing can be effectively simulated.
【學(xué)位授予單位】：上海交通大學(xué)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2015
【分類號(hào)】：V244.15
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