说New words
• Kerosine煤油
• Flame 火焰
• Flametube 火焰筒
• Combustionliner 火焰筒
• Snout 锥形口
• Swirlvane 漩涡叶片
• Flare 喇叭形
• Adjacent相邻
• Recirculation再循环、回流
• Toroidalvortex 环形旋涡
• Stabilize稳定
• Anchoring锚定
• Conical圆锥形
• Intersect相交、交叉
• Dilution稀释
• Remainder余数、其余的
• Film 气膜
• Spark 火花
• Igniterplug 点火电嘴
• Initiate启动
• Atomize雾化
• Pre-vaporization预汽化
• Multiplechamber 单管燃烧室
• Tubo-annularchamber 环管燃烧室
• Annularchamber 环形燃烧室
• Propagate传播
• Overhaul大修、翻修
• Compactness紧凑性
• Unburnt未燃烧
• Oxidize氧化
• Carbonmonoxide 一氧化碳
• Non-toxiccarbon dioxide 无毒二氧化碳
• Aerating充气
• Over-rich过度富裕
• Incurring引起
• Relight重新点燃
• Exceptionally分外、异常的
• Calorific发热的
• Expenditure支出、花费
• Cruise巡航
• Alight点燃
• Glide 滑翔
• Dive 俯冲
• Idling慢车
• Stabilityloop 稳定包线
• Pollutant污染物
• Legislatively立法上
• Hydrocarbon碳氢氧化物
• Nitrogen氮气
• Primaryzone 主燃区
• Insulation绝缘
• Gradient梯度
读Sentence
• 2. Theamount of fuel added to the air will depend upon the temperature rise required.However, the maximum temperature is limited to within the range of 850 to 1700deg. C. by the materials from which the turbine blades and nozzles are made.The air has already been heated to between 200 and 550 deg. C. by the work doneduring compression, giving a temperature rise requirement of 650 to 1150 deg.C. from the combustion process. Since the gas temperature required at theturbine varies with engine thrust, and in the case of the turbo-propellerengine upon the power required, the combustion chamber must also be capable ofmaintaining stable and efficient combustion over a wide range of engineoperating conditions.
• 5. Innormal operation, the overall air/fuel ratio of a combustion chamber can varybetween 45:1 and 130:1, However, kerosine will only burn efficiently at, orclose to, a ratio of 15:1, so the fuel must be burned with only part of the airentering the chamber, in what is called a primary combustion zone. This is achievedby means of a flame tube (combustion liner) that has various devices formetering the airflow distribution along the chamber.
• 9. Thetemperature of the gases released by combustion is about 1,800 to 2,000 deg.C., which is far too hot for entry to the nozzle guide vanes of the turbine.The air not used for combustion, which amounts to about 60 percent of the totalairflow, is therefore introduced progressively into the flame tube.Approximately a third of this is used to lower the gas temperature in thedilution zone before it enters the turbine and the remainder is used forcooling the walls of the flame tube. This is achieved by a film of cooling airflowing along the inside surface of the flame tube wall, insulating it from thehot combustion gases (fig. 4-4). A recent development allows cooling air toenter a network of passages within the flame tube wall before exiting to forman insulating film of air, this can reduce the required wall cooling airflow byup to 50 percent. Combustion should be completed before the dilution air entersthe flame tube, otherwise the incoming air will cool the flame and incompletecombustion will result.
• 23. Acombustion chamber must be capable of allowing fuel to burn efficiently over awide range of operating conditions without incurring a large pressure loss. Inaddition, if flame extinction occurs, then it must be possible to relight. Inperforming these functions, the flame tube and spray nozzle atomizer componentsmust be mechanically reliable.
• 29.For any particular type of combustion chamber there is both a rich and weaklimit to the air/fuel ratio, beyond which the flame is extinguished. Anextinction is most likely to occur in flight during a glide or dive with theengine idling, when there is a high airflow and only a small fuel flow, i.e. avery weak mixture strength.
读全文并回答以下问题：
• What are the design requirements of combustion chamber?
• What are the classification of oil supply methods?
• What is the difference between multiple combustion chamber and Whittle combustionchamber?
• What is the main advantage of annular chamber?
• What are the main pollutants for combustion chamber?
