说Topic: Why to learn?

•   To learn English related to aeronauticalscience;

•   To learn basic knowledge of aero-engine;

•   To improve reading comprehension ability ofSE;

•   To train oral and listening ability;

•   To train Chinese to English translationability.

关于“专业英语”

•   Scientific English 科技英语

–Scientific:科技的；

–Technical:技术的；

–University of technology:科技大学

–Scientific and technical information:科学技术情报

•   Professional English 专业英语

–Specialized, specialty, professional:专业的

–Expertise:专长；专门技能；专门知识

–Major:主修，专业

说New words

•        Gas turbine engine 燃气涡轮发动机

•        Aircraft power plant飞行器动力装置

•        Rapid 瞬间的、迅速的

•        Propulsion 推动力、推进

•        Reaction jet 反作用力喷气式飞机

•        Piston engine 活塞发动机

•        Airflow 气流

•        Jet 喷气式飞机

•        Patent 专利

•        Athodyd 冲压式空气喷气发动机

•        Manufacture  制造

•        Heat resisting material 耐热材料

•        Extremely inefficient 效率极低

•        Ramjet 冲压喷气发动机

•        Conception 概念

•        Grant （正式地或法律上）同意、允许

•        Combustion chamber 燃烧室

•        Air intake 进气道

•        Fuel supply 燃油供应

•        Propelling nozzle 推进喷管

•        Military 军用

•        Turbo-propeller engine 涡轮螺旋桨发动机

•        Power plant 动力装置

•        Twin-spool 双转子

•        Triple-spool 三转子

•        By-pass 内外涵道

•        Ducted fan 涵道风扇

•        Unducted fan 无涵道风扇

•        Propfan 螺桨风扇

•        Inevitable 不可避免的、必然的

•        Compressor 压气机

•        Turbine 涡轮

•        Fuel burner  燃油喷嘴

•        Jet pipe and propelling nozzle 喷管和推进喷口

•        Piston engine-propeller combination 活塞发动机-螺旋桨组合推进装置

•        Solely 完全地、单独地

•        Thrust 推力

•        Pulse jet 脉冲喷气发动机

•        Rocket 火箭发动机

•        Turbo/ram jet 涡轮/冲压喷气发动机

•        Turbo-rocket 涡轮-火箭发动机

•        Practical 实用的

•        Atmospheric air 大气

•        Apparatus 仪器、装置

•        Slipstream 滑流

•        Comparatively 相对而言

•        Momentum 动量

•        Impart 通知、给予

•        Revolve 旋转

•        Whirling 旋转、回旋

•        Mechanism 机械装置、构造

•        Virtue 优点、长处

•        Hose 软管

•        Illustration 插图

•        Carnival 嘉年华

•        Internal phenomenon 内部现象

•        Stream 流动、溪流

•        Expel 驱逐、开出

•        In all instances 在所有情况下

•        Resultant 因而产生的

•        Exerted 运用、施加

•        Proportional 比例

•        Former 前者的、以前的

•        Aero-thermodynamic-duct 气动热力涵道

•        Consist of 包括

•        Divergent 发散的

•        Convergent 收敛的

•        Convergent-divergent 收敛发散的

•        External 外部

•        Kinetic energy 动能

•        Missile 导弹

•        Target vehicle 靶机

•        Intermittent 间歇的

•        Static 静态的

•        Robust 强健的、结实耐用的

•        Valve 阀门

•        Spring 弹簧

•        Rearward 向后

•        Helicopter 直升机

•        Dispense 分配

•        Resonate 共振

•        Decomposed 分解

•        Oxygen 氧气

•        Inherent 固有的

•        Simplicity 简单

•        Subsequent 之后的、后来的

•        Blade 叶片

•        Approximately 大约

•        Offset 抵消、弥补、补偿

•        Comparative 比较的、相对的

•        Variable intake 可调进气道

•        Intake guide vanes 进口导流叶片

•        Surrounded 包围、围绕

•        Function 功能

•        Conventional 传统的

•        Lit 点燃

•        Inoperative 不工作的、不起作用的

•        Cruise 巡航

•        Mode 模式

•        Driven 驱动

•        Multi-stage 多级

•        Derived 获得、取得、产生

•        Kerosine 煤油

•        Diluted 稀释

•        Surplus 盈余

•        Interceptor  拦截器、截击机

•        Space-launcher 空间发射器

•        Duration 持续时间、续航时间

读Sentence

•        1. The development of the gas turbine engine as an aircraftpower plant has been so rapid that it is difficult to appreciate that prior tothe 1950s very few people had heard of this method of aircraft propulsion. Thepossibility of using a reaction jet had interested aircraft designers for along time, but initially the low speeds of early aircraft and the unsuitably ofa piston engine for producing the large high velocity airflow necessary for the‘jet’ presented many obstacles.

•        2. A French engineer, René Lorin, patented a jet propulsionengine (fig. 1-1) in 1913, but this was an athodyd (para. 11) and was at thatperiod impossible to manufacture or use, since suitable heat resistingmaterials had not then been developed and, in the second place, jet propulsionwould have been extremely inefficient at the low speeds of the aircraft ofthose days. However, today the modern ram jet is very similar to Lorin'sconception.

•        4. The jet engine (fig. 1-2), although appearing so differentfrom the piston engine-propeller combination, applies the same basic principlesto effect propulsion. As shown in fig. 1-3, both propel their aircraft solelyby thrusting a large weight of air backwards.

•        10. The types of jet engine, whether ram jet, pulse jet,rocket, gas turbine, turbo/ram jet or turbo-rocket, differ only in the way inwhich the 'thrust provider', or engine, supplies and converts the energy intopower for flight.

•        11. The ram jet engine (fig. 1-6) is an athodyd, or 'aero-thermodynamic-ductto give it its full name. It has no major rotating parts and consists of a ductwith a divergent entry and a convergent or convergent-divergent exit. Whenforward motion is imparted to it from an external source, air is forced intothe air intake where it loses velocity or kinetic energy and increases itspressure energy as it passes through the diverging duct. The total energy isthen increased by the combustion of fuel, and the expanding gases accelerate toatmosphere through the outlet duct.

•        12. The pulse jet engine (fig. 1-7) uses the principle ofintermittent combustion and unlike the ram jet it can be run at a staticcondition. The engine is formed by an aerodynamic duct similar to the ram jetbut, due to the higher pressures involved, it is of more robust construction.The duct inlet has a series of inlet 'valves' that are spring-loaded into theopen position. Air drawn through the open valves passes into the combustionchamber and is heated by the burning of fuel injected into the chamber. Theresulting expansion causes a rise in pressure, forcing the valves to close, andthe expanding gases are then ejected rearwards. A depression created by theexhausting gases allows the valves to open and repeat the cycle.

•        13. Although a rocket engine (fig. 1-8) is a jet engine, ithas one major difference in that it does not use atmospheric air as thepropulsive fluid stream. Instead, it produces its own propelling fluid by thecombustion of liquid or chemically decomposed fuel with oxygen, which itcarries, thus enabling it to operate outside the earth's atmosphere. It is,therefore, only suitable for operation over short periods.

•        15. The mechanical arrangement of the gas turbine engine issimple, for it consists of only two main rotating parts, a compressor (Part 3)and a turbine (Part 5), and one or a number of combustion chambers (Part 4).The mechanical arrangement of various gas turbine engines is shown in fig. 1-9. This simplicity, however, does not apply to all aspects of the engine, foras described in subsequent Parts the thermo and aerodynamic problems aresomewhat complex. They result from the high operating temperatures of thecombustion chamber and turbine, the effects of varying flows across thecompressor and turbine blades, and the design of the exhaust system throughwhich the gases are ejected to form the propulsive jet.

•        17. The advantages of the propeller/turbine combination haveto some extent been offset by the introduction of the by-pass, ducted fan andpropfan engines. These engines deal with larger comparative airflows and lowerjet velocities than the pure jet engine, thus giving a propulsive efficiency(Part 21) which is comparable to that of the turbo-prop and exceeds that of thepure jet engine (fig. 1-10).

•        19. The engine is surrounded by a duct that has a variableintake at the front and an afterburning jet pipe with a variable nozzle at therear. During take- off and acceleration, the engine functions as a conventionalturbo-jet with the afterburner lit; at other flight conditions up to Mach 3,the afterburner is inoperative. As the aircraft accelerates through Mach 3, theturbo-jet is shut down and the intake air is diverted from the compressor, byguide vanes, and ducted straight into the afterburning jet pipe, which becomesa ram jet combustion chamber. This engine is suitable for an aircraft requiringhigh speed and sustained high Mach number cruise conditions where the engineoperates in the ram jet mode.

•        21. The engine has a low pressure compressor driven by amulti-stage turbine; the power to drive the turbine is derived from combustionof kerosene and liquid oxygen in a rocket-type combustion chamber. Since thegas temperature will be in the order of 3,500 deg. C, additional fuel issprayed into the combustion chamber for cooling purposes before the gas entersthe turbine. This fuel-rich mixture (gas) is then diluted with air from thecompressor and the surplus fuel burnt in a conventional afterburning system.

读全文并回答以下问题：

•       Describe the Newton’s third law of motion.

•       The same thrust can be provided by two kinds of way, whichway is better for aero-engine?

•       Why the ram jet is unsuitable to work as an aircraft powerplant?

•       Why the pulse jet is unsuitable to work as an aircraft powerplant?

•       What kind of aircraft should use the combination of propeller and gasturbine engine as a power plant, and why?

作业收看收听以下资源的前11：30，并用英文回答问题，同时请将答案翻译成中文。