Фонетические упражнения
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ЗАДАНИE 3. ФОНЕТИЧЕСКИЕ УПРАЖНЕНИЯ Упражнение 1. Прочитайте и переведите следующие слова и словосочетания: Turbine, gas turbine unit, essential, combustion chamber, ignition, igniter plug, initially, button, necessary, surface, lubrication system, to be initiated, pressure, ma- jor, fuel, quantity, temperature, guide, energy, more, high speed, thrust. TEXT How the Gas Turbine Works A gas turbine unit consists of three essential components, (1) a rotary air compressor at the front, (2) a series of combustion chambers into which kerosene is sprayed and burnt continuously, and (3) a turbine revolving with the compressor on a common shaft. There are no pistons, valves or ignition apparatus save for two igniter plugs to attain a start. Initially an electric starter motor spins the main shaft at about one-eighth speed. Starting operations are automatically controlled by a time switch. The pilot opens a fuel cock, depresses a button, and in about half a minute the unit is running at idling speed. No warming-up period is necessary as bearings are few, there are no metal-to-metal sliding surfaces, and consequently only a simple lubrication system. After combustion of fuel is initiated in one of two chambers fitted with igni- ter plugs, the flame is propagated to all the other chambers through interconnecting pipes. On the ground air is induced at the front by the action of the rotating compressor, forced by the same compressor into the combustion chambers at a ratio of about 4 to 1 and into this compressed air, aviation kerosene is pumped at a pressure of about 750 lb. sq. in. and burnt continuously. In flight the work of compressing the air is greatly assisted by the forward motion of the aircraft. Only a small quantity of air Is used for combustion to provide the necessary air/ fuel ratio of about 14:1. The ma- jor portion – the so-called “dilution” air in distinction to the “combustion” air lowers the air/fuel ratio to about 60:1 and reduces the combustion temperature of, say, 1,800 deg. C. to about 850 deg. C. at the entry to the turbine. The tremendous heat released by the combustion of the fuel expands the air and as the chambers have an open end, in contrast to the closed cylinder of a piston engine, there is no rise in pressure. Ac-tually there is a slight fall in pressure, say 2 or 3 lb/sq. in. from the entry to the outlet of the chambers. By the reason of the rapid expansion, the heated air and combustion products at increased velocity force their way through the only exit from the chambers, namely, between the guide wanes in the stator ring of the turbine. These wanes direct the flow to the appropriate angle of attack for the blades on the periphery of the turbine wheel. The rapid passage of the heated gas through the airfoil-shaped blades (about 50 of them) causes the wheel to rotate rapidly from 8,000 to 16,000 r.p.m., for example, at full speed. In this manner mechanical energy is created at the shaft and the compre-ssor fixed to the front end of the shaft is made to do its work in compressing more air into the combustion chambers and the process goes on so long as fuel is introdu- ced. As in the orthodox engine, less fuel is required as altitude is increased and a ba- rometric device is fitted to regulate automatically the supply injected into the combu- stion chambers. The usual fuel is kerosene but petrol or diesel oil can be employed. Calorific value is the prime fuel characteristic and the specific calorific value per gallon is of more importance than the value per lb., as weight can be more readily ac- commodated in high speed aircraft than bulk. In a pure jet unit all the power delivered by the turbine is expanded in driving the air compressor and the necessary auxiliary equipment. To drive the compressor approximately 100 h.p. is required for each lb. of air delivered per second. A pound of air per second gives about 50 lb. thrust, therefore the turbine of a unit developing 2,000 lb. thrust must deliver about 4,000 h.p. from the rear of the turbine the heated air, still expanding, emerges from the tail nozzle as a high-velocity jet, say, 1,800 ft. per second, or 1,227 m.p.h. the temperature at the outlet is down to about 300deg. C., compared with 690 deg. C. maximum as it enters the jet pipe. Specific pressure is re- latively low, being only from one and a half to twice that of atmosphere. Комментарий к тексту: 1. rocket-assisted take-off – зд. ракетный двигатель, работающий на взлете, стар- товый ускоритель 2. a series of – ряд 3. save for – кроме 4. “dilution” air – вторичный воздух 5. “combustion” air – первичный воздух 6. say – скажем 7. by reason of – из-за 8. so long as – пока 9. being only from one and a half to twice that of atmosphere – примерно в полтора- два раза выше атмосферного 10. deg. (degree) – градус 11. lb.(pound) – фунт 12. h.p. (horse power) – лошадиная сила 13. sq.(square) – квадратный 14. r.p.m. (revolutions per minute) – обороты в минуту 15. m.p.h. (miles per hour) – мили в час Задания I. Прочтите и переведите текст. II. Найдите эквиваленты для английских словосочетаний: 1. the gas turbine 1. состоять из 2. the combustion chamber 2. основной 3. to consist of 3. давление 4. essential 4. доставлять 5. the lubrication system 5. камера сгорания 6. to be increased 6. требоваться 7. the pressure 7. высота 8. to be expanded 8. увеличиваться, возрастать 9. to deliver 9. система смазки 10. to be required 10. расширяться 11. the altitude 11. газовая турбина 12. a barometric device 12. барометрический регулятор подачи топлива в ТРД 13. a fuel tank 13. топливный кран III. Назовите английские эквиваленты: три основных части, система смазки, ротационный компрессор, камера сгорания, вращающаяся турбина, реле времени, топливо, сжатый воздух, давление. IV. Найдите в 1-м абзаце текста примеры употребления глагола в страдательном залоге. Дайте их перевод. Определите время по форме вспомогательного глаго-ла. V. Найдите в последнем абзаце предложения, содержащие инфинитив. Переве- дите их. VI. Найдите в последнем абзаце текста предложение, содержащее герундий. Переведите. VII. Скажите соответствуют ли предложения содержанию текста, если нет, то дайте правильный ответ. 1. A gas turbine unit consists of five essential components. 2. A gas turbine unit consists of three essential components, a rotary air compressor, a series of combustion chambers and a turbine revolving. 3. There are pistons, valves or ignition apparatus save for two igniter plugs to attain a start. 4. The pilot opens a fuel tank, depresses a button, and in about five minutes the unit is running at idling speed. 5. Starting operations are automatically controlled by a time switch. VIII. Составьте аннотацию текста. ДОПОЛНИТЕЛЬНЫЕ ТЕКСТЫ ДЛЯ САМОСТОЯТЕЛЬНОЙ РАБОТЫ History of Aircraft Engines Today engines developing several thousand horsepower greatly differ from those used many years ago. Thus the plane tested by Mozhaisky in 1884 was a monoplane provided with two engines developing 50-hp. Three four-bladed airscrews provided thrust, the main one was installed in the nose part, the two others were arranged in the rear. One of the problems worked at by the designers was to lighten the weight of the engine and to increase its efficiency. In 1880 the Russian mechanic Yagodzinsky designed and constructed anew engine type. The engine designed by him was the first gasoline engine working on the four-stroke cycle principle. The engine attracted the attention of many designers as it was lighter and more powerful as compared with the previous engines. After this invention there came a stage when engines installed in the airplane were motorcar engines simplified and reduced in weight. Still there remained an important but unsolved problem: how to combine efficiency and lightness in an engine. If used for an airplane, the gasoline engine had to have the reduced weight per horsepower of the engine. One more important problem dealt with both in the past and today is that of fuel. All well-known types of engines used today derive their energy from chemical elements or components called fuels which combine with oxygen. _________________________________________ four-stroke cycle - четырехтактный Aircraft Engine Designer The outstanding aircraft engine designer Alexander G.Ivchenko (1903-1968) was torn into a workers' family in the town of Tokmak (Zaporozhye Region), In 1920 lie began working as a founder and m 1930 he entered the Kharkov Machine-Building Institute, After graduating from this institute he began working as an aircraft engine designer and. devoted his entire life to the development of Russianaircraft engines. In 1946 Ivchenko headed an experimental aircraft engine bureau and showed his great talent as a designer. Working under his supervision for 20 years the design bureau created piston engines for training and sports planes and helicopters the highly reliable AL-20 gas-turbine engine for the IL-18, An-10, AN-12 aircraft and a small-size turbojet engine AL-25. Local service passenger airliners Yak-40s equipped with these engines have excellent performances and are praised in Russia and" abroad. A. Ivchenko trained many young designers and -engineers who are making their contribution to the development of aircraft engines. The prominent designer combined his great energy, professional talent and creativity in solving complicated problems with great organizational abilities. In 1964 A.Ivchenko received the title of academician and became a Member of the Academy of Sciences. For his great achievements in the development of Russian aviation he was honoured with different titles. The Wing The wing is a principal unit of the airplane. Its function is to create lift and support the airplane in flight. There are some terms which refer to the wing. The span is the length of the wing from the tip on one side to the tip on the other side. The leading edge is the front edge of the wing. The chord is the distance from the leading edge to the trailing edge. The aspect ratio is the ratio of the span to the mean chord. The angle of attack is the angle between the chord and the direction of the wind. The dihedral angle between the wing and a horizontal plane. The sweepback angle is the angle between the wing and a perpendicular to the longitudinal axis of the airplane. The design of the wing depends on the size, weight and use of the airplane. The wings of modern airplanes are of all-metal construction. The principal members of the wing are spars, stringers, ribs and skin. The spars form the structural base of the wing. The ribs give the wing a special streamlined shape. The stringers reinforce the skin. The skin transfers the loads to the ribs and carries a part of wing stresses. The Wing Structure The airplane wing consists of three main sections because its manufacture and assembly is difficult. These sections are the centre section, the port main plane and starboard main plane. The main planes are subdivided into main planes proper ailerons, flaps and wingtips. The ailerons are small movable parts located near the tips. Their construction is similar to the wing construction. They help to bank the airplane. The wingtips are small units attached to the outer and the outboard panel. The flaps are large airfoils hinged to the trailing edge of the wing. They reduce the landing speed of the airplane. There are four types of flaps, namely, plain flaps, split trailing edge flaps, slotted flaps and fowler flaps. The wings may have slots. Slots are passages through the airfoil near the leading edge. They help to maintain the airflow above the wing and this permits the airplane to fly at a higher angle of attack. Fin and Rudder In order to maintain directional stability a fin is provided. It is the vertical fixed surface at the rear of the fuselage. Directional control of the airplane, that is, control in the yawing plane or motion about the normal axis, is achieved by the pilot by means of a rudder which is a movable surface hinged to the rear of the fin in such a manner that it can be deflected right or left or retain in the neutral position in line with the fin. If the pilot requires to change his direction towards the right or starboard, he moves the rudder to the right when the reaction of airstream on the 'exposed surface produces a couple about the centre of gravity and the nose of the aircraft is turned to starboard. It must be pointed out that the fin is the stabilizing surface and the rudder is the controlling surface but when the rudder is centralized and the airplane is flying on a straight course stability is provided by the effect of the whole surface of the fin and rudder together. Similarly for longitudinal stability the necessary result is achieved by the action of the tail plane and elevator together. Undercarriage The undercarriage of an airplane consists of main and auxiliary units. They may be retractable or non-retractable. The main undercarriage forms the principal support of the airplane on land or water. It may include any combination of wheels, floats, skis, shock-absorbing equipment, brakes, retracting mechanism with controls and warning devices, cowling, fairing and structural members necessary to attach them to the primary structure. The auxiliary undercarriage consists of tail or nose landing-wheel installations, outboard pontoons, skids with necessary cowling. Non-retractable undercarriage is usually attached to structural members of the airplane with bolts, and equipped with cowling or fairing to reduce air resistance. An exposed undercarriage creates a considerable amount of drag and thus lowers flying speeds. This disadvantage has been decreased or eliminated by the use of retractable undercarriage - that is, undercarriage which may be withdrawn into recesses in the wing or fuselage. In this case the undercarriage is completely retracted and covered with fairing. Retraction of the undercarriage may be accomplished manually, electrically or hydraulically. Usually, electrically operated units also have manual controls for emergency use. ПРИЛОЖЕНИЯ ПРИЛОЖЕНИЕ 1 Таблица основных форм нестандартных глаголов.
ПРИЛОЖЕНИЕ 2 НАИБОЛЕЕ УПОТРЕБИТЕЛЬНЫЕ СУФФИКСЫ.
ПРИЛОЖЕНИЕ 3 НАИБОЛЕЕ УПОТРЕБИТЕЛЬНЫЕ ПРЕФИКСЫ.
ПРИЛОЖЕНИЕ 4 НАИБОЛЕЕ УПОТРЕБИТЕЛЬНЫЕ СОКРАЩЕНИЯ a.m. ante meridiem (лат.) во столько-то часов утра e.g. exsempli gratin (лат.) например e.m.f. electromotive force электродвижущая сила etc. et cetera (лат.) и т.д. f.p.s. feet per second футов в секунду ft. foot, feet фут(ы) gal. gallon галлон gr gram(me) грамм h (hr) hour час h.p. horse power лошадиная сила h.p. high pressure высокое давление i.e. id est (лат.) то есть kg kilogram килограмм lb pound фунт l.p. low pressure низкое давление m.p.h. miles per hour миль в час p.m. post meridiem (лат.) во столько-то часов пополудни p.s.i. pound per square foot фунтов на квадратный фут r.p.m revolution per minute оборотов в минуту r.p.s. revolution per second оборотов в секунду sq. square квадратный sec. second секунда w watt ватт X-rays Roetgen rays рентгеновские лучи ПРИЛОЖЕНИЕ 5 СЛОВОСОЧЕТАНИЕ СЛОВОСОЧЕТАНИЕ – это такое сочетание двух или нескольких слов ,в котором есть поясняемые (главные) компоненты и поясняющие, распространяющие структуру словосочетания, и тем самым конкретизирующие содержание номинации данной строительной единицы языка. modern airplanes round structures various loads fail safe design pat of the fuselage fuselages of modern airliners structural units of the airplane the forward end of the fuselage ОСОБЕННОСТЬ СОЧЕТАНИЙ СУЩ. + СУЩ, В АНГЛИЙСКОМ ЯЗЫКЕ СОСТОИТ В ТОМ ,ЧТО ОДНО ИЗ НИХ ВЫПОЛНЯЕТ ПОЯСНИТЕЛЬНУЮ ФУНКЦИЮ И ПЕРЕВОДИТСЯ НА РУССКИЙ ЯЗЫК ПРИЛОГАТЕЛЬНЫМ И СУЩЕСТВИТЕЛЬНЫМ В КОСВЕННОМ ПАДЕЖЕ. airplane engine - самолетный двигатель fuel system - топливная система baggage compartment - багажный отсек engine control - управление двигателя engine control system - система управления двигателя ПРИЛОЖЕНИЕ 6 ОСОБЕННОСТИ ПЕРЕВОДА СТРУКТУР С ГЛАГОЛОМ В ПАССИВНОМ ЗАЛОГЕ. СТРУКТУРА to be+ Participle II.  Глагол в страдательном залоге переводится: 1 - сочетание глагола <<быть>> с краткой формой причастия. The wing is (will be, was) inspected. Крыло ( было ,будет) осмотрено. 2 - глаголом,оканчивающимся на <<ся>>, <<сь>>. Control surfaces are divided into primary and secondary control surfaces. Плоскости управления разделяются на основные и вспомогательные. 3-неопределенно-личной формой глагола в действительном залоге в 3 л. ед. числа (если не указывается действующее лицо) The Russian youth is given the widest opportunity for study. Российским молодым людям предоставляют самую широкую возможность для учебы. He was given a book. - Ему дали книгу  ПРИЛОЖЕНИЕ 7 Функции инфинитива в предложении и его перевод.  . ПРИЛОЖЕНИЕ 8  ПРИЛОЖЕНИЕ 9 ИНФИНИТИВНЫЙ ОБОРОТ <<for + сущ. (местоим.) + инфинитив>>.
ПРИЛОЖЕНИЕ 10 ИНФИНИТИВНЫЙ ОПРЕДЕЛИТЕЛЬНЫЙ ОБОРОТ.
ПРИЛОЖЕНИЕ 12 Функции герундия и его перевод. Переводится:
Подлежащее -инфин., сущ. Learning is useful. Учиться полезно. (Учеба полезна). | |||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
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