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Файл:Jet Propulsion Engine Fundamentals английский язык для студентов специальности «Проектирование авиационных и ракетных двигателей». Учебное пособие
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напряжение принимает нулевое значение, они очень тонкие.
1. thermal distortion
2. failure
3. fluid dynamical
4. propeller thrust
5. constructional feature
6. rim speed
7. thrust output
8. air compressor
9. stress
10. steep
11. blade
12. outlet
13. thermal jet engine
14. auxiliaries
15. stress-strain characteristics
16. sustained period
17. exhaust gases
18. serviceability
19. tapered
20. bearing
21. choking of the flow
22. supercharger
23. axial velocity
24. bucket temperature
25. frontal area
26. gas seal
27. shaft power
28. propeller
29. jet
30. exhaust nozzle
31. thrust
32. root
33. strength
1.подшипник
2. турбинные лопатки
3. температура лопасти
4. осевой компрессор
5. вспомогательные
устройства
6.эксплуатационная
пригодность,
ремонтопригодность
7. мощность на валу
8. расход массы
9. реактивный
10. конический
11. паровая турбина
12. тяга
13. газонепроницаемое уплотнение
14. гидрогазодинамический
15. воздушный винт
16. теория упругих деформаций
17. нагнетатель
18. кольцо
19. прочность
20. температурный коэффициент
21. конструктивная особенность
22. остаточные напряжения
23. турбовинтовой двигатель
24. устройства
25. крутой
26. выпускное отверстие
27.воздушный компрессор
28. выходная мощность
29. тяга двигателя
30. лобовая площадь
13. Выбор окружной скорости – это компромисс между допустимым
напряжением и коэффициентом полезного действия турбины.
Task 14. Find the Russian equivalents for the English terms.
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34. turbine buckets
35. means
36. residual stresses
37.turbine-propeller engine
38. temperature gradient
39. steam turbine
40. power output
41. stress distribution
42. mass flow
43. annulus
44. propulsion engine
45. elastic theory
46. axial-flow compressor
31.окружная скорость
32. зависимость между напряжениями и
деформацией
33. осевая скорость
34. напряжение
35. повреждение
36. продолжительный
период
37. запирание потока
38. температурная
деформация
39. тяговый двигатель
40. воздушно-реактивный
двигатель
41.выхлопные газы
42. распределение напряжений
43. тяга воздушного винта
44. лопатка
45. выходное сопло
46. хвостовик, ножка
Task 15. Look through the texts (Task 7, 11) and find key sentences in each
paragraph.
Task 16. Write a summary to the text (Task 7)
Task 17. Sum up the text (Task 11).
Task 18. Skim the text and try to understand its subject matter.
In most designs the blades are twisted to maintain a favorable angle of attack for
the fluid throughout its length. In the early development of the turbo-jet, blading
failures did occur, but they are now a rarity. The difficulties were overcome by
increased accuracy in the manufacture of the blades, avoidance of small radii at root
junctions, better analysis of vibration problems, and improved metallurgy.
Since improving turbine efficiency and output are related to ability to operate
with higher temperatures, developments aimed at raising the permissible operating
temperature of the turbine are of great importance. One promising approach is the
application of ceramic coatings on the turbine blades to take the impact of the hot
gases. The problem here is to develop a ceramic coating of high melting point which
will bond to the metal and will have a coefficient of expansion close enough to that
of the metal to prevent the coating from cracking or flaking off. Another approach
proposes to let cooling liquid flow through a passage in the root of the blades.
A general thermodynamic treatment can be applied to both impulse and reaction
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stages by considering an intermediate stage of a multistage reaction turbine; the
intermediate stage typifies the general case of a turbine stage. In such a stage the
stationary blade row is the counterpart of the nozzle of an impulse stage.
(Kates E.K. Diesel and High Compression Gas Engines)
Task 19. Choose the right variant to fill in the gap.
1. In most designs … are twisted to maintain a favorable angle of attack for the
fluid throughout its length.
a) the buckets
b) the blades
c) the ducts
2. The difficulties were overcome by increased accuracy in … of the blades,
avoidance of small radii at root junctions, better analysis of vibration problems, and
improved metallurgy.
a) the manufacture
b) the design
c) the construction
3. In the early development of…, blading failures did occur, but they are now a
rarity.
a) the turbojet
b) the turboprop
c) the jet engine
4. One promising approach is the application of … to take the impact of the hot
gases.
a) composite coatings on the turbine blades
b) ceramic coats on the turbine blades
c) ceramic coatings on the turbine blades
5. It is critical to develop a ceramic coating of high melting point which will bond
to the metal and will have … close enough to that of the metal to prevent the coating
from cracking or flaking off.
a) a coefficient of expansion
b) a coefficient of compression
c) a coefficient of friction
6. A general thermodynamic treatment can be applied to both impulse and
reaction stages by considering an … stage of a multistage reaction turbine.
a) initial
b) final
c) intermediate
Task 20. Collect all the possible supplementary information on the theme of Unit
2 and present it to your groupmates.
23
UNIT 3. The Combustion Chamber
Adjectives
Degrees
Positive
Comparative
Superlative
Synthetic form
-er
-est
Monosyllabic
adjectives
cheap
cheaper
cheapest
Adjectives of two
syllables ending in y, -er, -ow, -le
easy
easier
easiest
clever
cleverer
cleverest
narrow
narrower
narrowest
simple
simpler
simplest
Adjectives of two
syllables having the
stress on the second
syllable
polite
politer
politest
Analytical form
more
most
Other adjectives of
two syllables
famous
more famous
most famous
Adjectives of three
or more syllables
difficult
more difficult
most difficult
Degrees
Positive
Comparative
Superlative
good
better
best
bad
worse
worst
many (much)
more
most
little
less
least
old
older
oldest
elder
eldest
far
farther
farthest
further
furthest
TEXT: THE COMBUSTION CHAMBER
Grammar: Degrees of Comparison of Adjectives
Task 1. Study the formation of the degrees of comparison of qualitative adjectives
in English and translate the sentences into Russian.
Task 2. Give the comparative and the superlative degree of the following
adjectives.
Special forms
24
advantage - преимущество
air-fuel mixture – топливно-воздушная
смесь
air pollution – загрязнение воздушной
среды
annular combustion chamber –
кольцевая камера сгорания
capable to withstand – в состоянии
выдержать, противостоять
centrifugal compressor –
центробежный компрессор
corrosive effects – коррозионные
воздействия
double ring – двойное кольцо
flame tube – жаровая труба
to install - устанавливать
multiple combustion chamber layout –
камера сгорания с отдельными
жаровыми трубами
layout – планировка, расположение,
схема, компоновка
to manufacture –изготовлять,
производить
fuel-efficient – оптимальный расход
топлива
one inside the other – один внутри
другого
overhaul – ремонтировать
products of combustion – продукты
сгорания
to reduce – сокращать, частично
решать (проблемы)
separate outer casing – отдельный
внешний кожух
shaped – имеющие форму
tubo-annular combustion chamber –
трубчато-кольцевая камера сгорания
Sincere, light, busy, hot, interesting, wide, common, noble, brave, good, active,
nervous, fine, cold, active sharp, little, dirty, far, wonderful, old, narrow, severe, able,
comfortable, bad, wet, important.
Task 3. Study the following words and word combinations and learn them by heart.
Task 4. Translate the words into Russian. Mind suffixes.
Mechanic – mechanical, burn – burning, to differ – different, radial – radially, present –
presently, case – casing, to combust – combustion, to compress – compressor , to pollute –
pollution, to corrode – corrosion – corrosive, rough – roughly, to cool - cooling.
Task 5. Read and translate the following international words.
Mixture, radially, design, form, to group, compact, problem, temperature, effect,
product, efficient, acceleration, positive, structure, balance, adequate.
Task 6. Translate the sentences into Russian using the terms from Task 3.
1. The flame tube of annular combustion chambers is in the form of a double ring,
25
which in turn is fitted into an annular casing of two more rings.
2. The multiple combustion chamber layout is used with engines having
centrifugal compressor.
3. Tubo-annular chambers are easier to manufacture and overhaul, while annular
chambers, besides possessing these advantages, are also more compact.
4. The acceleration of the air-fuel mixture imparts positive thrust to the
combustion chamber structure.
5. All combustion chambers must be capable to withstand very high temperatures,
rapid changes of temperature and corrosive effects produced by the products of
combustion.
Task 7. Read the following text carefully paying attention to the words in bold
type. Try to understand the subject matter of the text and be ready to answer the
following questions.
1. What are combustion chambers designed for?
2. What part of the jet engine is before the combustion chamber?
3. How many layouts of the combustion chamber are there?
4. What type of compressors is the multiple combustion chamber layout
used with?
5. What is the disposition of flame tubes in the multiple combustion
chamber layout?
6. What is a common design of combustion chambers nowadays?
7. What is the form and disposition of the flame tube in annular combustion
chambers?
8. What is the disposition of flame tubes in tubo-annular combustion
chambers?
9. What differs tubo-annular combustion chambers from annular
combustion chambers?
10. What is the purpose of the combustion chambers in a turbine engine?
11. What requirements must all combustion chambers comply with?
TEXT
THE COMBUSTION CHAMBER
Combustion chambers are mechanical devices for burning air-fuel mixture. They
may be installed in the engine in a number of different ways. The multiple combustion
chamber layout is used with engines having centrifugal compressor. In this layout a
number of flame tubes are disposed radially round the engine. Annular and tubo-annular
designs of combustion chambers are more often used presently.
The flame tube of annular combustion chambers is in the form of a double ring,
which in turn is fitted into an annular casing of two more rings. Tubo-annular
combustion chambers have flame tubes grouped round the engine, as in the multiple
26
layout, but instead of each having a separate outer casing, they are all disposed in a
the combustion chambers, air pollution, nozzle, corrosive effects, fuel-efficient,
blades, layout, outer casing, flame tube, centrifugal, a double ring, the air stream,
tubo-annular combustion chambers
common annular casing, shaped like two broad rings, one inside the other.
Tubo-annular chambers are easier to manufacture and overhaul, while annular
chambers, besides possessing these advantages, are also more compact. Annular
chambers are more fuel-efficient and reduce many of the problems of air pollution. All
combustion chambers must be capable to withstand very high temperatures, rapid
changes of temperature and corrosive effects produced by the products of combustion.
The purpose of the combustion chambers in a turbine engine is to expand the air
passing through the engine by burning fuel in the air stream. The heat released by the
burning fuel adds energy to the air in the form of velocity. The acceleration of the airfuel mixture imparts positive thrust to the combustion chamber structure.
Roughly, one-fourth of the air entering the combustion chamber area is burnt with
the fuel. The balance of the air serves to keep the temperature of the heated gases
down to a level, which will not damage the turbine nozzle and blades. For this reason,
the design of the combustion chambers must be such that adequate fuel combustion is
accomplished and that proper cooling is attained.
(The Jet Engine)
Task 8. Find in the text the English equivalents for the following words and word
combinations.
Камера сгорания, устройство, сжигание, воздушно-топливная смесь,
двигатель, различные способы, центробежный компрессор, схема, жаровые
трубы, располагаются, кольцевая конструкция, трубчато-кольцевая
конструкция, кольцевая оболочка, имеющий форму, ремонтировать,
преимущество, оптимальный расход топлива, выдерживать, коррозионное
воздействие, продукты сгорания.
Task 9. Fill in the gaps with appropriate words from the box.
1. The multiple combustion chamber __________ is used with engines having
__________compressor.
2. The __________of annular combustion chambers is in the form
of___________, which in turn is fitted into an annular casing of two more rings.
3. Annular chambers are more _________and reduce many of the problems
of___________.
4. The purpose of __________ in a turbine engine is to expand the air
passing through the engine by burning fuel in___________.
5. The balance of the air serves to keep the temperature of the heated gases
down to a level, which will not damage the turbine _________ and __________.
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6. All combustion chambers must be capable to withstand very high
1. The flame tube of annular combustion
chambers is …
2. Annular chambers are …
3. Combustion chambers are …
4. In the multiple combustion chamber a
number of flame tubes …
5. The multiple combustion chamber layout
is used …
6. All combustion chambers must …
7. Tubo-annular combustion chambers
have …
8. Annular and tubo-annular designs of
combustion chambers are …
1. are disposed radially round the engine.
2. with engines having centrifugal
compressor.
3. be capable to withstand very high
temperatures, rapid changes of temperature
and corrosive effects produced by the
products of combustion.
4. more fuel-efficient and reduce many of
the problems of air pollution.
5. in the form of a double ring which in turn
is fitted into an annular casing
6. mechanical devices for burning air-fuel
mixture.
7. more often used presently.
8. flame tubes grouped round the engine and
disposed in a common annular casing,
shaped like two broad rings, one inside the
other.
temperatures, rapid changes of temperature and __________ produced by the products of
combustion.
7. ____________have flame tubes grouped round the engine, as in the multiple
layout, but instead of each having a separate__________, they are all disposed in a
common annular casing, shaped like two broad rings, one inside the other.
Task 10. Complete the sentences with appropriate endings.
Task 11. Read the following text and try to understand its subject matter.
Translate the text into Russian. Use the dictionary if necessary.
As an integral and may be the most important component of the thrust chamber
assembly, the combustion chamber must be specifically designed to satisfy the
operating requirements of engine. The basic components of a combustion chamber
are the coolant inlet and discharge manifolds, a cooled internal liner consisting of
tubes or channels and an external structural assembly which is capable to carry all
structural and flight loads such as thrust, pressure, and vibrations. The contour of the
inner liner is aerodynamically designed to provide maximum performance and thrust
for the engine operating conditions.
Combustion chambers are generally categorized by the cooling method or the
configuration of the coolant passages, where the coolant pressure inside may be as
high as 30 MPa. The high combustion temperatures which may exceed 3600 K and
the high heat transfer rates, peak values may reach 100 MW/m2 encountered in a
28
combustion chamber present a formidable challenge to the designer. To meet this
challenge, several chamber cooling techniques have been utilized successfully.
Regenerative cooling is the most widely used method of cooling a combustion
chamber and is accomplished by flowing high-velocity coolant over the back side of
the chamber hot gas wall to convectively cool the hot gas liner. The coolant with the
heat input from cooling the liner is then discharged into the injector and utilized as a
propellant. Quite a large number of engines have a "tubular wall" combustion
chamber design. The primary advantage of the design is its light weight and the large
experience base that has accrued however this method exceed its application limits at
pressures in the range of 10 MPa. The best solution to date is the "channel wall"
design, so named because the hot gas wall cooling is accomplished by flowing
coolant through rectangular channels, which are machined or formed into a hot gas
liner fabricated from a high-conductivity material, i.e. oxygen-free copper or copper
alloys such as Narloy Z (CuAgZr).
Film cooling provides protection from excessive heat by introducing a thin film of
coolant or propellant through orifices around the injector periphery or in the chamber
wall near the injector or chamber throat region. This method is typically used in high
heat flux regions and in combination with regenerative cooling.
With ablative cooling, combustion gas-side wall material is successively
sacrificed by melting, vaporization and chemical changes to dissipate heat. As a
result, relatively cool gases flow over the wall surface, thus lowering the boundarylayer temperature and assisting the cooling process. Ablative cooling may be applied
either to the entire combustion chamber liner or to the throat section alone. Typically
all solid rocket boosters have ablative cooled nozzles. Sample chambers with
partially ablative cooled throat sections are the Viking or more recent the RS-68.
Although successfully applied this cooling method has a major drawback since it
doesn’t allow for modifications of the engine burn time.
A radiation cooled chamber transmits the heat from its outer surface, chamber or
nozzle extension. Radiation cooling is typically used for small thrust chambers with a
high-temperature wall material (refractory) and in low-heat flux regions, such as a
nozzle extension. An example of an entirely radiation cooled thrusters is the RS-21
Mariner/Viking Orbiter spacecraft, RL 10B or similar upper stage engines have
radiation cooled ceramic nozzles.
(Oscar J. Haidn Advanced Rocket Engines)
Task 12. Answer the questions and use them as a plan for retelling the text.
1. Why is it critical for the combustion chamber to be specifically designed?
2. What are the basic components of a combustion chamber?
3. What ways could combustion chambers be categorized?
4. What is regenerative cooling?
5. What is the advantage of a ‘tubular wall’ combustion chamber?
6. What specifies the ‘channel wall’ design?
7. What does film cooling provide?
29
8. What is ablative cooling?
1. thrust chamber assembly
2. combustion chamber
3. to design
4. operating requirements
5. coolant inlet
6. discharge manifold
7. load
8. pressure
9. performance
10. engine
11. thrust
12. heat transfer
13. rate
14. regenerative cooling
15. high-velocity
16. injector
17. propellant
18. high-conductivity
19. oxygen-free
1. скорость, коэффициент
2. давление
3. тяга
4. бескислородный
5. корпус, футеровка, покрытие
6. высокоскоростной
7. горловина камеры сгорания
8. коллектор
9. инжектор
10. испарение
11. топливо
12. плавление, оплавление
13. дросселирующее отверстие (для
дренажа)
14. радиационное охлаждение
15. проектировать
16. низкая тепловая нагрузка
17. поток
18. керамический
9. Where may ablative cooling be applied?
10. What does a radiation cooled chamber do?
11. Where is radiation cooling used?
Task 13. Translate the following sentences into English.
1. Камера сгорания – это механическое устройство, предназначенное
для сжигания воздушно-топливной смеси.
2. Камера сгорания с отдельными жаровыми трубами используется в
двигателях, имеющих центробежный компрессор.
3. В камере сгорания с отдельными жаровыми трубами ряд жаровых
труб располагается радиально вокруг двигателя.
4. Жаровая труба кольцевой камеры сгорания имеет форму двойного
кольца.
5. Трубчато-кольцевая камера сгорания имеет жаровые трубы,
сгруппированные вокруг двигателя.
6. Кольцевые камеры сгорания более оптимальны по расходу топлива
и уменьшают многие проблемы загрязнения воздушной среды.
7. Все камеры сгорания должны выдерживать высокие температуры,
быстрое изменение температуры и коррозионное воздействие продуктов
сгорания.
Task 14. Find the Russian equivalents for the English terms.
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