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TURBINE 360 > MOD 1-2 > Flashcards

MOD 1-2 Flashcards

1
Q

Jet propulsion can be defined as

A

a method of propulsion produced when a mass of air is given acceleration

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2
Q

Sir Isaac Newton second law of motion

A

Force = mass x accelaration

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3
Q

Leonardo De vinchi create the first example of a reaction turbine and it called

A

chimnay jack

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4
Q

Sir Frank Little is consider the father of

A

of the jet engine, first flight Gloster E28

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5
Q

first German flight of a jet propeller

A

HE178-1100 Lbs Trust 400 m/h

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6
Q

Turbine Engine classifications

A

Turbo jet Turbo fan Turbo prop Turbo shaft

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7
Q

what is TSFC

A

Thrust Specific Fuel Consumption, how much fuel is consume to produce thrust

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8
Q

Turbo Jet characteristics

A

Low Thrust High TSFC at low altitudes and lower speeds long take off roll -disadvantage small frontal area lightest specific weight (weight for power produce) takes advantage of high ram pressure

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9
Q

Turbo Fan Characteristics

A

-increase thrust at speeds for short take off , but not falling off at higher speeds -weight lighter than TP heavier than TJ -medium TSFC -medium frontal area -reduce noise from turbo jet

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10
Q

Turbo prop characteristics

A

-high propulsive efficiency at low speeds -more complicated and heavier than TF and TJ -lowest TSFC -large frontal area -efficient reverse system (180 degree)

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11
Q

what is propulsion efficiency

A

is an indication of how much energy is being wasted or lost

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12
Q

turbo shaft

A

similar to turbo prop out to a transition or gearbox can not get a propulsive efficiency

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13
Q

3 Mayor sub classification of a gas turbine

A

axial centrifugal axial-centrifugal

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14
Q

why turbo shaft or turbo prop required gearbox

A

to reduce the speed of the blades or propeller not allowing get to the speed of sound

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15
Q

basic components of a turbine

A

air inlet, compressor, diffuser, combustors, turbine, tail pipe and jet nozzle

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16
Q

common engine identification

A

1-atmosphere

2-face compressor

3-discharge freom final compresor

4-combustion discharge

5-turbine section

6-turbine discharge

7- exhaust

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17
Q

what is creep strenght

A

the ability of a metal to resist slow deformation from strees of time, temp, load

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18
Q

engine cycle definition

A

VARIES BETWEEN MANUFACTURES

May be a start and RPM exceeding 80% N2

Maintenance run for leak check may not be counted as a cycle if RPM is kept below 80% N2

Some may only count a cycle if the wheels leave the

ground ( can do a full power run and not count a cycle

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19
Q

What is Yield Strength

A

the point when a metal takes on a permanent set due to application of a load

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20
Q

what is Rupture Strength

A

The point at which a metal will fail due to continual loading for long periods of time

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21
Q

Aluminum alloys carachteristics

A

Temperatures up to about 500

good strength to weight ratios

typical use-inlet ducts, centrifugal compressor components, accessory drive cases

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22
Q

Titanium alloys

A

temperatures up to about 1000 F

high strength, low density

•

typical use

-

centrifugal flow compressors, axial flow

compressor rotors and blades

ignition point is lower than melting point

does not dissipate heat well (low density)

Cold section parts

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23
Q

Steel alloys characteristics

A

temperatures up to about 1000 to1200 depending on the alloying elements

-low cost (relative to cost of other materials) ease of fabrication and machining

•typical use

compressor stators, engine structural members,compressor shafts, gears, cases

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24
Q

Nickel base alloy

A
  • temperatures up to about 1200 to1800 F. depending on the alloying elements
  • good high temperature strength

typical use–turbine wheels,turbine blades, shafts, combustion

liners

•Hot section parts

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25
Q

Cobalt base alloy

A

withstands high temperatures

  • melting point–2700 F
  • expensive
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26
Q

4 types cooling

A

Convection -heat disipades to the air

Inpingment-bleed air blown onto a hot part

Film-bleed air through holes

transpiration cooling -mesh

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27
Q

What is

N1

N2

Ng

Nf

A

N1 -Rotational RPM low compressor and turbine )

N2-rotation RPM high pressure compresor and turbine

Ng -RPM of the gas producer

Nf -RPM of free turbine

28
Q

what is

ITT

TOT

TIT

Tt15

A

ITT-Inlet turbine temp

TOT- turbine outlet temp

TIT-turbine inlet temp

Tt15 -Turbine temp station 5

29
Q

N1 and N2 is a measurment of what

A

rotational speed in % RPM

30
Q

what is primary creep,secundary creep and tetiary creep

A

primary is a significant change that happens in a short period of time secundary is the slow deformation of the blade over a long period of time, tertery creep is a fast deterioration of the blade.

31
Q

three prymary indications necessary for a gas turbine engine are

A

RPM

TEMPERATURE

TORQUE OR THRUST

32
Q

Creep strenght is ussually referred to in terms of ?

A

time,temp,load

33
Q

Brayton cycle is also known as ?

A

constant pressure cycle because the pressure in the combustion section remains the same

34
Q

difference betwen potencial energy and kenetic energy

A

potencial energy relates to the mass, gravity and height and kenetic energy is in motion not in rest

35
Q

difference between heat and temp

A

heat is the transfer of thermal energy and temp is the average kenetic energy

36
Q

potencial energy can also reffered as ?

A

static pressure

37
Q

kenetic energy canbe referred to as ?

A

dynamic pressure

38
Q

according to bernoulis law, when fluid flows thruogh a divergent duct does the pressure increase or decrease

A

velocity decrease so pressure increase

39
Q

according to bernoulis law, when fluid flows thruogh a convergent duct does the pressure increase or decrease

A

velocity increase so pressure decrease

40
Q

in the Bryton cycle what section of the engine represents by point B to C

A

Combustion

41
Q

in the Bryton cycle what section of the engine represents by point D to E

A

exhaust -turbine trust for propulsion (turbo jet and turbo fan)

42
Q

in the Bryton cycle what section of the engine represents by point D to F

A

exhaust -turbine trust for propulsion (turbo prop and turbo shaft)

43
Q

in the Bryton cycle what section of the engine represents by point C to D

A

Turbine

44
Q

in the Bryton cycle what section of the engine represents by point F to G

A

represents the energy left in the gases after the last turbine (in a turbo prop).

45
Q

in the Bryton cycle what section of the engine represents by point A to B

A

Compresor

46
Q

on the engine map why does the pressure increase trought the convergent duct instead of decrease ?

A

because the divergent inside of the convergent duct

47
Q

where is the highest total pressure in the engine

A

last part of the compressor stage

48
Q

where is the lowest velocity ?

A

getting into the combustion section

49
Q

why the specific heat of air under constant pressure, a higher BTU value that the specific heat air under constant volume

A

because the volume increase in constant pressure and requires more energy

50
Q

performance limitation

A

RPM

turbine temp

torque or thrust

51
Q

total energy= to?

A

potencial energy +kenetic energy

or

static pressure + velocity

52
Q

total pressure = to?

A

static pressure +dynamic pressure

53
Q

The area of a ____________decreases in

the direction of fluid is flowing

A

convergent duct nozzle

54
Q

The area of a ______________increases in the direction of fluid is flowin

A

divergent duct (diffuser )

55
Q

what is thermal efficency ?

A

A ratio of the engines energy output (thrust or

torque), to the fuel energy input

56
Q

horsepower is equivalent to ?

A

1 HP = 33000 ft/min

1 HP = 550 ft/sec

57
Q

amount of energy required to raise 1 # of air under constant volume ?

A

0.1715 BTU

58
Q

amount of energy required to raise 1 # of air under constant pressure ?

A

0.24 BTU

59
Q

specific heat formula what are the constants and what is Wa, delta T and |Cp ?

A
60
Q

In the airflow through a convergent or divergent duct, the potential energy can also be referred to as __________.

A

static pressure

61
Q

. In the airflow through a convergent or divergent duct, the kinetic energy can also be referred to as __________.

A

dynamic pressure

62
Q

According to Bernoulli’s Principle, when a fluid flows through a convergent duct, does the total pressure increase, decrease or remain the same?

A

decrease

63
Q

According to Bernoulli’s Principle, when a fluid flows through a divergent/diffusing duct, does the total pressure increase, decrease or remain the same?

A

increase

64
Q

According to the General Gas Law, does “V” represent velocity or volume?

A

volume

65
Q

According to the General Gas Law, if “V” is held constant and “P” increases, does “T” increase or decrease?

A

increase

TURBINE 360 (3 decks)

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