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prelims 2nd sem > powerplant > Flashcards

powerplant Flashcards

1
Q

what powers majority of the aircraft

A

turbine engines

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2
Q

who developed the first “jet engine”

A

Hero, Egyptian scientist and mathematician from Alexandria

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3
Q

when was the first “jet engine” developed

A

150 BC

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4
Q

what was the name of the basic engine made by hero

A

aeolipile

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5
Q

what consisted of the aeolipile

A

boiler, two hollow bent tubes mounted to a sphere, and the sphere

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6
Q

what was first known as the first “steam engine”

A

heron’s aeolipile

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7
Q

when was newton’s three laws of motion announced

A

1687

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8
Q

what is the first law of motion

A

an object at rest will stay at rest and an object at motion will stay in motion unless acted upon an external force

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9
Q

what is the second law of motion

A

force is equal to mass times acceleration

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10
Q

what is the third law of motion

A

for every action, there is an equal and opposite reaction

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11
Q

what did newton invent but didn’t work

A

steam wagon

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12
Q

how did the newton propelled the wagon?

A

generating steam in a boiler on the wagon

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13
Q

who made and when was the first patent gas turbine engine made?

A

1791 John Barber

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14
Q

when did the design production for the gas turbine engine made a full swing in america

A

early 1900s

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15
Q

pioneer in the development of a turbo supercharger that was used in WWI

A

Sanford A. Moss

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16
Q

who was credited to have the first flying test and when

A

Frank Whittle 1941

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17
Q

what was the first flying test aircraft

A

Gloster E28/29

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18
Q

discovered the principal that defines the action of air through a turbine engine and more

A

Bernoulli

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19
Q

Bernoulli’s theory

A
  1. Fluid is incompressible and not viscous
  2. There is no energy loss from the air and the wall of the pipe/orifice
  3. There is no heat energy transferred across the boundaries of the pipe to the fluid as either a heat gain or loss
  4. There are no pumps in the section of pipe under consideration
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20
Q

parts of gas turbine engine

A
  1. an air inlet
  2. compressor section
  3. combustion section
  4. turbine section
  5. exhaust section
  6. accessory section
  7. systems necessary for starting, lubrication, fuel supply, and auxilary purposes such as anti-icing, cooling, and pressurization
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21
Q

three types of compressors

A

centrifugal flow, axial flow, and centrifugal-axial flow

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22
Q

compression of inlet air is achieved by accelerating air outward perpendicular to the longitudinal axis of the machine

A

centrifugal flow

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23
Q

compresses air by a series of rotating and stationary airfoils moving the air parallel to the longitudinal axis

A

axial-flow engine

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24
Q

uses both axial and centrifugal flow to achieve the desired compression

A

centrifugal-axial flow

25
Q

four types of engine

A

turbojet, turbofan, turboprop, and turboshaft

26
Q

used to describe any gas turbine engine used in aircraft

A

turbojet

27
Q

first developed in Germany and England prior to WWII and is the simplest of all jet engines

A

turbojet engine

28
Q

has problems with noise and fuel consumption in the speed range that airlines fly. limited on range and endurance and mostly used in military aviation

A

turbojet

29
Q

four sections of turbojet engine

A

compressor, combustion chamber, turbine section, and exhaust

30
Q

passes inlet air at a high rate of speed to the combustion chamber

A

compressor section

31
Q

contains the fuel inlet and igniter for combustion

A

combustion chamber

32
Q

expanding air drives this, which is connected by a shaft to the compressor, sustaining engine operation

A

turbine

33
Q

the accelerated exhaust gases from the engine provide

A

thrust

34
Q

basic application of compressing air

A

igniting the fuel-air mixture, producing power to self-sustain the engine operation, and exhaust for propulsion

35
Q

advantages of turbojet engine

A
  1. relatively simple design
  2. capable of very high speeds
  3. takes up little space
36
Q

disadvantages of turbojet engine

A
  1. high fuel consumption
  2. loud
  3. poor performance at slow speeds
  4. limited in range and endurance
37
Q

when and who designed the first turboprop engine

A

between 1939 and 1942 by Gyorgy Jendrassik

38
Q

when did the first turboprop engine first flew and who made it

A

September 20, 1945 by Rolls Royce

39
Q

turbine engine that drives an aircraft propeller

A

turboprop

40
Q

efficient at lower flight speeds, burning less fuel and requiring significantly less runway for takeoff and landing

A

turboprop equipped aircraft

41
Q

airlines that operate regional aircraft to provide passenger air service to communities without sufficient demand to attract mainline service

A

air transport regional

42
Q

advantages of turboprop

A
  1. Very fuel efficient
  2. Most efficient at mid-range speed between
    250-400 knots (Mach 0.2-0.4 or 200-400+kph)
  3. Most efficient at mid-range altitudes of
    18,000-30,000 feet
43
Q

disadvantages of turboprop engine

A
  1. Limited forward airspeed
  2. Gearing systems are heavy and can break down
44
Q

engine in a for of gas turbine that is optimized to produce shaft power rather than jet thrust

A

turboshaft engine

45
Q

made to transfer horsepower to a shaft that turns a helicopter transmission

A

turboshaft

46
Q

advantages of turboshaft engine

A
  1. Much higher power-to-weight ratio than
    piston engines
  2. Typically smaller than piston engines
47
Q

disadvantages of turboshaft engine

A
  1. loud
  2. gear systems connected to the shaft can be complex and break down
48
Q

primary difference between helicopter and airplane

A

the way that the mechanics are designed to generate lift.

49
Q

use their rapidly spinning rotors to create the momentum required to lift the aircraft.

A

helicopters

50
Q

cold section of gas turbine engine consists of

A

air inlet duct and compressor

51
Q

part of the aircraft that brings air into the propulsion system.

A

inlet

52
Q

affects the performance of the propulsion system.

A

inlet design

53
Q

draws air into the engine, pressurizes it, and feeds it to the combustion chamber at speeds of hundreds of miles per hour.

A

compressor

54
Q

hot section of the gas turbine engine consists of

A

combustor, turbine, and exhaust

55
Q

fuel is combined with high pressure
air and burned here

A

combustor

56
Q

other word for combustor

A

burn

57
Q

used to turn the power turbine and produce thrust when passed through a nozzle.

A

resulting high temperature exhaust gas

58
Q

transforms a portion of the kinetic (velocity) energy of the exhaust gases into mechanical energy to drive the gas generator compressor and accessories.

A

turbine

59
Q

located directly behind the turbine section and ends when the gases are ejected at the rear in the form of a high-velocity exhaust gases.

A

exhaust section

prelims 2nd sem (5 decks)

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