97. SEMANAS 2018

Question

Q1. When it is produced stagnation pressure losses in the inlets:

Answer 1

A. Increase thrust

Answer 2

B. Increase Specific Fuel Consumption

Answer 3

C. Decrease thrust

Answer 4

D. A and B are correct

Answer 5

Generally, subsonic inlets are named “Pitot”

Answer 6

Typical parameters are NACA Serie 1 profiles

Answer 7

Drag is not due to inlet outer surface

Answer 8

The shape is aerodynamically smooth

Answer 9

A. 2D or spike

Answer 10

B. 3D or wedge

Answer 11

C. 2D or wedge

Answer 12

D. A and B are correct

Answer 13

Increase the pressure of the air mass received

Answer 14

Take the air to the combustion section

Answer 15

Provide bleed air for cabin pressure and other systems

Answer 16

All are correct

Answer 17

A. Bi-directional

Answer 18

C. Centrifugal

Answer 19

D. B and C are right

Answer 20

Stabilizer

Answer 21

Front case

Answer 22

Divergent nozzles

Answer 23

Convergent nozzles

Answer 24

Divergent and convergent nozzles

Answer 25

None of them

Answer 26

Single-spool is a type of axial compressors

Answer 27

Multi-spool is a type of centrifugal compressors

Answer 28

Generally, in aviation are used single-spool and two spools

Answer 29

Multi-spool is a type of axial compressors

Answer 30

Boundary layer can stall

Answer 31

Will cause transonic zones

Answer 32

Can cause heating problem

Answer 33

Nothing can go wrong

Answer 34

Variable IGV

Answer 35

Variable stator blades

Answer 36

They close when velocity reduces

Answer 37

None of the above

Answer 38

A. Provides information of pressure ratio an equivalent flow for a throttle setting (IDLE-100%)

Answer 39

B. Does not give info relative to throttle settings

Answer 40

C. Gives info relative to weather conditions

Answer 41

D. Both A and C are correct

Answer 42

Ensure stable fuel burn with max. Thermal efficiency in large conditions ranges

Answer 43

Are not used for aviation engines

Answer 44

Max temperature (850-1700oC) due to turbine materials

Answer 45

Combustion is initiated by an electric spark from an igniter plug

Answer 46

Corrugated strip cooling

Answer 47

Machined cooling ring

Answer 48

Splash cooling strip

Answer 49

Capsule icing allocation

Answer 50

Tubo-annular

Answer 51

All the above

Answer 52

Both A and B are correct

Answer 53

Both A and B are false

Answer 54

A. Compressor

Answer 55

B. IMPULSE TURBINE

Answer 56

C. REACTION TURBINE

Answer 57

D. B and C

Answer 58

Turbofan of low derivation

Answer 59

Turbofan of high derivation

Answer 60

Piston engines

Answer 61

Because it implies more drag inside engine

Answer 62

Indeed, it is a really efficient method, especially in military aviation

Answer 63

Because of increment in thrust, that is proportional to (Tpc)^1/2 / (T noPC)^1/2

Answer 64

Because the increment in thrust follows a linear gradient, so that is not too much.

Answer 65

A. Afterburning provides the best method of thrust augmentation for short periods.

Answer 66

B. Afterburning provides the worst method of thrust augmentation for short periods.

Answer 67

C. Afterburning provides the best method of thrust augmentation for long periods.

Answer 68

D. Afterburning provides the worst method of thrust augmentation for long periods.

Answer 69

A. It is a method of augmenting the basic thrust of an engine.

Answer 70

B. For military aircraft improve combat performance

Answer 71

C. It is the worst method of thrust augmentation for short periods.

Answer 72

D. A and B are correct

Answer 73

A. The nozzle expands

Answer 74

B. the nozzle contracts

Answer 75

C. the nozzle stays fixed

Answer 76

D. the nozzle opens and closes periodically

Answer 77

A. low derivation

Answer 78

B. high derivation

Answer 79

C. turboreactors

Answer 80

D. a and b are correct

Answer 81

Commercial planes

Answer 82

Fighters planes

Answer 83

None of the above

Answer 84

Helicopters

Answer 85

Control of bearing axial loads

Answer 86

Cooling the engine

Answer 87

Measure the ground speed of the plane

Answer 88

Engine anti-icing

Answer 89

Prevent oil leakage from engine bearing chambers

Answer 90

Control cooling airflows

Answer 91

Prevent ingress of the mainstream gas into turbine disc cavities

Answer 92

All of the above

Answer 93

Avoid the formation of chemtrails

Answer 94

It is used for cooling and pressurization

Answer 95

Is more powerful than high compression air flow

Answer 96

None of them

Answer 97

Venturi effect

Answer 98

De-icing systems

Answer 99

Cooling oil

Answer 100

All are wrong

Answer 101

Control of thrust

Answer 102

Hydraulic controls of engine system

Answer 103

Oil cooling

Answer 104

All are right

Answer 105

James Patterson, the inventor of the fuel

Answer 106

Jet Purpose

Answer 107

Jet Propeller

Answer 108

None of above

Answer 109

It is flamable and dangerous

Answer 110

It isn ́t ecological

Answer 111

Fuel isn ́t so important for aeronautic operators

Answer 112

It represents almost a 40%, of the total cost, of a flight

Answer 113

AVCAT ( Aviation Carrier Turbine fuel)

Answer 114

GPA (General Purpose Aviation fuel)

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97. SEMANAS 2018

Description

Resource summary

Question 1

Question 2

Question 3

Question 4

Question 5

Question 6

Question 7

Question 8

Question 9

Question 10

Question 11

Question 12

Question 13

Question 14

Question 15

Question 16

Question 17

Question 18

Question 19

Question 20

Question 21

Question 22

Question 23

Question 24

Question 25

Question 26

Question 27

Question 28

Question 29

Question 30

Question 31

Question 32

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	Created by Ismael Vázquez over 6 years ago