Use LEFT and RIGHT arrow keys to navigate between flashcards;
Use UP and DOWN arrow keys to flip the card;
H to show hint;
A reads text to speech;
88 Cards in this Set
- Front
- Back
|
In aircraft taxiing at a steady speed can be used to determine |
Newtons first law of motion |
|
|
Newtons third law of motion explains why an operating jet engine produces |
Forward thrust |
|
|
Which type of duct would decrease velocity and increase the pressure of a gas as it passes through? |
Divergent |
|
|
The combination of decreased pressure above an airfoil and the increased pressure below the airflow produces lift is best described by |
Bernoulli's principle |
|
|
Foot pounds and inch pounds are units of measure for |
Work |
|
|
What does fuel for an engine represent? |
Potential energy |
|
|
Which section of a jet engine continually supplies air and maintains pressure? |
Compressor |
|
|
Temperature of compressed air in a jet engine must be raised to |
Increase energy |
|
|
Which section of the jet engine introduces in burns fuel? |
Combustion |
|
|
How many British thermal units does the heat content per pound of kerosene produce? |
18,500 |
|
|
The efficiency of a jet engine is often referred to as |
Thermal efficiency |
|
|
The product of thermal efficiency and propulsive efficiency is |
Overall efficiency |
|
|
To measure barometric pressure you would use a |
Barometer |
|
|
What effect does moisture content or humidity have on density of air? |
More moisture less dense |
|
|
Due to the divergent design of the diffuser, air pressure |
Increases |
|
|
The air temperature of a jet engine gradually rises across the compressor to the diffuser outlet as a result of |
Compression |
|
|
Where is the highest point of temperature reached in an engine? |
Combustion section |
|
|
Which engine component meters fuel for combustion? |
Fuel control |
|
|
What happens to the energy that is absorbed by the turbine wheel? |
It is returned to the compressor |
|
|
What is the required velocity for air and gases flowing through a jet engine? |
Greater velocity exiting than entering |
|
|
The velocity of the stream of air that flows through a jet engine reaches its highest point at the |
Ejector nozzle |
|
|
What is the general flow of gases from the combustion chamber? |
Parallel to the axis of the rotor shaft |
|
|
Gases enter the jet engines first stage turbine wheel blades from the |
Turbine stator |
|
|
When two or more turbine wheels are used in a jet engine which component is placed directly in front of each turbine wheel? |
Turbine stator (nozzle diaphragm) |
|
|
A jet engine derives its name from its design in that it uses |
And exhaust gas driven turbine wheel to drive its compressor |
|
|
A turbo supercharger is essentially a |
High-capacity air pump |
|
|
The two forces that air is subjected to after it is drawn into the guide vanes of a centrifugal compressor are |
Rotational and centrifugal |
|
|
A constructional feature of the centrifugal compressor is at the impeller |
Is forged as a single unit |
|
|
The jet engine compressor that is cheaper to manufacture is the |
Centrifugal type because of its fewer parts |
|
|
Which is a constructional feature of an axial flow compressor casing? |
Split along the horizontal centerline |
|
|
The percentage of combustion efficiency of a gas turbine is usually between |
95 and 100 |
|
|
What is the most probable cause of a flame out of a jet engine flying at 40,000 feet with a constant engine revolutions per minute a 50%? |
The RPM is too low |
|
|
The excess airflow that is not burned in the combustion section is used to |
Mix with and cool the burned gases |
|
|
The inner and outer surfaces of an annular type combustion chamber are formed by |
Interlocking stainless steel bands |
|
|
Fuel that accumulates after a failed start is |
Drained overboard by a drain system |
|
|
The parts on a can-annular combustion section must be removed in a specific order because of the |
Combustion chamber crossover tubes |
|
|
What is the most common type of fuel nozzle system? |
Pressure atomizing |
|
|
Three types of turbine in vane assemblies used in jet engines are impulse reaction and |
Reaction-impulse |
|
|
The fir tree method of attaching turbine blades to the turbine rotor disc is preferred because |
Of the temperature differential between the turbine rotor disc and the blades |
|
|
In a non-afterburning engine the exhaust duct connects the turbine outlet and the |
Jet nozzle |
|
|
The purpose of the exhaust duct is to |
Straighten exhaust gas flow |
|
|
What is one common type of variable area orifice that is used on augmenters? |
Segmented flap |
|
|
The purpose of an augmentor in a jet engine is to |
Augment the maximum thrust capability of the basic engine |
|
|
How many different types of loads can be imposed on a jet engine bearing? |
Three |
|
|
When you handle jet engine bearings you must change cotton gloves frequently because they |
Get soaked with sweat |
|
|
Before inspecting new jet engine bearings you should |
Remove the preservative coding |
|
|
Next to contamination and improper lubrication what is the greatest enemy of anti-friction bearings? |
Improper removal |
|
|
The most commonly used bearing removal tools include |
Arbor presses and bearing pullers |
|
|
Which type of defect appears on bearings as a result of bearing parts striking together? |
Nicks |
|
|
Which type of defect appears on bearings as a result of small particles of foreign material becoming lodged between the rollers? |
Grooves |
|
|
Excessive bearing wear can usually be detected by |
Roughness of the metal |
|
|
Before you install separable bearings you must ensure the |
Bearings are a matched set |
|
|
Of the following the recommended method of expanding a bearing race before installation is to use a |
Hot oil bath |
|
|
The reduction gearbox on a F100-PW-220 engine reduces speed between the main fuel gear pump in the engine driven main gearbox by |
52% |
|
|
Which turbine stages on an F100-PW-220 engine drive the front compressor? |
Third and fourth |
|
|
What is one advantage of a modular engine? |
Entire engines are not withheld from service |
|
|
One advantage of the modular engine concept is that it eliminates the need to |
Return whole engines to depot for overhaul |
|
|
On which module of an F100-PW-220 engine is the stator generator mounted? |
Gearbox |
|
|
When discussing a jet engine and the location of its parts you must always do so as if you were standing at the |
Rear of the engine |
|
|
External flanges on the F100 engine are referred to by |
Letter designations |
|
|
On an F100-PW-220 engine the leading edge vanes are hollow |
So that anti-icing air can flow through them |
|
|
On an F100-PW-220 engine, the total temperature (Tt2) sensor sends electronic signals to the |
Digital electronic engine control (DEEC) |
|
|
The F100-PW-220 core module proximate splitter which divides airflow from the front compressor into fan airflow and primary airflow is contained in the |
Compressor intermediate case |
|
|
On an F100-PW-220 engine which stages of compressor stator vanes are variable? |
Fourth and fifth |
|
|
On an F100-PW-220 engine which stage of compression provides anti-icing air for the engine inlet? |
13th |
|
|
On an F100-PW-220 engine, which devices attach the combustion chamber assembly to the diffuser case? |
Eight mounting bolts |
|
|
On an F100-PW-220 engine, The front compressor drive turbine shaft is connected to the front compressor rotor by |
The turbine shaft nut coupling |
|
|
On an F100-PW-220 engine, The augmentor spray rings are pressure sensitive and can adjust their fuel nozzle openings in response to |
Fuel pressure |
|
|
Which component on an F100-PW-220 engine sends a signal to drive the primary actuator flexible shaft? |
Convergent exhaust nozzle control (CENC) |
|
|
On an F100-PW-220 engine, the gearbox module is driven by the rear compressor through |
A gearbox drive shaft |
|
|
How many stages are in the inlet fan module of the F119-PW-100 engine? |
Three |
|
|
Engine stations on the F119 engine are identified by |
Numerical designations |
|
|
In addition to the augmentor what is the other major assembly on the F119-PW-100 engine? |
Gearbox |
|
|
Where is the No.2 bearing located in the F119-PW-100 engine? |
Intermediate case |
|
|
How many hollow inlet struts are contained within the inlet fan case of the F119 engine? |
21 |
|
|
What stage of compressor air provides anti-icing to the inlet guide vanes of the F119-PW-100 engine? |
9th |
|
|
Where's the total temperature sensor located on a F119-PW-100 engine? |
Inside the fan inlet guide vane case at the 5:30 o'clock position |
|
|
Where is the N1 sensor mounted on the F119-PW-100 engine? |
Intermediate case |
|
|
How many stages are in the high pressure compressor (HPC) of a F119-PW-100 engine? |
Six |
|
|
On an F119-PW-100 engine, what function does the diffuser case serve other than housing to combustor? |
Reduces the velocity of compressor discharge air |
|
|
How many gas generator/core fuel nozzles are mounted on the diffuser case of the F119-PW-100 engine? |
24 |
|
|
What drives the inlet fan module (IFM) in the F119-PW-100 engine? |
Low-pressure turbine (LPT) module |
|
|
Which bearing is located in the low-pressure turbine (LPT) module of the F119-PW-100 engine? |
No. 5 bearing |
|
|
On the F119-PW-100 engine, what connects the LPT to the inlet fan module? |
Tie-bolts |
|
|
Where is the gearbox mounted on the F119-PW-100 engine and what drives it? |
6 o'clock position intermediate case; core module |
|
|
How many liners are contained in the transition duct of the nozzle module on a F119-PW-100 engine? |
20 |
|
|
Which actuators position nozzle flaps to establish trust vectoring angle on the F119-PW-100 engine? |
Divergent actuators |
|
|
What is the function of the fan bypass ducts on the F119-PW-100 engine? |
Directing fan bypass air into the turbine exhaust case and augmenter duct for cooling |
