問題一覧
1
The turbine of a turboprop engine extracts up to __________ percent of the engines total power output to drive the propeller.
85
2
What two factors determine the angle of attack of a compressor blade? a. ___________ b. ___________
inlet air velocity, compressor rpm
3
Afterburning can produce as much as a 100% increase in thrust, with fuel flows increasing by __________ to __________ times.
3, 5
4
The section of a turbine engine directly behind the compressor is known as the __________.
diffuser
5
Turbine blades may be open or _________ at their tips.
shrouded
6
When turbine blades are installed on a turbine disk, the unit is known as a turbine _________.
wheel
7
Turbofan engines __________ (often or seldom) require noise suppression.
seldom
8
What are the two functions of the turbine nozzle? a. _________ b. _________
convert some of the exhaust gases pressure energy into velocity energy, direct the flow of exhuast gasses to strike the turbine rotor at the correct
9
The jet nozzle imparts a final __________(increase or decrease) in the velocity to the gases.
increase
10
High temperature, high pressure air taken from the compressor for various purposes is known as __________air.
hybrid
11
The three types of combustion chambers that may be found in turbine engines are: a. __________ b. __________ c. __________
multi can, can annular, annular or basket type
12
The three classifications used to describe turbine blades are: a. _________ b. _________ c. _________
impulse, reaction, impulse-reaction
13
To take advantage of the good points of both the centrifugal flow and axial flow compressors, some engines may use a __________ compressor.
12
14
The primary air, or the air that enters into the combustion process, amounts to about _________ percent of the total air that flows through a gas turbine engine.
25
15
As primary air flow enters a combustor, it passes through a set of __________ __________, which give the air a radial motion.
swirl vanes
16
Annular combustors which reverse the direction of the airflow are __________ combustors.
reverse flow
17
On a multi-spool engine, the low-pressure compressor (N1) will ___________ (speed up or slow down) with an increase in altitude.
speed up
18
The special set of vanes located at the discharge end of the compressor form the outlet vane assembly. The purpose of this assembly is to help straighten the airflow and eliminate any __________.
swirling
19
The pressure in the __________ section of a gas turbine engine is the highest of any section in the engine.
diffuser
20
Gas turbine engine rotors are usually supported by either __________ or __________ (what type) bearings.
ball, roller
21
The two types of flameout that can occur in a gas turbine engine are refered to as: a. _________ b. _________
lean die out, rich blow out
22
Approximately _________ (what percentage) of the total pressure energy from the exhaust gasses is absorbed by the turbine section is used to turn the compressor and drive the accessories.
60-80
23
Compressor stalls may cause the air flowing in the compressor to __________, or stagnate. In some cases the air may reverse direction.
slow down
24
The most common method of attaching turbine blades to the disk is the _________ _________method.
fir tree
25
Design factors which contribute to the prevention of compressor stalls include: a. __________ b. __________ c. __________
variable inlet guide vanes, bleed valves, variable stator vanes
26
Some current applications of bleed air are: a. __________ b. __________ c. __________ d. __________ e. __________
cabin pressurization, heating, cooling, de-icing and anti-icing, pneumatic engine starting