at what point in an axial flow turbojet engine will the highest gas press. occur? |
|
at the compressor outlet(burner inltet. |
| |
what does a nozzle diaphragm in a turbine engine do? |
|
directs the flow of gases to strike the turbine blades at the desired angle. |
| |
the fan rotational speed of a dual axial compressor forward fan engine is the same as the..? |
|
low pressure compressor. |
| |
the abbreviation Pt17 used in turbine engine term means..? |
|
the total pressure at station number 17. |
| |
how should the blending of blades and vanes in a turbine engine be performed? |
|
parallel to the length of the blades using smooth contours to minimize stress points. |
| |
what turbine engine section provides for proper mixing of the fuel and air? |
|
combustion section. |
| |
in a gas turbine engine, combustion occurs at a constant..? |
|
pressure. |
| |
what is the relationship between thrust and RPM in jet engines? |
|
at higher engine speeds, thrust increases rapidly with small increases in RPM. |
| |
some high volume turboprop and turbojet engines are equipped w/ two-spool or split compressors. what happens to these engines when operated at high altitudes? |
|
the low press. rotor will increase in speed as the compressor load decreases in the lower density air. |
| |
turbine nozzle diaphragms located on the upstream side of each turbine wheel, are used in the gas turbine engine to..? |
|
increase the velocity of the heated gases flowing past this point. |
| |
where is the ighest gas pressure in a turbojet engine? |
|
in the entrance of the burner section. |
| |
an exhaust cone placed aft of te turbine in a jet engine will cause the pressure in the first part of the exhaust duct to..? |
|
increase and the velocity to decrease. |
| |
what is the function of the stator vane assembly at the discharge end of a typical axial flow compressor? |
|
to straighten airflow to eliminate turbulence. |
| |
the turbine section of a jet engine drives the..? |
|
compressor section. |
| |
when starting a turbine engine a hot start is indicated..? |
|
if the exhaust gas temp. exceeds specified limits. |
| |
in the dual axial flow or twin spool compressor system, the first stage turbine drives the..? |
|
N2 compressor. |
| |
when starting a turbine engine, a hung start is indicated..? |
|
when the engine fails to reach idle RPM. |
| |
what are the two basic elemts of the turbine section in a turbine engine? |
|
stator and rotor. |
| |
the function of the exhaust cone assembly of a turbine engine is to..? |
|
straighten and collect the exhaust gases into a solid exhaust jet. |
| |
what are the two elements in a centrifugal compressor? |
|
impeller and diffuser. |
| |
what must be done after the fuel control unit has been replaced on an aircraft gas turbine engine? |
|
retrim te engine. |
| |
a turbine engine compressor which containes vanes on both sides of the impeller is a..? |
|
double entry centrifugal compressor. |
| |
what is the first engine instrument indication of a succesful start of a turbine engine? |
|
a rise in the exhaust gas temp. |
| |
who establises the recommended operating time between overhauls(TBO) of a turbine engine used in general aviation? |
|
the engine manufacturer. |
| |
turbine engine components exposed to high temp, generally may NOT be marked w/..? |
|
wax, grease, or graphite pencil. |
| |
who establishes mandatory replacement times for critical components of turbine engines? |
|
the engine manufacturer. |
| |
main bearing oil seals used with turbine engines are usually what type? |
|
labyrinth and/or carbon rubbing. |
| |
how does a dual axial flow compressor improve the efficiency of a turbojet engine? |
|
higher compression ratios can be obtained. |
| |
three types of turbine blades are..? |
|
impulse, reaction, and impulse-reaction. |
| |
an advantage of the axial flow compressor is its..? |
|
high peak efficiency. |
| |
what is one purpose of the stator blades in the compressor section of a turbine engine? |
|
controls the direction of the airflow. |
| |
what is the purpose of the diffuser section in a turbine engine? |
|
to increase pressure and reduce velocity. |
| |
where do stress rupture cracks usually appear on turbine blades? |
|
across the leading or trailing edge at a right angle to the edge length. |
| |
in which type of turbine enging combustion chamber is the case and liner removed and installed as one unit during maintenance? |
|
can. |
| |
the diffuser section of a jet engine is located between..? |
|
the compressor and the burner section. |
| |
when the leading edge of a first stage turbine blade is found to have stress rupture cracks, which of the following should be suspected? |
|
overtemp. conditions. |
| |
turbine blades are generally more susceptible to perating damage than compressor blades because of..? |
|
exposure to high temp. |
| |
which is the ultimate limiting factor of turbine engine operation? |
|
turbine inlet temp (TIT). |
| |
the recurrent ingestion of dust or other fine airborne particulates into a turbine engine can result in..? |
|
erosion damage to the compressor and turbine sections. |
| |
whic of the following engine variables is the most critical during turbine engine operation? |
|
TIT. |
| |
reduced blade vibration and improved airflow characteristics in gas turbines are brought about by..? |
|
shrouded turbine rotor blades. |
| |
which turbine engine compressor offers the greatest advantages for both starting flexibility and improved high altitude performance? |
|
split spool, axial flow. |
| |
an advantage of the centrifugal flow compressor is its high..? |
|
pressure rise per stage. |
| |
the highest heat to metal contact in a jet engine is the..? |
|
turbine inlet guide vanes. |
| |
which two elements make up the axial flow compressor assembly? |
|
rotor and stator. |
| |
the two types of centrifugal compressor impellers are..? |
|
single entry and double entry. |
| |
between each row of rotating blades in a turbine engine compressor, there is a row of stationary blades which act to diffuse the air. they are called..? |
|
stators. |
| |
when turbine blades are subjected to excessive heat stress, what type of failures would you expect? |
|
stress rupture. |
| |
in an axial flow compressor, one purpose of the stator vanes is to..? |
|
straighten the airflow and eliminate turbulence. |
| |
the purpose of the shrouds on the turbine blades of an axial flow engine is to..? |
|
reduce vibration. |
| |
in a dual axial flow compressor, the first stage turbine drives..? |
|
N2 compressor. |
| |
what should be done initially if a turbine engine catches fire when starting? |
|
turn off the fuel and continue engine roation w/ the starter. |
| |
what is the proper starting sequence for a turbojet engine? |
|
starter, ignition, fuel. |
| |
a weak fuel to air mixture along with normal airflow through a turbine engine may result in..? |
|
a lean die out. |
| |
what is used in turbine engines to aid in stabilization of compressor airflow during low thrust engine operation? |
|
variable guide vanes and compressor bleed valves. |
| |
in a turbine engine with a dual spool compressor, the low speed compressor..? |
|
seeks its own best operating speed. |
| |
what is the function of the inlet guide vane assembly on an axial flow compressor? |
|
directs the air into the first stage rotor blades at the proper angle. |
| |
the stator vanes in an axial flow compressor..? |
|
convert velocity energy into pressure energy. |
| |
anti icing of jet engine air inlet is commonly accomplished by..? |
|
engine bleed air ducts. |
| |
when starting a turbine engine, the starter should be disengaged..? |
|
after the engine has reached self accelerating speed |
| |
what is the primary advantage of an axial flow compressor over a centrifugal one? |
|
greater pressure ratio. |
| |
the purpose of a bleed air valve in an aircraft gas turbine engine is to.. |
|
vent some of the air overboard. |
| |
what is meant by a double entry centrifugal compressor? |
|
a compressor with vanes on both sides of the impeller. |
| |
whats te function of the turbine assembly in a turbojet engine? |
|
supplies power to turn the compressor. |
| |
stator blades in the compressor section of an axial flow turbine engine..? |
|
decreases the air velocity and prevent swirling. |
| |
a gas turbine engine comprises which three main sections? |
|
turbine, compressor, combustion. |
| |
what type of turbine blade is most commonly used in aircraft jet engines? |
|
impulse reation. |
| |
what is the primary factor which controls the pressure ratio of an axial flow compressor? |
|
the number of stages in the compressor. |
| |
the non rotating axial flow compressor airfoils in an aircraft gas turbine engine are called.. |
|
stator vanes. |
| |
the air passing trough the combustion chamber of a turbine engine is used to..? |
|
support combustion and to cool the engine. |
| |
the stators in the turbine section of a gas turbine engine..? |
|
increase the velocity of the gas flow. |
| |
the compressor stators in a gas turbine engine act as diffusers to..? |
|
decrease the velocity of the gas flow/ |
| |
what is the possible cause when a turbine engine indicates no change in power setting parameters, but oil temperature is high? |
|
engine main bearing distress. |
| |
a turbine engine hot section is susptible to what kind of damage? |
|
cracking. |
| |
what influences the operation of an automatic fuel control unit on a turbojet engine? |
|
burner pressure. |
| |
the compression ratio of an axial flow compressor is a function of the..? |
|
number of compressor stages. |
| |
why do some turbine engines have more than one turbine wheel? |
|
to extract more power from the exhaust gases. |
| |
the exhaust section of a turbine engine is designed to..? |
|
impart a high exit velocity to the exhaust gases. |
| |
which of the following types of combustion sections are used in aircraft turbine engines? |
|
multiple-can, annular, and can-annular. |
| |
a cool off period prior to shutdown of a turbine engine is accomplished in order to..? |
|
allow the turbine wheel to cool before the case contracts around it. |
| |
what term is used to describe permanent deformation of the turbine blades of a turbojet engine? |
|
creep. |
| |
what is the purpose of the dump valve used on aircraft gas turbine engine? |
|
dumps the fuel from the fuel manifold when the engine is shut down. |
| |
at what stage ina turbine engine are gas pressures the greatest? |
|
compressor outlet. |
| |
in waht section of a turbojet engine is the jet nozzle located? |
|
exhaust. |
| |
compressor stall is caused by..? |
|
a high angle of attack airflow through the first stages of compression. |
| |
hotspots are possible indicators of..? |
|
malfunctioning fuel nozzles. |
| |