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82 Cards in this Set

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  • Back
8108. At what point in an axial flow turbojet engine will the highest gas pressure occur?
At the compressor outlet.
8109. One function of the nozzle diaphram in a turbine engine is to?
Direst the flow of gases to strike the turbine blades at the desired angle.
8110. What is the profile of a turbine engine compressor blade?
A cutout that reduces blade tip thickness.
8111. The fan rotational speed of a duel axial compressor forward fan engine is the same as the
Low pressure compressor.
8112. The abbreviation "P" with the subscript t7 used in turbine engine terminology means
The total pressure at station No. 7.
8113. The blending of blades and vanes in a turbine engine
Should be performed parallel to the length of the blade using smooth contours to minimize stress points.
8114. What turbine engine section provides the proper mixing of the fuel and air?
Combustion section.
8115. In a gas turbine engine, combustion occurs at a constant
8116. Which Statement is true regarding jet engines?
At the higher engine speeds, thrust increases rapidly with small increase in RPM.
8117. Some high volume turboprop and turbojet engines are equipped with two spool or split compressors. When these engines are operated at high altitudes, the
Low pressure rotor will increase in speed as the compressor load decreases in the lower density air.
8118. Turbine nozzel 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.
8119. Where is the highest gas pressure in a turbojet engine?
In the entrance of the burner section.
8120. An exhaust cone placed aft of the turbine in a jet engine will cause the pressure in the first part of the exhaust duct to
Increase and the velocity to decrease.
8121. What is the function of the stator vane assembly at the discharge end of a typical axial flow compressor?
To straighten airflow to eliminate turbulance.
8122. The turbine section of a jet engine
drives the compressor section.
8123. When starting turbine engine,
a hot start is indicated if the exhaust gas temperature exceeds specified limits.
8124. In the dual axial flow or twin spool compressor system, the first stage turbine drives the
N2 compressor.
8125. During inspection, turbine engine components exposed to high temperatures may only be marked with such materials as allowed by yhe manufacturer. These materials generally include
1. layout dye
2. commercial felt tip marker
8126. When starting a turbine engine, a hing start is indicated if the engine
Fails to reach idle RPM.
8127. What are the two basic elements of the turbine section in a turbine engine?
Stator and Rotor.
8128. The function of the exhaust cone assembly of a turbine engine is to
Straighten and collect the exhaust gases into a solid exhaust jet.
8129. What are the two functional elements in a centrifugal compressor?
Impeller and diffuser.
8130. What must be done after the fuel control unit has been replaced on an aircraft gas turbine engine?
Retrim the engine.
9131. If, during inspection at engine overhaul, ball or roller bearings are found to have magnetism but otherwise have no defects, they
Must be degaussed before use.
8132. A turbine engine compressor which contains vanes on both sides of the impeller is a
Dual entry centrifugal compressor.
8133. What is the first engine instrument indication of a successful start of a turbine engine?
A rise in the exhaust gas temperature.
8134. Some engine manufacturers of twin spool gas turbine engines identify turbine discharge pressure in their maintenance manual as
8135. Who establishes the recommended operating time between overhauls (TBO) of a turbine engine used in general aviation?
The engine manufacturer.
8136. The basic gas turbine engine is divided into two main sections: the cold section and the hot section.
1) The cold section includes the engine inlet, compressor, and turbine sections.
2) The hot section includes the combustor, diffuser, and the exhaust sections.
Regarding the above statements,
Neither No. 1 nor No. 2 is true.
1) Welding and straightening of turbine engine rotating airfoils does not require special equipment.
2) Welding and straightening of turbine engine rotating airfoils is commonly recommended by the manufacturer.
Regarding the above statements,
Neither No. 1 nor No. 2 is true.
8138. Turbine engine components exposed to high temperature generally may NOT be marked with
3. Wax or grease pencil.
5. Graphite lead pencil.
8139. Who establishes mandatory replacement times for critical components of turbine engines?
The engine manufacturer.
8140. Main bearing oil seals used with turbine engines are usually what type(s)?
Labyrinth and/or carbon rubbing.
8141. How does a duel axial flow compressor improve the efficiency of a turbojet engine?
Higher compression ratios can be obtained.
8142. Three types of turbine blades are
Impulse, reaction, and impulse reaction.
8143. Which statement is true regarding aircraft engine propulsion?
1) An engine driven propeller imparts a relatively large amount of acceleration to a large mass of air.
2) Turbojet and turbofan engines impart a relatively large amount of acceleration to a smaller mass of air.
3) In modern turboprop engines, nearly 50% of the exhaust gas energy is extracted by turbines to drive the propeller and the compressor with the rest providing exhaust thrust.
1 and 2
8144. AN advantage of the axial flow compressor is its
High peak efficiency.
8145. What is one purpose of the stator blades in the compressor section of a turbine engine?
Control the direction of the airflow.
8146. What is the purpose of the diffuser section in a turbine engine?
To increase pressure and reduce velocity.
8147. Where do stress rupture cracks usually appear on the turbine blades?
Across the leading or trailing edge at a right angle to the edge length.
8148. In which type of turbine engine combustion chamber is the case and liner removed and installed as one unit during routine maintenance?
8149. The diffusersection of a jet engine is located between
The compressor section and the burner section.
8150. When the leading edge of a first stage turbine blade is found to have stress rupture cracks, which of the following should be suspected?
Overtemperature condition.
8151. Turbine blades are generally more susceptible to operating damage than compressor blades because of
Exposure to high temperatures.
8152. Which of the following is the ultimate limiting factor of turbine engine operation?
Turbine inlet temperature.
8153. 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.
8154. Which of the following engine variables is the most critical during turbine engine operation?
Turbine inlet temperature.
8155. Reduced blade vibration and improved airflow characteristics in gas turbines are brought out by
Shrouded turbine rotor blades.
8156. Which turbine engine compressor offers the greatest advantages for both starting flexibility and improved high altitude performance?
Split spool, axial flow.
8157. Jet engine turbine blades removed for detailed inspection must be reinstalled in
The same slot.
8158. An advantage of the centrifugal flow compressor is its high
Pressure rise per stage.
8159. The highest heat to metal contact in a jet engine is in the
Turbine inlet guide vanes.
8160. Which two elements make up the axial flow compressor assembly?
Rotor and Stator
8161. The two types of centrifugal compressor impellers are
Single entry and double entry
8162. Between each row of rotating blades in a turbine engine compressor, there is a row of stationary blades which act to diffuse the air. These stationary blades are called
8163. Standard sea level pressure is
29.92" Hg.
8164. Using the atmospheric conditions, the standard sea level temperature is
59 ºF
8165. When aircraft turbine blades are subjected to excessive heat stress, what type of failures would you expect?
Stress rupture.
8166. In an axial flow compressor, one purpose of the stator vane at the discharge end of the compressor is to
Straighten the airflow and eliminate turbulance.
8167. Compressor field cleaning on turbine engines is performed primarily in order to
Prevent engine performance degradation, increased fuel costs, and damage or corrosion to gas path surfaces.
8168. Hot section inspections for many modern turbine engines are required
On a time or cycle basis.
8169. A purpose of the shrouds on the turbine blades of an axial flow engine is to
Reduce vibration.
8170. In a dual axial flow compessor, the first stage turbine drives
N2 compressor.
8171. What should be done initially if a turbine engine catches fire when starting?
Turn off the fuel and continue engine rotation with the starter.
8172. What is the proper starting sequences for a turbojet engine?
Starter, ignition, fuel.
8173. A weak fuel to air mixture along with normal airflow through a turbine engine may result in
A lean die-out.
8174. What is used in turbine engines to aid in stabilization of compressor airflow during low thrust engine operation?
Variable guide vanes and/or compessor blees valves.
8175. In a turbine engine with a dual spool compressor, the low speed compressor
Seeks its own best operating speed.
8176. 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.
8177. Hot spots on the tail cone of a turbine engine are possible indicators of a malfunctioning fuel nozzle or
A faulty combustion chamber.
8178. The stator vanes in an axial flow compressor
Convert velocity energy into pressure energy.
8179. The velocity of subsonic air as it flows through a convergent nozzle
8180. The velocity of supersonic air as it flows through a divergent nozzle
8181. The pressure of subsonic air as it flows through a convergent nozzle
8182. The pressure of supersonic air as it flows through a divergent nozzle
8183. Anti-icing of jet engine air inlets is commonly accomplished by
Engine bleed air ducted through the critical areas.
8184. Generally, when starting a turbine engine, the starter should be disengaged
After the engine has reached self-accelerating speed.
8185. What is the primary advantage of an axial flow compressor over a centrifugal compressor?
Greater pressure ratio.
8186. The purpose of a bleed valve, located in the beginning stages of the compressor, in an aircraft gas turbine engine is to
Vent some of the air overboard to prevent a compressor stall.
8187. What is meant by a double entry centrifugal compressor?
A compressor with vanes on both sides of the impeller.
8188. What is the major function of the turbine assembly in a turbojet?
Supplies the power to turn the compressor
8189. Stator blades in the compressorsection of an axial flow turbine engine
Decrease the air velocity and prevent swirling.