Powerplant

Front 1

8108. At what point in an axial flow turbojet engine will the highest gas pressure occur?

Back 1

At the compressor outlet.

Front 2

8109. One function of the nozzle diaphram in a turbine engine is to?

Back 2

Direst the flow of gases to strike the turbine blades at the desired angle.

Front 3

8110. What is the profile of a turbine engine compressor blade?

Back 3

A cutout that reduces blade tip thickness.

Front 4

8111. The fan rotational speed of a duel axial compressor forward fan engine is the same as the

Back 4

Low pressure compressor.

Front 5

8112. The abbreviation "P" with the subscript t7 used in turbine engine terminology means

Back 5

The total pressure at station No. 7.

Front 6

8113. The blending of blades and vanes in a turbine engine

Back 6

Should be performed parallel to the length of the blade using smooth contours to minimize stress points.

Front 7

8114. What turbine engine section provides the proper mixing of the fuel and air?

Back 7

Combustion section.

Front 8

8115. In a gas turbine engine, combustion occurs at a constant

Back 8

Pressure.

Front 9

8116. Which Statement is true regarding jet engines?

Back 9

At the higher engine speeds, thrust increases rapidly with small increase in RPM.

Front 10

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

Back 10

Low pressure rotor will increase in speed as the compressor load decreases in the lower density air.

Front 11

8118. Turbine nozzel diaphragms located on the upstream side of each turbine wheel, are used in the gas turbine engine to

Back 11

Increase the velocity of the heated gases flowing past this point.

Front 12

8119. Where is the highest gas pressure in a turbojet engine?

Back 12

In the entrance of the burner section.

Front 13

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

Back 13

Increase and the velocity to decrease.

Front 14

8121. What is the function of the stator vane assembly at the discharge end of a typical axial flow compressor?

Back 14

To straighten airflow to eliminate turbulance.

Front 15

8122. The turbine section of a jet engine

Back 15

drives the compressor section.

Front 16

8123. When starting turbine engine,

Back 16

a hot start is indicated if the exhaust gas temperature exceeds specified limits.

Front 17

8124. In the dual axial flow or twin spool compressor system, the first stage turbine drives the

Back 17

N2 compressor.

Front 18

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

Back 18

1. layout dye
2. commercial felt tip marker
4.chalk

Front 19

8126. When starting a turbine engine, a hing start is indicated if the engine

Back 19

Fails to reach idle RPM.

Front 20

8127. What are the two basic elements of the turbine section in a turbine engine?

Back 20

Stator and Rotor.

Front 21

8128. The function of the exhaust cone assembly of a turbine engine is to

Back 21

Straighten and collect the exhaust gases into a solid exhaust jet.

Front 22

8129. What are the two functional elements in a centrifugal compressor?

Back 22

Impeller and diffuser.

Front 23

8130. What must be done after the fuel control unit has been replaced on an aircraft gas turbine engine?

Back 23

Retrim the engine.

Front 24

9131. If, during inspection at engine overhaul, ball or roller bearings are found to have magnetism but otherwise have no defects, they

Back 24

Must be degaussed before use.

Front 25

8132. A turbine engine compressor which contains vanes on both sides of the impeller is a

Back 25

Dual entry centrifugal compressor.

Front 26

8133. What is the first engine instrument indication of a successful start of a turbine engine?

Back 26

A rise in the exhaust gas temperature.

Front 27

8134. Some engine manufacturers of twin spool gas turbine engines identify turbine discharge pressure in their maintenance manual as

Back 27

Pt7

Front 28

8135. Who establishes the recommended operating time between overhauls (TBO) of a turbine engine used in general aviation?

Back 28

The engine manufacturer.

Front 29

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,

Back 29

Neither No. 1 nor No. 2 is true.

Front 30

8137.
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,

Back 30

Neither No. 1 nor No. 2 is true.

Front 31

8138. Turbine engine components exposed to high temperature generally may NOT be marked with

Back 31

3. Wax or grease pencil.
5. Graphite lead pencil.

Front 32

8139. Who establishes mandatory replacement times for critical components of turbine engines?

Back 32

The engine manufacturer.

Front 33

8140. Main bearing oil seals used with turbine engines are usually what type(s)?

Back 33

Labyrinth and/or carbon rubbing.

Front 34

8141. How does a duel axial flow compressor improve the efficiency of a turbojet engine?

Back 34

Higher compression ratios can be obtained.

Front 35

8142. Three types of turbine blades are

Back 35

Impulse, reaction, and impulse reaction.

Front 36

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.

Back 36

1 and 2

Front 37

8144. AN advantage of the axial flow compressor is its

Back 37

High peak efficiency.

Front 38

8145. What is one purpose of the stator blades in the compressor section of a turbine engine?

Back 38

Control the direction of the airflow.

Front 39

8146. What is the purpose of the diffuser section in a turbine engine?

Back 39

To increase pressure and reduce velocity.

Front 40

8147. Where do stress rupture cracks usually appear on the turbine blades?

Back 40

Across the leading or trailing edge at a right angle to the edge length.

Front 41

8148. In which type of turbine engine combustion chamber is the case and liner removed and installed as one unit during routine maintenance?

Back 41

Can.

Front 42

8149. The diffusersection of a jet engine is located between

Back 42

The compressor section and the burner section.

Front 43

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?

Back 43

Overtemperature condition.

Front 44

8151. Turbine blades are generally more susceptible to operating damage than compressor blades because of

Back 44

Exposure to high temperatures.

Front 45

8152. Which of the following is the ultimate limiting factor of turbine engine operation?

Back 45

Turbine inlet temperature.

Front 46

8153. The recurrent ingestion of dust or other fine airborne particulates into a turbine engine can result in

Back 46

Erosion damage to the compressor and turbine sections.

Front 47

8154. Which of the following engine variables is the most critical during turbine engine operation?

Back 47

Turbine inlet temperature.

Front 48

8155. Reduced blade vibration and improved airflow characteristics in gas turbines are brought out by

Back 48

Shrouded turbine rotor blades.

Front 49

8156. Which turbine engine compressor offers the greatest advantages for both starting flexibility and improved high altitude performance?

Back 49

Split spool, axial flow.

Front 50

8157. Jet engine turbine blades removed for detailed inspection must be reinstalled in

Back 50

The same slot.

Front 51

8158. An advantage of the centrifugal flow compressor is its high

Back 51

Pressure rise per stage.

Front 52

8159. The highest heat to metal contact in a jet engine is in the

Back 52

Turbine inlet guide vanes.

Front 53

8160. Which two elements make up the axial flow compressor assembly?

Back 53

Rotor and Stator

Front 54

8161. The two types of centrifugal compressor impellers are

Back 54

Single entry and double entry

Front 55

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

Back 55

Stators

Front 56

8163. Standard sea level pressure is

Back 56

29.92" Hg.

Front 57

8164. Using the atmospheric conditions, the standard sea level temperature is

Back 57

59 ºF

Front 58

8165. When aircraft turbine blades are subjected to excessive heat stress, what type of failures would you expect?

Back 58

Stress rupture.

Front 59

8166. In an axial flow compressor, one purpose of the stator vane at the discharge end of the compressor is to

Back 59

Straighten the airflow and eliminate turbulance.

Front 60

8167. Compressor field cleaning on turbine engines is performed primarily in order to

Back 60

Prevent engine performance degradation, increased fuel costs, and damage or corrosion to gas path surfaces.

Front 61

8168. Hot section inspections for many modern turbine engines are required

Back 61

On a time or cycle basis.

Front 62

8169. A purpose of the shrouds on the turbine blades of an axial flow engine is to

Back 62

Reduce vibration.

Front 63

8170. In a dual axial flow compessor, the first stage turbine drives

Back 63

N2 compressor.

Front 64

8171. What should be done initially if a turbine engine catches fire when starting?

Back 64

Turn off the fuel and continue engine rotation with the starter.

Front 65

8172. What is the proper starting sequences for a turbojet engine?

Back 65

Starter, ignition, fuel.

Front 66

8173. A weak fuel to air mixture along with normal airflow through a turbine engine may result in

Back 66

A lean die-out.

Front 67

8174. What is used in turbine engines to aid in stabilization of compressor airflow during low thrust engine operation?

Back 67

Variable guide vanes and/or compessor blees valves.

Front 68

8175. In a turbine engine with a dual spool compressor, the low speed compressor

Back 68

Seeks its own best operating speed.

Front 69

8176. What is the function of the inlet guide vane assembly on an axial flow compressor?

Back 69

Directs the air into the first stage rotor blades at the proper angle.

Front 70

8177. Hot spots on the tail cone of a turbine engine are possible indicators of a malfunctioning fuel nozzle or

Back 70

A faulty combustion chamber.

Front 71

8178. The stator vanes in an axial flow compressor

Back 71

Convert velocity energy into pressure energy.

Front 72

8179. The velocity of subsonic air as it flows through a convergent nozzle

Back 72

Increases.

Front 73

8180. The velocity of supersonic air as it flows through a divergent nozzle

Back 73

Increases.

Front 74

8181. The pressure of subsonic air as it flows through a convergent nozzle

Back 74

Decreases.

Front 75

8182. The pressure of supersonic air as it flows through a divergent nozzle

Back 75

Decreases.

Front 76

8183. Anti-icing of jet engine air inlets is commonly accomplished by

Back 76

Engine bleed air ducted through the critical areas.

Front 77

8184. Generally, when starting a turbine engine, the starter should be disengaged

Back 77

After the engine has reached self-accelerating speed.

Front 78

8185. What is the primary advantage of an axial flow compressor over a centrifugal compressor?

Back 78

Greater pressure ratio.

Front 79

8186. The purpose of a bleed valve, located in the beginning stages of the compressor, in an aircraft gas turbine engine is to

Back 79

Vent some of the air overboard to prevent a compressor stall.

Front 80

8187. What is meant by a double entry centrifugal compressor?

Back 80

A compressor with vanes on both sides of the impeller.

Front 81

8188. What is the major function of the turbine assembly in a turbojet?

Back 81

Supplies the power to turn the compressor

Front 82

8189. Stator blades in the compressorsection of an axial flow turbine engine

Back 82

Decrease the air velocity and prevent swirling.