CDC2 Aerospace Propulsion

  1. "An unbalanced force on a body produces or tends to produce an acceleration in the direction of the force and that the acceleration, if any, is directly proportional to the force and inversely proportional to the mass of the body." This statement is
    Newton's second law of motion.
  2. Which type of duct would decrease the velocity and increase the pressure of a gas as it passes through?
  3. "The Combination of decreased pressure above an airfoil, and the icreased pressure below the airfoil produces lift" is best described by
    Bernoulli's principle
  4. The tendency of an object at rest to remain at rest and the tendency of an object in motion to continue its motion in a straight line at the same speed is called
  5. Which section of a jet engine introdeces and burns fuel?
  6. Which section of a jet engine keeps the compressor rotating?
  7. Which method of producing thrust does a turbopro engine use?
    Accelerating a large mass of air by a small amount.
  8. Which type of horsepower is delivered to the propeller for useful work?
  9. The heat content per pund of kerosene is how many Btu's?
  10. To measure barometric pressure, you would use a
  11. What is the sea-level atmospheric pressure at "Standard Day" conditions?
    14.7 psi
  12. What effect does the divergent design of a diffuser have on air pressure?
    Increases pressure.
  13. Which engine component meters fuel for combustion?
    Fuel control.
  14. What directs the gases onto the first-stage turbine wheel blades in a jet engine?
    Turbine Stator
  15. 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)
  16. The three major sections of all jet engines are compressor, combustion, and
  17. Vane-type fuel pumps used in jet engines are similar to
    sliding-vane air compressors.
  18. The two froces that air is subjected to after it is drawn into the guide vanes of a centrifugal compressor are
    rotational and centrifugal
  19. a constructionla feature of the centrigual compressor is that the impeller
    is forged as a single unit.
  20. The forward end of the shaft on a centrifugal compressor is hollow in order to
    provide a passage for the main fuel supply.
  21. Stationary vanes positioned between rotor discs in a compressor are used to
    direct air and increase pressure.
  22. In a dual-spool compressor, rpm of the N2 compressor are determined by the
    fuel control.
  23. Which facet of engine design helps prevent igniter plug fouling?
    Directing air around the plug.
  24. The excess airflow that is not burned in the combustion section is used to
    cool the burner surfaces.
  25. Fuel that accumulates after a failed start is
    drained overboard by a drain system.
  26. The parts on a can-annular combustion section must be removed in a specific order because of the
    combustion chamber crossover tubes.
  27. What is the most common type of fuel nozzle system?
  28. Swirl-type fuel nozzles usually are used to provide what type of flame speed?
  29. Three types of turbine and vane assemblies used in jet engines are impulse, reaction, and
  30. What is placed in front of the rotating blades in an engine turbine section?
    Turbine nozzle vane assembly.
  31. Why is the "fir tree" method of attaching turbine blades (buckets) to the turbine rotor disc preferred?
    There is a significant temperature differential between the turbine rotor disc and the blades.
  32. The exhaust duct connects the turbine outlet and the
    jet nozzle.
  33. The purpose of the exhaust duct is to
    straighten exhaust gas-flow.
  34. The purpose of an augmentor (afterburner) in a jet engine is to
    augment basic engine thrust.
  35. How many different types of loads can be imposed on a jet engine bearing?
  36. When you handle jet engine bearings, you must change cotton gloves frequently because they
    get soaked in sweat.
  37. Before inspecting new jet engine bearings, you should
    remove the preservative coating.
  38. The bearing removal tools that are most commonly used include
    arbor presses and bearing pullers.
  39. Which type of defect appears on bearings as a result of bearing parts striking together?
  40. Which type of defect appears on bearings as a result of small particles of foreign material becoming lodged between the rollers?
  41. Excessive bearing wear can usually be detected by
    roughness of the metal.
  42. The recommended method of bheating inner reaces of bearings before installing them is
    hot-oil bath.
  43. Which component reduces the engine rotor speed to the rmp required for accessories?
    Reduction geartrain.
  44. On an F108 engine, the radial drive shaft connects the core engine to the
    accesory drive assembly.
  45. The major sections of a turboprop engine are the power unit, torquemeter assembly, and
    RGB assembly.
  46. On the T56 turboprop engine, how many stages of reduction are in the RGB's main reduction gear train?
  47. On the T56 turboprop engine, what is the overall reduction ratio of the RGB's main reduction gear train?
    13.54 to 1.
  48. On the T56 turboprop engine, there are mounting pads on the aft side of the accessory drive for the fuel control, fuel pump, and
    external scavenge oil pump
  49. On the T56 turboprop engine, which compressor section assembly diperses compressor discharge air and directs it to the combustion chambers?
  50. In the T56 engine, which RGB component rotates at the same speed as the power unit rotors?
    Pinion input gear.
  51. What is the total gear reduction ratio of the RGB?
    13.54 to 1.
  52. What is not a propeller brake position?
  53. The propeller brake is in which position when the aircraft is on the ground and the engine is stopped?
  54. Whcih valve in the propeller control assembly is actuated by the NTS actuator rod to increase propeller blade angle?
  55. Which components comprise the torquemeter assembly?
    Two concentric shafts, torquemeter housing, and torquemeter pickup.
  56. The amount of twisting deflection is determined by the
    reference shaft.
  57. The torquemeter exciter wheels are in phase when
    the rectangular teeth on the exciter wheels are alined at zero torque.
  58. The purpose of the T56 safety coupling is to
    disconnect the power section from the RGB assembly.
  59. For the safety coupling to disconnect the power unit from the RGB, torque must reach between
    -4200 and -7200 inch-pounds.
  60. The stationary (stator) vane blades on the T56 compressor are used to
    increase pressure.
  61. What type of bearings support the T56 compressor rotor at the front and rear?
    Front, roller; rear,ball
  62. Which T56 compressor component supports the compressor rear bearing labyrinth seal?
    Compressor diffuser.
  63. In the T56 engine, turbine rotor torque is transferred to the compressor rotor by the
    turbine coupling shaft.
  64. The purpose of the guide vane support is to direct airflow
    onto the turbine rotor blades.
  65. What are used to retain the turbine buckets in the first-stage wheel of the T56-A-15 engine?
    Cover plate seals.
  66. The AE2100D3 power plant major assemblies are the PGB, torqumeter assembly, power section, accessory drives, and the
    nacelle structure.
  67. On the AE2100D3, the forward engine mounts are located on the
    sides of the PGB.
  68. What type of compressor rotor assembly is used on the AE2100D3 engine?
    14 stage axial-flow.
  69. What AE2100D3 nacelle access door contains a fire access door?
    Lower right turbine acces door.
  70. The AE2100D3 engine mount is divided into how many major structures?
  71. The T700 engine consists of what four modules?
    Accessory, compressor, combustion, and power turbine section.
  72. What routes oil and fuel through the T700 engine AGB?
    Internal passages.
  73. What components mount on the front face of the AGB on the T700 engine?
    Alternator and fuel bood pump.
  74. The T700 gas generator turbine rotor drives the
    compressor and AGB.
  75. The T700 power turbine drive shaft assembly is made up of what two components?
    Drive shaft and torque sensor tube.
  76. Which F108 major engine module provides for mounting of the front of the engine to the airframe?
    Fan major module.
  77. Primary airflow in the F108 engine is through all of the following components except the
    accessory gearbox.
  78. the F108 engine can be broken down into how many individual modules?
  79. What percentage of the total engine thrust does the secodary airflow on the F108 engine produce?
  80. On the F108 engine, the purpose of the HPT nozzle assembly is to accelerate the energy from the combustion gases to drive the
    HPT rotor
  81. On the F108 engine, the LPT shaft assembly connects the fan shaft with the
    LPT rotor
  82. On the F108 engine, what connects the IGB to the TGB bevel gears?
    Radial drive shaft.
  83. On which module of an F100-PW-220 engine is the stator generator mounted?
  84. External flanges on the F100 engine are referred to by
    letter designations.
  85. On an F100-PW-220 engine, the No. 1 bearing assembly is located in the
    front compresor stator inlet shroud.
  86. When blending fourth stage compressor blades on an F100-PW-220 engine, a maximum of how many blends are allowed on any single edge?
  87. On an F100-PW-220 engine, the front compressor drive turbine shaft is connected to the front compressor rotor by
    the turbine drive shaft coupling.
  88. Which bearing is located in the fan drive turbine nodule on an F100-PW-220 engine?
    No. 5
  89. Major components of the F100-PW-220 engine augmentor duct and nozzle module are nozzle actuators, nozzle assembly, and
    combustion chamber liner and duct.
  90. On an F100-PW-220 engine, the gearbox module is driven by the rear compressor through
    a gearbox drive shaft.
  91. How many stages are in the inlet fan module of the F119-PW-100 engine?
  92. How many hollow struts/inlet guide vanes are contained in the inlet fan case of the F119 engine?
  93. Where is the Tt2 located on a F119-PW-100 engine?
    In the fan inlet guide vane case at the 5:30 position.
  94. Which is not a part of the core module of a F119-PW-100 engine?
    Low pressure compressor.
  95. Which bearing compartment is contained in the intermediate case of the F119-PW-100 engine?
    No. 2 and No. 3 bearing.
  96. On an F119-PW-100 engine, what function does the diffuser case serve other than housing the combuster?
    Reduces the veloocity of compressor discharge air.
  97. What drives the IFM in the F119-PW-100 enigne?
    LPT module
  98. which bearing is located in the LPT of the F119-PW-100 engine?
    No. 5 bearing
  99. On the F119-PW-100 engine, which of the following is not attached to the gearbox assembly?
    Augmentor fuel control.
  100. What is the nozzle module mounted to on the F119-PW-100 engine?
    Augmentor assembly.
Card Set
CDC2 Aerospace Propulsion
CDC Volume 2, 5 level