Jet Engine Theory And Design

39 Questions | Total Attempts: 52

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Jet Engine Quizzes & Trivia

Questions and Answers
  • 1. 
    WHICH OF THE FOLLOWING TYPES OF ENGINE DOES NOT USE ATMOSPHERIC AIR FOR COMBUSTION
    • A. 

      ROCKET

    • B. 

      PULSEJET

    • C. 

      RAMJET

  • 2. 
    WHAT EFFECT DOES A DIVERGENT DUCT HAVE ON AIRFLOW
    • A. 

      AN INCREASE IN PRESSURE AND DECREASE IN VELOCITY

    • B. 

      AN INCREASE IN PRESSURE AND INCREASE IN VELOCITY

    • C. 

      A DECRASE IN PRESSURE

  • 3. 
    DEFINITION OF FORCE ?
    • A. 

      ACTION ON A BODY THAT CHANGES EITHER ITS MASS OR ITS WEIGHT

    • B. 

      THE TOTAL AMOUNT OF WORK REQUIERED TO MOVE AN OBJET

    • C. 

      ACTION ON A BODY THAT CHANGES ITS STATE OF MOTION

  • 4. 
    MAS IS THE QUANTITY OF MATTER, WEIGHT IS PULL OF GRAVITY ON THAT QUANTITY OF MATTER
    • A. 

      True

    • B. 

      False

  • 5. 
    RATE OF DOING WORK
  • 6. 
    ENGLISH MEASUREMENT FOR MECHANICAL POWER
  • 7. 
    MEASURAMENT OF FORCE TIMES DISTANCE
  • 8. 
    CAPACITY FOR DOING WORK
  • 9. 
    A STANDER DAY AT SEA LEVEL IS INDICATE BY
    • A. 

      30.95 INCHES OF MERCURY, 0.00% HUMIDITY, AND A TEMPERATURE OF 59.0 DEGREE F

    • B. 

      30.95, 25.-65

    • C. 

      29.92 INCHES OF MERCURY, 0.00 % HUMIDITY AND A TEMPERATUR OF 59.0 D F

  • 10. 
    WHEN TEMP INCREASE IT THE SLUG OF AIR THE MOLECULES MOVE FASTER, RUN INTO EACH OTHER WITH MORE IMPACT AND MOVE FUTHER APART DECREASING AIR DENSITY
    • A. 

      True

    • B. 

      False

  • 11. 
    WHAT IS THE RAM EFFECT
    • A. 

      MORE AIR ARRIVING THE ENGINE

    • B. 

      MORE AIR ARRIVING THE ENGINE INTAKE THAN THE ENGIEN CAN INGEST

    • C. 

      THE AIRSPEED AT WICH RAM PRESSURE DECREASE EQUAL FRICTION

  • 12. 
    WORK
    • A. 

      NEWTONS 1ERS LAW

    • B. 

      NEWTONS 2D LAW

    • C. 

      NEWTONS 3ER LAW

  • 13. 
    ACTION/ REACTION
    • A. 

      NEWTONS 1ERS LAW

    • B. 

      NEWTONS 2D LAW

    • C. 

      NEWTONS 3RS LAW

  • 14. 
    ACELL/ ERATION
    • A. 

      NEWTONS 1ERS LAW

    • B. 

      NEWTONS 2D LAW

    • C. 

      NEWTONS 3ERS LAW

  • 15. 
    WHAT ARE THE THREE PARTS OF MIL-STD-879 ENGINE DESIGNATION SYSTEM
    • A. 

      TYPE INDICATOR , MANUFACTOR SYMBOL, AND MODEL INDICATOR

    • B. 

      TYPE INDICATOR , MANUFACTOR SYMBOL, SERVICE INDENTIFIFIER

    • C. 

      TYPE INDICATOR , MANUFACTOR SYMBOL, AND TYPE INDICATOR

  • 16. 
    WHICH OF THE FOLLOWING IS A REASON FOR PROPER AIR ENTRANCE DUCT DESIGN
    • A. 

      TO INCREASE RAM RECOVERY WHILE REDUCING PRESSURE DROPS

    • B. 

      TO REDUCE THE RATIO OF COMPRESSOR DISCHARGE PRESSURE TO DUCT INLET PRESSURE

  • 17. 
    A SINGLE AIR ENTRANCE IS MORE ADVANTAGEOUS THAN DUAL AIR ENTRANCE SYSTEM FOR WICH OF THE FOLLOWING  REASONS
    • A. 

      IT EASIER FOR AIRCRAFT TO MANUFACTURE

    • B. 

      IT OBTAINS MAXIMUN RAM PRESSURE

  • 18. 
    DURING SUPERSONIC FLIGHT WHAT MAJOR AIRCRAFT COMPONENT CAN NOT WITHTAND SUPERSONIC VELOCITY AIRFLOW
    • A. 

      THE TAIL

    • B. 

      THE ENGINE

    • C. 

      THE INTAKE

  • 19. 
    IN AN AXIAL-FLOW ENGINE, BY WHAT MEANS IS HIGH-VELOCITY , LOW PRESSURE AIR CONVERTED TO LOW-VELOCITY, HIGH PRESSURE AIR
    • A. 

      ACTION OF SINGLE INTAKE DIFFUSER

    • B. 

      ACTION OF STATOR BLADES AT EACH STAGE OF COMPRESSION

  • 20. 
    WHAT IS THE MOST SERIOUS DISADVANTAGE OF AXIAL-FLOW COMPRESSOR
    • A. 

      LOW COMPRESSION RATIO

    • B. 

      HIGH STARTING POWER NEEDS

    • C. 

      HIGH TENDENCY TO STALL

  • 21. 
    WITCH REFERENCE TO AXIAL-FLOW ENGINE THE ANGLE OF ATTACK IS THE ANGLE AT WICH THE AIRFLOW
    • A. 

      STRIKES THE ROTOR BLADES

    • B. 

      BECOMES TURBULANT OVER THE UPPER FOIL SURFACE

  • 22. 
    WHAT THREE ENGINE OPERATING PARAMETER CAUSE THE AIRFLOW  ANGLE OF ATTACT TO VARY
    • A. 

      ENGINE RPM, HUMIDITY AND COMPRESSOR DISCHARGE PRESSURE

    • B. 

      ENGINE, RPM, COMPRESSOR-INLER TEMP AND COMPRESSOR DISCHARGE PRESSURE

  • 23. 
    ENGINE CHOKING REFER TO WHICH OF THE FOLLOWING TERMS
    • A. 

      HIGH COMPRESSOR INLET AIR TEMP

    • B. 

      STALL DUE TO AN EXCESS VOLUME OF AIR IN THE REAR OF COMPRESSOR

  • 24. 
    WHICH OF THE FOLLOWING IS NOT CONSIDER BY ENGINE MANUFACTURES AS CORRECTIVE ACTION FOR A FRONT END, LOW SPEED. HIGH TEMP STALL
    • A. 

      INSTALLING A BLEED VALVE IN THE MIDDLE OF REAR PORTION OF THE COMPRESSOR SECTION

    • B. 

      INCREASING COMPRESSOR LOAD THROUGH THE USE OF VARIABLE-AREA EXHAUST NOZZLES

  • 25. 
    GIUDES VANE CHANGE THE DIRECTION OF THE AIR ENTERING AND LEAVING THE COMPRESSOR IN WHAT MANER
    • A. 

      BY SWIRLING IT AS IT ENTERS AND LEAVES

    • B. 

      BY SWIRLING IT AS IT ENTERS AND STRAIGHTENING IT OUT AS IT LEAVES

  • 26. 
    BLEED AIR FOR UNLOADING THE COMPRESSOR DURING STARTING , COCKPIT PRESSURIZATION AND HEATING, ENGINE ANTI-ICING, FUEL TANK , PRESSURIZATION AND VARIOUS OTHER PURPOSES IS TAPPED FROM WHICH OF THE FOLLOWING SOURCE
    • A. 

      THE COMPRESSOR FOR LOW PRESSURE AND TEM NEEDS ONLY

    • B. 

      DIFFERENT STAGES OF THE COMPRESSOR DEPENDING ON THE PRESSURE AND TEMP NEEDED

  • 27. 
    WHAT ARE TWO COMMON FORM OF BLADE ROOTS
    • A. 

      GRUB AND BULB

    • B. 

      FIR-TREE AND BULB

  • 28. 
    WHAT IS THE PROFILE OF COMPRESSOR BLADE
    • A. 

      THE LENGTH OF THE BLADE

    • B. 

      A CUTOUT THAT REDUCES BLADE THICKNESS

  • 29. 
    WHAT IS THE PURPOSE OF COMPRESSOR BLADE PROFILES
    • A. 

      TO ALLOW LESS AIRFLOW TO ESCAPE AROUND THE EDGE OF THE TIP

    • B. 

      TO ALLOW THE COMPRESSOR BLADE TIPS TO RUB WITHOUT CAUSING SERIOUS DAMAGE

  • 30. 
    WHICH OF THE FOLLOWING IS A DISADVANTAGE OF THE AXIA-FLOW COMPRESSOR
    • A. 

      HIGH STARTING POWER NEEDS

    • B. 

      LOU PEAK EFFICIENCIES

  • 31. 
    WHICH OF THE FOLLOWING TYPES OF COMPRESSOR PROVIDES GREATER STARTING FLEXIBILITY AND IMPROVED HIGH-ALTITUDE PERFORMANCE
    • A. 

      SPLIT-SPOOL. AXIAL-FLOW

    • B. 

      SOLID-SPOOL, AXIAL-FLOW

  • 32. 
    WHAT IS THE PRIMARY FUNCTION OF THE COMBUSTION SECTION
    • A. 

      TO PROVIDE IGNITION

    • B. 

      TO BURN THE FUEL-AIR MIXTURE

  • 33. 
    APPROXIMATELY WHAT % OF AIR ENTERING THE COMBUSTION CHAMBER IS MIXED WITH FUEL FOR COMBUSTION
    • A. 

      40 %

    • B. 

      35%

    • C. 

      25%

  • 34. 
    APPROXIMATELY WHAT % OF AIR ENTERING THE COMBUSTION CHAMBER SERVES AS FLAME CONTROL
    • A. 

      80

    • B. 

      75

    • C. 

      65

  • 35. 
    DURING THE COMBUSTION PROCESS, THE EMISSION LEVEL OF WHITCH OF THE FOLLOWING POLLUTANT INCREASES AS TEMP INCREASES
    • A. 

      CARBON MONOXID

    • B. 

      CARBON DIOXIDE

    • C. 

      NITRIC OXIDE

  • 36. 
    WHICH OF THE FOLLOWING IS NOT A BASIC ELEMENT OR SYSTEM OF COMBUSTION CHAMBER
    • A. 

      CASING

    • B. 

      INNER LINER

    • C. 

      AIR POLLUTION EMISION REDUCTION

  • 37. 
    WHICH OF THE FOLLOWING IS NOT A BASIC TYPE OF COMBUSTION CHAMBER
    • A. 

      ANNULAR

    • B. 

      CAN-ANNULAR

    • C. 

      BASKET-CHAMBER

  • 38. 
    PRESENTLY, WHAT TOTAL NUMBER OF COMBUSTION LINER ARE USED IN JET ENGINE USING CAN-TYPE COMBUSTION CHAMBER
    • A. 

      2 OR 4

    • B. 

      6 OR 7

    • C. 

      8 OR 10

  • 39. 
    WHICH OF THE FOLLOWING TYPES OF FUEL NOZZLES ARE USED IN JET ENGINES
    • A. 

      INTERNAL AND EXTERNAL

    • B. 

      SIMPLEX AND DUPLEX