13 Gas Turbines Introduction – LMS

📄 Detailed Notes ⚡ Cheat Sheet

Results

📄 Notes ⚡ Cheat Sheet

Q1. Both gas turbine and piston engines use a cycle made up of induction,compression, combustion and exhaust phases. Which of these statements about a gas turbine are correct or incorrect?I. The process in a gas turbine engine is continuous.II. Theoretically the combustion occurs at constant pressure.

I is incorrect, II is incorrect.

I is incorrect, II is correct.

I is correct, II is correct.

I is correct, II is incorrect.

Q2. Both gas turbine and piston engines use a cycle made up of induction, compression, combustion and exhaust phases. Which of these statements about a piston engine are correct or incorrect? I. The process in a piston engine is intermittent. II. Theoretically the combustion occurs at constant volume.

I is incorrect, II is correct.

I is correct, II is incorrect.

I is correct, II is correct.

I is incorrect, II is incorrect.

Q3. Both gas turbine and piston engines use a cycle made up of induction, compression, combustion and exhaust phases. Which of these statements about a gas turbine are correct or incorrect? I. The process in a gas turbine engine is intermittent. II. Theoretically, the combustion occurs at constant volume.

I is correct, II is incorrect.

I is incorrect, II is correct.

I is incorrect, II is incorrect.

I is correct, II is correct.

Q4. Both gas turbine and piston engines use a cycle made up of induction, compression, combustion and exhaust phases. Which of these statements about a piston engine are correct or incorrect?I. The process in a piston engine is continuous.II. Theoretically the combustion occurs at constant pressure.

I is incorrect, II is correct.

I is correct, II is correct.

I is incorrect, II is incorrect.

I is correct, II is incorrect.

Q5. Both gas turbine and piston engines use a cycle made up of induction, compression, combustion and exhaust phases. Which of these statements about a piston engine are correct or incorrect?I. The process in a piston engine is intermittent.II. Theoretically the combustion occurs at constant pressure.

I is incorrect, II is incorrect

I is correct, II is incorrect

I is correct, II is correct

I is incorrect, II is correct

Q6. Both gas turbine and piston engines use a cycle made up of induction, compression, combustion and exhaust phases. Which of these statements about a gas turbine are correct or incorrect?I. The process in a gas turbine engine is continuous.II. Theoretically the combustion occurs at constant volume.

I is incorrect, II is incorrect.

I is incorrect, II is correct.

I is correct, II is correct.

I is correct, II is incorrect.

Q7. In the airflow through a single-spool axial flow turbo-jet engine, the axial velocity of the air is greatest:

as it leaves the compressor

on exit from the propelling nozzle

within the combustion chamber

as it leaves the turbine

Q8. When the combustion gases pass through a turbine the:

axial velocity of the flow decreases

pressure rises

pressure drops

temperature increases

Q9. In the airflow through a single-spool axial flow turbojet engine, the axial velocity of the air is greatest:

Within the combustion chamber

As it leaves the turbine

On exiting the propelling nozzle

As it leaves the compressor

Q10. The principle of aeroplane propulsion is to generate a propelling force by:

accelerating air or gas in order to obtain a reaction force.

generating a high velocity jet pushing against the outside air.

heating up air in order to obtain a reaction force.

pressurising air or gas in order to obtain a reaction force.

Q11. In a single spool gas turbine engine, the compressor rpm is:

the same as turbine rpm

greater than turbine rpm

less than turbine rpm

independent of turbine rpm

Q12. In a turbo-jet, the purpose of the turbine is to …

compress the air in order to provide a better charge of the combustion chamber

drive devices like pumps, regulator, generator

clear the burnt gases, the expansion of which provide the thrust

drive the compressor by using part of the energy from the exhaust gases

Q13. Jet engine total efficiency indicates the efficiency at which:

the increase of jet kinetic energy is transformed into propulsive energy.

potential energy in the jet is transformed into propulsive energy.

chemical power in the fuel is transformed into an increase of jet kinetic energy per second.

chemical power in the fuel is transformed into propulsive power (T x V).

Q14. The gas turbine illustrated is of the following type:

single shaft turbine and centrifugal compressor

free turbine and centrifugal compressor

free turbine and axial compressor

single shaft turbine and axial compressor

Q15. The engine type represented in the annex is:

twin spool turbofan.

twin spool turbojet.

triple spool turbofan.

single spool turbofan.

Q16. The engine type represented in the drawing is a:

triple-spool turbofan

twin-spool turbojet

single spool turbofan

twin-spool turbofan

Q17. Increasing the power setting of a gas turbine engine with a constant speed propeller and free power turbine causes:

HP spool speed to decrease and EGT to increase.

HP spool speed to remain constant and EGT to increase.

HP spool speed to increase and EGT to remain constant.

both HP spool speed and EGT to increase.

Q18. Which statement is correct for a gas turbine engine with a constant speedpropeller and free power turbine, when the power setting is increased?I. The gas generator speed increases.II. The EGT decreases.

I is correct, II is correct

I is incorrect, II is correct.

I is incorrect, II is incorrect

I is correct , II is incorrect

Q19. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The HP spool speed increases.II. The EGT remains constant.

I is incorrect, II is incorrect.

I is correct, II is correct.

I is correct, II is incorrect.

I is incorrect, II is correct.

Q20. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The gas generator speed decreases.II. The EGT increases.

I is correct, II is correct.

I is correct, II is incorrect.

I is incorrect, II is correct.

I is incorrect, II is incorrect.

Q21. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed increases.II. The EGT remains constant.

I is incorrect, II is correct.

I is correct, II is correct.

I is incorrect, II is incorrect.

I is correct, II is incorrect.

Q22. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The HP spool speed increases.II. The EGT increases.

I is incorrect, II is correct.

I is correct, II is correct.

I is correct, II is incorrect.

I is incorrect, II is incorrect.

Q23. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is decreased?I. The HP spool speed decreases.II. The EGT decreases.

I is correct, II is incorrect.

I is incorrect, II is incorrect.

I is incorrect, II is correct.

I is correct, II is correct.

Q24. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The HP spool speed remains constant.II. The EGT increases.

I is correct, II is incorrect.

I is correct, II is correct.

I is incorrect, II is correct.

I is incorrect, II is incorrect.

Q25. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The HP spool speed decreases.II. The EGT increases.

I is correct, II is correct.

I is incorrect, II is incorrect.

I is correct, II is incorrect.

I is incorrect, II is correct.

Q26. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed increases.II. The EGT decreases.

I is incorrect, II is incorrect.

I is correct, II is incorrect.

I is incorrect, II is correct.

I is correct, II is correct.

Q27. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed remains constant.II. The EGT decreases.

I is correct, II is correct.

I is incorrect, II is incorrect.

I is incorrect, II is correct.

I is correct, II is incorrect.

Q28. Which statement is correct for a gas turbine engine with a constant speedpropeller and free power turbine, when the power setting is increased?I. The gas generator speed decreases.II. The EGT remains constant.

I is incorrect, II is correct.

I is correct, II is incorrect.

I is correct, II is correct.

I is incorrect, II is incorrect.

Q29. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed remains constant.II. The EGT decreases.

I is correct, II is correct.

I is correct, II is incorrect.

I is incorrect, II is correct.

I is incorrect, II is incorrect.

Q30. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed decreases.II. The EGT decreases.

I is correct, II is correct.

I is incorrect, II is correct.

I is correct, II is incorrect.

I is incorrect, II is incorrect.

Q31. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed increases.II. The EGT increases.

I is correct, II is correct.

I is incorrect, II is incorrect.

I is incorrect, II is correct.

I is correct, II is incorrect.

Q32. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed remains constant.II. The EGT increases.

I is correct, II is incorrect.

I is incorrect, II is correct.

I is correct, II is correct.

I is incorrect, II is incorrect.

Q33. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed decreases.II. The EGT remains constant.

I is incorrect, II is incorrect.

I is incorrect, II is correct.

I is correct, II is incorrect.

I is correct, II is correct.

Q34. The bypass ratio:I. is the ratio of bypass air mass flow to HP compressor mass flow.II. can be determined from the inlet air volume flow and the HP compressor volume flow.

I is incorrect, II is correct

I is correct, II is correct

I is correct, II is incorrect

I is incorrect, II is incorrect

Q35. The bypass ratio:I. is the ratio of bypass air mass flow to HP compressor mass flow.II. can be determined from the inlet air mass flow and the HP compressor mass flow.

I is incorrect, II is incorrect

I is incorrect, II is correct

I is correct, II is incorrect

I is correct, II is correct

Q36. A turbofan engine with an inlet air mass flow of 200 kg/s and a HP compressor mass flow of 20 kg/s has a bypass ratio of:

Q37. A turbofan engine with an inlet air mass flow of 300 kg/s and a HP compressor mass flow of 50 kg/s has a bypass ratio of:

1.2

Q38. A turbofan engine with a bypass mass flow of 250 kg/s and a HP compressor mass flow of 50 kg/s has a bypass ratio of:

1.2

Q39. A turbofan engine with an inlet air mass flow of 300 kg/s and a bypass mass flow of 250 kg/s has a bypass ratio of:

1.2

2.2

Q40. A turbofan engine with a bypass mass flow of 888 kg/s and a HP compressor mass flow of 111 kg/s has a bypass ratio of:

1.12

Q41. A turbofan engine with an inlet air mass flow of 1000 kg/s and a HP compressor mass flow of 111 kg/s has a bypass ratio of:

1.12

8.01

10.01

9.01

Q42. A turbofan engine with an inlet air mass flow of 220 kg/s and a HP compressor mass flow of 20 kg/s has a bypass ratio of:

1.1

Q43. A turbofan engine with a bypass air mass flow of 200 kg/s and a HP compressor mass flow of 20 kg/s has a bypass ratio of:

1.1

Q44. A turbofan engine with an inlet air mass flow of 220 kg/s and a bypass mass flow of 200 kg/s has a bypass ratio of:

1.1

Q45. A twin-spool engine with an inlet air mass flow of 500 kg/s and a HP compressor mass flow of 250 kg/s has a bypass ratio of:

Q46. A twin-spool engine with a bypass mass flow of 250 kg/s and a HP compressor mass flow of 250 kg/s has a bypass ratio of:

0.5

Q47. A twin-spool engine with an inlet air mass flow of 500 kg/s and a bypass mass flow of 250 kg/s has a bypass ratio (BPR) of:

Q48. A turbofan engine with an inlet air mass flow of 1000 kg/s and a bypass mass flow of 889 kg/s has a bypass ratio of:

2.12

17.02

8.01

1.12

Q49. For a fan jet engine, the by-pass ratio is the:

fuel flow mass divided by the internal airflow mass

internal airflow mass divided by the external airflow mass

internal airflow mass divided by the fuel flow mass

external airflow mass divided by the internal airflow mass

Q50. By-pass turbine engines are mainly used in commercial aviation, because:

at high subsonic airspeeds they have a better propulsive efficiency than propeller or straight jet engines

they produce less noise

twin spool or triple spool jet engines require a high by pass ratio

they are lighter than straight jet engines

Q51. The By-pass ratio of an engine is the ratio of:

Primary to tertiary air

Primary to secondary air

Cold stream air to that flowing through the hot core of the engine

Exhaust gas pressure to air intake pressure

Q52. The by-pass air in a turbo fan engine has the effect of a lower specific fuel consumption by causing an overall:

increase in the mean jet temperature and increase in thermal efficiency

increase in average exhaust gas flow velocity thus increasing engine pressure ratio

decrease in average exhaust gas flow velocity and a higher mass flow

decrease in combustion chamber temperature and higher thermal efficiency

Q53. The bypass ratio:I. is the ratio of inlet airflow to HP compressor flow.II. can be determined from the inlet air mass flow and the HP compressor mass flow.

I is correct, II is correct.

I is incorrect, II is correct.

I is incorrect, II is incorrect.

I is correct, II is incorrect.

Q54. The bypass ratio:I. is the ratio of inlet air mass flow to exhaust air mass flow.II. can be determined from the bypass air mass flow and the HP compressor mass flow.

I is correct, II is correct.

I is correct, II is incorrect.

I is incorrect, II is incorrect.

I is incorrect, II is correct.

Q55. The bypass ratio:I. is the ratio of the volume of air passing through the inlet to that through the HP compressor.II. can be determined from the inlet air mass flow and the bypass mass flow.

I is correct, II is incorrect.

I is incorrect, II is correct.

I is incorrect, II is incorrect.

I is correct, II is correct.

Q56. The bypass ratio:I. is the ratio of inlet air mass flow to HP compressor mass flow.II. can be determined from the inlet air volume flow and the HP compressor volume flow.

I is correct, II is incorrect.

I is incorrect, II is correct.

I is incorrect, II is incorrect.

I is correct, II is correct.

Q57. A twin-spool engine with an inlet air mass flow of 220 kg/s and a HP compressor mass flow of 220 kg/s has a bypass ratio of:

1.1

Q58. For a fan jet engine, the by-pass ratio is the:

hot air mass flow divided by the cold air mass flow

hot air mass flow divided by the fuel flow

cold air mass flow divided by the hot air mass flow

fuel flow divided by hot air mass flow

Q59. The bypass ratio in a turbine engine is the ratio of:

Cold air mass flow to the hot air mass flow

Speed of the combusted air to the speed of the bypass air

Intake air pressure to the turbine delivery air pressure

Tertiary air mass flow to the primary air mass flow

Q60. A booster or LP compressor in a twin spool turbofan:

rotates at the same rotor speed as the fan.

rotates at the same rotor speed as the HP compressor.

rotates at the same rotor speed as the HP turbine.

rotates at a rotor speed different from both fan, HP compressor and HP turbine.

Q61. A “fan” stage of a ducted-fan turbine engine is driven by:

the high pressure turbine

the high pressure compressor through reduction gearing

the low pressure turbine

airflow drawn across it by the high pressure compressor

Q62. In a multi-spool turbofan engine, the fan is driven by:

the rearmost turbine

the intermediate turbine

the foremost turbine

all three turbines since they are on a common shaft with the compressor

Q63. The fan of a turbofan engine is driven by:

The High Pressure compressor through reduction gearing

Airflow drawn across it by the High Pressure compressor

The Low Pressure turbine

The High Pressure turbine

Q64. The fan of a turbo-fan engine is driven by:

the HP compressor through reduction gearing.

the HP turbine.

airflow drawn across it by the HP compressor.

the LP turbine.

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Results

Q7. In the airflow through a single-spool axial flow turbo-jet engine, the axial velocity of the air is greatest:

Q8. When the combustion gases pass through a turbine the:

Q9. In the airflow through a single-spool axial flow turbojet engine, the axial velocity of the air is greatest:

Q10. The principle of aeroplane propulsion is to generate a propelling force by:

Q11. In a single spool gas turbine engine, the compressor rpm is:

Q12. In a turbo-jet, the purpose of the turbine is to …

Q13. Jet engine total efficiency indicates the efficiency at which:

Q14. The gas turbine illustrated is of the following type:

Q15. The engine type represented in the annex is:

Q16. The engine type represented in the drawing is a:

Q17. Increasing the power setting of a gas turbine engine with a constant speed propeller and free power turbine causes:

Q18. Which statement is correct for a gas turbine engine with a constant speedpropeller and free power turbine, when the power setting is increased?I. The gas generator speed increases.II. The EGT decreases.

Q19. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The HP spool speed increases.II. The EGT remains constant.

Q20. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The gas generator speed decreases.II. The EGT increases.

Q21. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed increases.II. The EGT remains constant.

Q22. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The HP spool speed increases.II. The EGT increases.

Q23. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is decreased?I. The HP spool speed decreases.II. The EGT decreases.

Q24. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The HP spool speed remains constant.II. The EGT increases.

Q25. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I.The HP spool speed decreases.II. The EGT increases.

Q26. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed increases.II. The EGT decreases.

Q27. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed remains constant.II. The EGT decreases.

Q28. Which statement is correct for a gas turbine engine with a constant speedpropeller and free power turbine, when the power setting is increased?I. The gas generator speed decreases.II. The EGT remains constant.

Q29. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed remains constant.II. The EGT decreases.

Q30. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed decreases.II. The EGT decreases.

Q31. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed increases.II. The EGT increases.

Q32. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed remains constant.II. The EGT increases.

Q33. Which statement is correct for a gas turbine engine with a constant speed propeller and free power turbine, when the power setting is increased?I. The gas generator speed decreases.II. The EGT remains constant.

Q34. The bypass ratio:I. is the ratio of bypass air mass flow to HP compressor mass flow.II. can be determined from the inlet air volume flow and the HP compressor volume flow.

Q35. The bypass ratio:I. is the ratio of bypass air mass flow to HP compressor mass flow.II. can be determined from the inlet air mass flow and the HP compressor mass flow.

Q36. A turbofan engine with an inlet air mass flow of 200 kg/s and a HP compressor mass flow of 20 kg/s has a bypass ratio of:

Q37. A turbofan engine with an inlet air mass flow of 300 kg/s and a HP compressor mass flow of 50 kg/s has a bypass ratio of:

Q38. A turbofan engine with a bypass mass flow of 250 kg/s and a HP compressor mass flow of 50 kg/s has a bypass ratio of:

Q39. A turbofan engine with an inlet air mass flow of 300 kg/s and a bypass mass flow of 250 kg/s has a bypass ratio of:

Q40. A turbofan engine with a bypass mass flow of 888 kg/s and a HP compressor mass flow of 111 kg/s has a bypass ratio of:

Q41. A turbofan engine with an inlet air mass flow of 1000 kg/s and a HP compressor mass flow of 111 kg/s has a bypass ratio of:

Q42. A turbofan engine with an inlet air mass flow of 220 kg/s and a HP compressor mass flow of 20 kg/s has a bypass ratio of:

Q43. A turbofan engine with a bypass air mass flow of 200 kg/s and a HP compressor mass flow of 20 kg/s has a bypass ratio of:

Q44. A turbofan engine with an inlet air mass flow of 220 kg/s and a bypass mass flow of 200 kg/s has a bypass ratio of:

Q45. A twin-spool engine with an inlet air mass flow of 500 kg/s and a HP compressor mass flow of 250 kg/s has a bypass ratio of:

Q46. A twin-spool engine with a bypass mass flow of 250 kg/s and a HP compressor mass flow of 250 kg/s has a bypass ratio of:

Q47. A twin-spool engine with an inlet air mass flow of 500 kg/s and a bypass mass flow of 250 kg/s has a bypass ratio (BPR) of:

Q48. A turbofan engine with an inlet air mass flow of 1000 kg/s and a bypass mass flow of 889 kg/s has a bypass ratio of:

Q49. For a fan jet engine, the by-pass ratio is the:

Q50. By-pass turbine engines are mainly used in commercial aviation, because:

Q51. The By-pass ratio of an engine is the ratio of:

Q52. The by-pass air in a turbo fan engine has the effect of a lower specific fuel consumption by causing an overall:

Q53. The bypass ratio:I. is the ratio of inlet airflow to HP compressor flow.II. can be determined from the inlet air mass flow and the HP compressor mass flow.

Q54. The bypass ratio:I. is the ratio of inlet air mass flow to exhaust air mass flow.II. can be determined from the bypass air mass flow and the HP compressor mass flow.

Q55. The bypass ratio:I. is the ratio of the volume of air passing through the inlet to that through the HP compressor.II. can be determined from the inlet air mass flow and the bypass mass flow.

Q56. The bypass ratio:I. is the ratio of inlet air mass flow to HP compressor mass flow.II. can be determined from the inlet air volume flow and the HP compressor volume flow.

Q57. A twin-spool engine with an inlet air mass flow of 220 kg/s and a HP compressor mass flow of 220 kg/s has a bypass ratio of:

Q58. For a fan jet engine, the by-pass ratio is the:

Q59. The bypass ratio in a turbine engine is the ratio of:

Q60. A booster or LP compressor in a twin spool turbofan:

Q61. A “fan” stage of a ducted-fan turbine engine is driven by:

Q62. In a multi-spool turbofan engine, the fan is driven by:

Q63. The fan of a turbofan engine is driven by:

Q64. The fan of a turbo-fan engine is driven by:

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