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 ? Control > visibility

exemple question 169 — I correct ii correct. Piston engine combustion process intermittent governed the rythm of back forth movements of piston in a cylinder the combustion occurs at constant volume in cylinder turbine engine combustion process continuous occurs at constant pressure.

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 ?

exemple question 170 — 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 I correct ii correct. bypass ratio = bypass mass flow / hp compressor mass flow 220 220 = 0 0/220 = 0 bypass ratio = 0.

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 ?

exemple question 171 — 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 I correct ii correct. bypass ratio = bypass mass flow / hp compressor mass flow 200 20 = 180 180/20 = 9.

exemple question 172 — 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 I correct ii correct. bypass ratio = bypass mass flow / hp compressor mass flow 220 20 = 200 200 / 20 = 10.

exemple question 173 — 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 I correct ii correct. bypass ratio = bypass mass flow / hp compressor mass flow 200/20 = 10.

exemple question 174 — 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 I correct ii correct. bypass ratio = bypass mass flow / hp compressor mass flow 220 200 = 20 200 / 20 = 10.

exemple question 175 — The throttle lever angle tla information of a fadec controlled gas turbine engine provided To electronic engine control unit a direct electrical wiring connection. Tla (thrust lever angle) indicates position of thrust lever in control stand from a reference point usually this 0° when thrust lever at idle increases up to 40° when thrust lever advanced to take off position this thrust lever connected mechanical linkages to an electrical resolver synchro sensor called thrust lever angle resolver the resolver has a stator rotor the angle of rotor with respect to stator reference point changes as thrust lever moved this angle called thrust lever resolver angle (tra) this resolver connected to electronic engine control(eec) to control engine thrust different positions of thrust lever.

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 To electronic engine control unit a direct electrical wiring connection. bypass ratio = bypass mass flow / hp compressor mass flow 250 / 250 = 1.

Which of following statements regarding variable inlet guide vanes vigvs and variable stator vanes vsvs on a high bypass engines correct Vigvs are located at front of hp compressor and together with vsvs control compressor airflow. The compression system usually split into two units a low pressure (lp) compressor mounted on one shaft followed an high pressure (hp) compressor mounted on hp shaft driven its own (hp) turbine the fan blades of general electric engine on a boeing 747 800 behind fan compressor inlet guide vanes (inner circle) variable stator vanes (outer circle) can be seen.

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 Vigvs are located at front of hp compressor and together with vsvs control compressor airflow. bypass ratio = bypass mass flow / hp compressor mass flow 300 50 = 250 250 / 50 = 5.

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 Vigvs are located at front of hp compressor and together with vsvs control compressor airflow. bypass ratio = bypass mass flow / hp compressor mass flow hp compressor mass flow = 50 bypass = 250 250 / 50 = 5.

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 Vigvs are located at front of hp compressor and together with vsvs control compressor airflow. bypass ratio = bypass mass flow / hp compressor mass flow inlet = 300 bypass = 50 hp compressor mass flow 300 50 = 250 bypass ratio = 250 / 50 = 5.

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 Vigvs are located at front of hp compressor and together with vsvs control compressor airflow. bypass ratio = bypass mass flow / hp compressor mass flow 888 / 111 = 8.

Bleeding air from hp compressor of a turbofan whilst maintaining thrust increases Vigvs are located at front of hp compressor and together with vsvs control compressor airflow. oscarjp if there less air flow coming in egt will rise in function of that because there a loss on efficiency due to bleed more work demanded to system so fuel flow increases.

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 Vigvs are located at front of hp compressor and together with vsvs control compressor airflow. bypass ratio = bypass mass flow / hp compressor mass flow inlet = 500 bypass = 250 > compressor = 250 250 / 250 = 1.

Compressor stall due to An excessively high angle of attack of rotor blades. Like stall of a wing compressor stall caused a breakdown of airflow if your wing suitable high speed you fly at low speed large angle of attack stall most likely to occur a compressor stall most likely to occur when air flow stagnates in rear stages of compressor a compressor blade hitting oncoming airflow at an angle of attack that determined a combination of rotational speed the incoming airflow when incoming speed low angle of attack will be high when angle of attack gets too high blade stalls so when axial flow in a compressor backs up blades stall (pressure increase in rear stages this slows down flow) you can prevent this dumping some late stage air to atmosphere (via bleed valves).

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 An excessively high angle of attack of rotor blades. bypass ratio = bypass mass flow / hp compressor mass flow bypass mass flow = 1000 111 = 889 889 / 111 = 8 01.

Which of these statements about an reaction turbine are correct or incorrect i the pressure drops across nozzle guide vanes ii the pressure remains constant across rotor blades I correct ii incorrect. There a pressure drop a velocity increase across stator of a reaction turbine.

The electronic engine control of a fadec gas turbine engine checks All input output data. The full authority digital engine control system (fadec) receives all necessary data engine operation takes over virtually all of steady state transient control functions which includes compressor airflow control (vigv's vsv's etc).

Jet engine total efficiency indicates efficiency at which Chemical power in fuel transformed into propulsive power (t x v). The full authority digital engine control system (fadec) receives all necessary data engine operation takes over virtually all of steady state transient control functions which includes compressor airflow control (vigv's vsv's etc).

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