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How does engine thrust vary with temperature?. Increase in temperature gives greater thrust because of low friction in compressors. Low temperatures give low thrust. Low temperature gives greater mass flow and therefore greater thrust.

A method of comparing engine efficiencies is by comparing. fuel consumption. thrust to weight ratio. specific fuel consumption.

With a fixed throttle in a climb. RPM will increase. RPM will remain constant. RPM will decrease.

The point of maximum velocity in the engine is in the. exhaust exit nozzle. combustion chamber. nozzle guide vanes.

At constant RPM, the pressure ratio of the compressor and the temperature rise across the compressor. increases with height. remains constant irrespective of height. decrease with height.

With the aircraft stationary, propulsive efficiency. depends on RPM. is minimum. is maximum.

The efficiency of conversion of kinetic energy into propulsive work is a measure of. mechanical efficiency. propulsive efficiency. thermal efficiency.

What effect does high atmospheric humidity have on the operation of a jet engine?. Decreases compressor and turbine RPM. Decreases engine pressure ratio. Has little or no effect.

Power is adjusted in a gas turbine engine by. increasing fuel flow. increasing air and fuel flow. increasing airflow to the combustion chamber.

The engine rating plug. is permanently connected to the E E C. is connected to the EPR transmitter. is permanently connected to the Engine casing.

Flat Rated thrust is defined as. the thrust at the ambient temperature point above which thrust drops below 100%. that power achieved at idle RPM. that power achieved at maximum EGT.

Thrust rating on an FADEC controlled engine can be changed by. varying the ballast resistor in the EGT system. changing the engine rating plug. varying the EPR datum plug.

Propeller torque is analogous to. engine RPM. shaft horsepower. propeller RPM.

The total power in a turboprop engine is the. SHP. BHP. E S HP .

In a dive, with the throttles fixed, the EPR will. not change. increase. decrease.

With an increase in forward speed, the engine thrust. decreases slightly but recover due to ram effect. increases. decreases.

The main factor considered when designing an engine is. maximum fuel consumption. maximum turbine temperature. maximum tip speed.

To ensure an engine maintains self sustaining speed. idle remains same for any density. idle increases with density decrease. idle increases with density increase.

A factor that limits EGT is the. jet pipe. compressors. turbine.

Thrust will. increase at high temperatures. decrease at low temperatures. increase at low temperatures.

Across the turbines, there is. a general temperature rise. a general temperature drop. an isometric expansion.

If the throttle position remains constant. with increasing OAT, RPM and TGT will increase. with decreasing OAT, RPM will increase. with increasing OAT, TGT will increase.

If an aircraft climbs with a fixed throttle position. thrust decreases and RPM increases. thrust and RPM remain the same. thrust increases and RPM remains the same.

Ram pressure recovery will generally take effect at aircraft speeds of. mach 1. mach 0.1 - 0.2. only when the aircraft is stationary with engines running.

As the air is passed through the turbine, due to the convergent shape formed between adjacent blades. pressure decreases, velocity increases, temperature increases. pressure increases, velocity increases, temperature constant. pressure decreases, velocity increases, temperature decreases.

The hottest component in a gas turbine engine is. the nozzle guide vanes. the turbines. the combustion chamber.

The basic equation for thrust is. thrust = force * acceleration. thrust = mass * velocity. thrust = mass * acceleration.

To maintain the selected RPM of a gas turbine at altitude. the pilot will have to throttle back. more fuel will automatically be added. the fuel will automatically be reduced as the aircraft climbs.

The term Pb means. burner pressure measured at the diffuser case. burner pressure measured at the NGV. burner pressure measured at the combustion chamber.

Which of the following is not an engine rating?. Maximum Continuous. Idle. Maximum Take Off.

At higher then standard day ambient temperatures, compressor speed will be. lower than standard day speed. no different. higher than standard day speed.

Most likely parameter limiting the height at which a jet engine powered aircraft can operate would be insufficient. lift to support the aircraft weight. mass airflow to maintain 15:1 air/fuel ratio. oxygen to support combustion.

With increasing ram effect. turbine temperatures decreases. propulsive efficiency decreases. propulsive efficiency increases.

Full reverse power is approximately. 95% of forward thrust. 75% of forward thrust. 50% of forward thrust.

The efficiency of a gas turbine would be greatest at. cold temperatures. low pressure. hot temperatures.

In a gas turbine engine, turbine section. temperature decreases along with pressure and velocity. velocity decreases and pressure increases. velocity increases and pressure decreases.

In a gas turbine engine, turbine section. temperature decreases along with pressure and velocity. velocity decreases and pressure increases. velocity increases and pressure decreases.

As air density changes the RPM of a gas turbine engine will change. How is RPM kept at a constant speed?. It is not. Automatically by a simple engine device. Manually by the pilot.

With fixed throttle and increasing altitude, the fan on a high by-pass engine will. decrease RPM. increase RPM. stay the same RPM.

Through turbine rotor blades, the pressure. increases, temperature increases, velocity decreases. decreases, temperature and velocity decreases. remains constant, temperature increases.

If an electrical de-icing system is operating, thrust will. decrease. remain constant. increase.

A bellmouth compressor inlet is used on. helicopters. supersonic aircraft. aircraft with low ground clearance.

Electrical de-icing operates. continuously and intermittently. cyclically independent of ambient air temperature. cyclically dependent on ambient air temperature.

The inlet door on a variable geometry intake is open at. idle speed. supersonic speeds. subsonic speeds.

Pitot intake is divergent from front to rear because it. speeds up the air before it hits the compressor face. produces the maximum amount of ram compression. reduces ram compression.

Anti icing of jet engine air inlets is commonly accomplished by. electrical heating elements located within the engine air inlet cowling. electrical heating elements inside the inlet guide vanes. engine bleed air ducted through the critical areas.

An increase in the Ram Ratio of an intake will. increase the temperature of the compressed air. have no effect upon the temperature of the compressed air. decrease the temperature of the compressed air.

As an aircraft approaches the transonic range, the aerodynamic efficiency of a Pitot type intake. increases due to the ram effect. decreases due to the shock wave. is not effected by forward speed.

Inlet guide vanes are anti-iced with. rubber boots. thermal blankets. engine bleed air.

Intake air turbulence. decreases the efficiency of the compressor. increases the efficiency of the compressor. has little effect on the efficiency of the compressor.

What will be the effect of operating the intake anti-icing system of a gas turbine engine?. A decrease in power. Increased power at altitude. Increased power for take off.

A Pitot intake is divergent from front to rear because it. produces the maximum amount of ram compression. reduces ram compression and turbulence. speeds up the air before it hits the compressor face.

With an electrical ice protection system, the heating elements operate. continuously. part continuous - part intermittent. intermittently.

The purpose of a bellmouth compressor inlet is to. provide an increased ram air effect at low airspeeds. maximize the aerodynamic efficiency of the inlet. provide an increased pressure drop in the inlet.

The vortex dissipators installed on some turbine-powered aircraft to prevent engine FOD utilize. variable geometry inlet ducts. variable inlet guide vanes (IGV) and/or variable first stage fan blades. a stream of engine bleed air blown toward the ground ahead of the engine.

Variable Ramp Intakes restrict airflow by. diverting the airflow around the intake. reducing the area of the intake. creating shock-waves in the intake.

The inlet door of a variable geometry intake at supersonic speeds will be. closed. open. mid-Position.

Anti-icing for a turboprop is achieved by. bleed air supply from compressor. electric bonded heater mats. hot oil supply from lubrication system.

A divergent intake is. divergent from front to rear. convergent/divergent from front to rear. divergent/convergent from front to rear.

What purpose does the nose cone serve on the(N1) fan on a high bypass engine?. Streamlined fairing. Reduce. Assist.

A variable geometry intake at subsonic speeds. jet pipe area is increased. throat area is decreased. throat area is increased.

Electrical anti-ice. heats oil which is distributed around engine. heats elements, placed under mats around engine. heats air which is distributed around engine.

The cycling speed of the electrical de-icing mat. comes in 4 speeds. is not affected by weather conditions. is affected by weather conditions.