Modulo 15 EASA Tres

At higher then standard day ambient temperatures, compressor speed will be. lower than standard day speed. higher than standard day speed.

Ram Recovery' is a measure of. intake efficiency. net thrust.

most likely parameter limiting the height at which a jet engine powered aircraft can operate would be insufficient. lift to support the aircraft weight. oxygen to support combustion.

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

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

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

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

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

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

Temperature of the mass airflow through a Gas Turbine Engine. increases from the inlet, through the compressor and the diffuser into the burner, and decreases through the turbine into the exhaust. remains constant at the inlet, increases from the compressor and the diffuser into the burner, and decreases through the turbine into the exhaust.

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

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

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

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

Anti-ice is recommended during. OAT +10°Centigrade and visible moisture. OAT below 10°Centigrade.

A pitot intake is divergent from front to rear because it. reduces ram compression. produces the maximum amount of ram compression.

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

The term 'Ram Ratio' in regard to air intakes is the relationship between. ambient pressure and ambient temperature. ambient pressure and compressor inlet pressure.

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

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

Intake air turbulence. decreases 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 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.

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

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.

The vortex dissipators installed on some turbine-powered aircraft to prevent engine FOD utilize. variable geometry inlet ducts. 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. creating shock-waves in the intake.

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

When operating an engine in icing conditions, care should be taken when the. temperature is below +10°Centigrade with visible moisture. temperature is below 0°Centigrade.

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

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

What purpose does the nose cone serve on the(N1) fan on a high bypass engine?. Streamlined fairing. Reduce and straighten any turbulent air.

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

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

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

The variable inlet guide vanes are operated. by fuel pressure. electrically from cockpit.

The intake of a gas turbine engine is designed to. protect compressor from FOD. provide turbulent free air.

The velocity of air on entry to compressor inlet on an aircraft flying supersonic speed would be controlled at. Mach 2.2. Mach 0.4.

If an inlet is choked then the velocity. increases and pressure decreases. decreases and pressure increases.

In an aircraft flying at supersonic speed, to reduce the air velocity at the compressor, the variable intake. exhaust jet cone area increased. throat area is decreased.

A well designed intake will take advantage of forward speed by. converting kinetic energy into pressure energy. converting velocity energy into kinetic energy.

In subsonic multi-engine aircraft, a normal inlet duct will. decrease and then increase in size, front to rear, along length of the duct. increase in size, front to rear, along length of the duct.

What type of intake is one that decreases gradually in area and then increases?. Convergent. Convergent / Divergent.

. In an electrical de-icing system, the main elements will be on. continuously and intermittently. intermittently, 4 times a minute, dependant on OAT.

Intakes are designed to. decrease the intake air pressure. decelerate the free air stream flow.

The air intake for a gas turbine powered subsonic aircraft would be of. convergent form. divergent form.

turboprop engine inlet anti-ice system operates. continuously. cyclically dependant on weather conditions.

What is true for a bellmouth intake. Pressure increases and velocity decreases. Velocity increases and pressure decreases.