TURBINE ENGINE PART 2

Where is the highest gas pressure in a turbojet engine?. At the outlet of the tailpipe section. At the entrance of the turbine section. In the entrance of the burner section.

When aircraft turbine blades are subjected to excessive heat stress, what type of failures would the aviation mechanic expect?. Bending and torsion. Torsion and tension. Stress rupture.

What type of combustion chamber is used in a turbine engine when engine length is critical?. Can-annular. Annular. Reverse-flow.

What is the major function of the turbine assembly in a turbojet engine?. Directs the gases in the proper direction to the tailpipe. Supplies the power to turn the compressor. Increases the temperature of the exhaust gases.

Turbine engine components exposed to high temperatures generally may not be marked with. layout dye, commercial felt tip marker, or chalk. wax, grease pencil, or a graphite lead pencil. commercial felt tip marker or grease pencil.

Which of the following may be used to mark turbine engine components exposed to high temperatures?. Grease or wax pencil. Layout dye. Graphite lead pencil.

What is one purpose of the stator blades in the compressor section of a turbine engine?. Stabilize the pressure of the airflow. Control the direction of the airflow. Increase the velocity of the airflow.

One function of the nozzle diaphragm in a turbine engine is to. Decrease the velocity of exhaust gases. Center the fuel spray in the combustion chamber. Direct the flow of gases to strike the turbine blades at the desired angle.

Why do some turbine engines have more than one turbine wheel attached to a single shaft?. To facilitate balancing of the turbine assembly. To help stabilize the pressure between the compressor and the turbine. To extract more power from the exhaust gases than a single wheel can absorb.

The two types of centrifugal compressor impellers are. single entry and double entry. rotor and stator. impeller and diffuser.

Which of the following may be used to accomplish internal inspection of an assembled turbine engine?. Infrared photography. Ultrasound. A borescope.

The turbine section of a jet engine. increases air velocity to generate thrust forces. utilizes heat energy to expand and accelerate the incoming gas flow. drives the compressor section.

When in operation, the speed of an APU. is controlled by a cockpit power lever. remains at idle and automatically accelerates to rated speed when placed under load. remains at or near rated speed regardless of the load condition.

Which of the following variables affect the inlet air density of a turbine engine?. Speed of the aircraft, compression ratio, and ambient temperature. Speed of the aircraft, altitude of the aircraft, and ambient temperature. Compression ratio, turbine inlet temperature, and turbine and compressor efficiency.

At what stage in a turbine engine are gas pressures the greatest?. Compressor inlet. Turbine outlet. Compressor outlet.

Newton's law of motion, generally termed the "law of momentum," states: Acceleration is produced when a force acts on a mass. The greater the mass, the greater the amount of force needed. For every action there is an equal and opposite reaction. Every body persists in its state of rest, or of motion in a straight line, unless acted upon by some outside force.

In a gas turbine engine, combustion occurs at a constant. volume. pressure. density.

Which of the following statements is true regarding a turbine engine axial-flow compressor?. Each parallel pair of rotor blades and stator vanes constitutes a pressure stage. The number of rows of stages is determined by the amount of air and total pressure rise required. Each consecutive pair of rotor blades and stator vanes constitutes a pressure stage.

Using standard atmospheric conditions, the standard sea level temperature is. 59°F. 59°C. 29°C.

An advantage of the centrifugal-flow compressor is its high. pressure rise per stage. ram efficiency. peak efficiency.

The compression ratio of an axial-flow compressor is a function of the. number of compressor stages. rotor diameter. air inlet velocity.

Some high-volume turboprop and turbojet engines are equipped with two-spool or split compressors. When these engines are operated at high altitudes, the. low-pressure rotor will increase in speed as the compressor load decreases in the lower density air. throttle must be retarded to prevent overspeeding of the high-pressure rotor due to the lower density air. low-pressure rotor will decrease in speed as the compressor load decreases in the lower density air.

What is used in turbine engines to aid in stabilization of compressor airflow during low thrust engine operation?. Stator vanes and rotor vanes. Variable guide vanes and/or compressor bleed valves. Pressurization and dump valves.

What type igniter plug is used in the low tension ignition system of an aircraft turbofan engine?. Low voltage, high amperage glow plug. Self-ionizing or shunted-gap type plug. Recessed surface gap plug.

When starting a turbine engine,. a hot start is indicated if the exhaust gas temperature exceeds specified limits. an excessively lean mixture is likely to cause a hot start. release the starter switch as soon as indication of light-off occurs.

What is meant by a shrouded turbine?. The turbine blades are shaped so that their ends form a band or shroud. The turbine wheel is enclosed by a protective shroud to contain the blades in case of failure. The turbine wheel has a shroud or duct which provides cooling air to the turbine blades.

What is the first engine instrument indication of a successful start of a turbine engine?. A rise in engine RPM. A rise in oil temperature. A rise in the exhaust gas temperature.

Hot spots in the combustion section of a turbojet engine are possible indicators of. faulty igniter plugs. dirty compressor blades. malfunctioning fuel nozzles.

Who establishes the recommended operating time between overhauls (TBO) of a turbine engine used in general aviation?. The engine manufacturer. TBO does not apply to turbine engines. The aircraft manufacturer.

What are the two basic elements of the turbine section in a turbine engine?. Impeller and diffuser. Hot and cold. Stator and rotor.

The velocity of supersonic air as it flows through a divergent nozzle. increases. decreases. is inversely proportional to the temperature.

Which of the following factors affect the thermal efficiency of a turbine engine?. Ambient temperature, speed of the aircraft, and altitude of the aircraft. Turbine inlet temperature, compression ratio, and turbine and compressor efficiency. Turbine inlet temperature and ambient temperature.

The compressor stators in a gas turbine engine act as diffusers to. decrease the velocity of the gas flow. increase the velocity of the gas flow. increase the velocity and decrease the pressure of the gas.

The highest heat-to-metal contact in a jet engine is the. burner cans. turbine inlet guide vanes. turbine blades.