TURBINE ENGINE PART 3

What is the function of the inlet guide vane assembly on an axial-flow compressor?. Directs the air into the first stage rotor blades at the proper angle. Converts velocity energy into pressure energy. Converts pressure energy into velocity energy.

What must be done after the fuel control unit has been replaced on an aircraft gas turbine engine?. Perform a full power engine run to check fuel flow. Recalibrate the fuel nozzles. Retrim the engine.

Jet engine turbine blades removed for detailed inspection must be reinstalled in. a specified slot 180° away. a specified slot 90° away in the direction of rotation. the same slot.

What is the primary factor which controls the pressure ratio of an axial-flow compressor?. Number of stages in compressor. Compressor inlet pressure. Compressor inlet temperature.

Which of the following statements is true regarding welding and straightening of turbine engine rotating airfoils?. Special equipment is not required. Neither procedure is typically authorized by the engine manufacturer. These procedures are commonly recommended by the manufacturer.

Standard sea level pressure is. 29.00" Hg. 29.29" Hg. 29.92" Hg.

Reduced blade vibration and improved airflow characteristics in gas turbines are brought about by. fir-tree blade attachment. impulse type blades. shrouded turbine rotor blades.

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

What turbine engine section provides for proper mixing of the fuel and air?. Combustion section. Compressor section. Diffuser section.

In which type of turbine engine combustion chamber is the case and liner removed and installed as one unit during routine maintenance?. Can. Can-annular. Annular.

Fuel is normally supplied to an APU from the. APU independent fuel tank. airplane's header fuel tank. airplane's main fuel tank.

The non-rotating axial-flow compressor airfoils in an aircraft gas turbine engine, are called. rotor blades. stator vanes. disc rims.

Stator blades in the compressor section of an axial-flow turbine engine. increase the air velocity and prevent swirling. straighten the airflow and accelerate it. decrease the air velocity and prevent swirling.

The pressure of subsonic air as it flows through a convergent nozzle. increases. decreases. remains constant.

The recurrent ingestion of dust or other fine airborne particulates into a turbine engine can result in. foreign object damage to the compressor section. the need for less frequent abrasive grit cleaning of the engine. erosion damage to the compressor and turbine sections.

Newton's first law of motion, generally termed the law of inertia, states: To every action there is an equal and opposite reaction. Force is proportional to the product of mass and acceleration. Every body persists in its state of rest, or of motion in a straight line, unless acted upon by some outside force.

If, during inspection at engine overhaul, ball or roller bearings are found to have magnetism but otherwise have no defects, they. cannot be used again. are in an acceptable service condition. must be degaussed before use.

Compressor field cleaning on turbine engines is performed primarily in order to. prevent engine oil contamination and subsequent engine bearing wear or damage. facilitate flight line inspection of engine inlet and compressor areas for defects or FOD. prevent engine performance degradation, increased fuel costs, and damage or corrosion to gas path surfaces.

Which of the following types of combustion sections are used in aircraft turbine engines?. Annular, variable, and cascade vane. Can, multiple-can, and variable. Multiple-can, annular, and can-annular.

Which statements are true regarding aircraft engine propulsion?. An engine driven propeller imparts a relatively small amount of acceleration to a large mass of air. An engine driven propeller imparts a relatively large amount of acceleration to a smaller mass of air. In modern turboprop engines, nearly 50 percent of the exhaust gas energy is extracted by turbines to drive the propeller and compressor with the rest providing exhaust thrust.

Continued and/or excessive heat and centrifugal force on turbine engine rotor blades is likely to cause. profile. creep. galling.

Where do stress rupture cracks usually appear on turbine blades?. Across the blade root, parallel to the fir tree. Along the leading edge, parallel to the edge. Across the leading or trailing edge at a right angle to the edge length.

A turbine engine compressor which contains vanes on both sides of the impeller is a. double entry centrifugal compressor. double entry axial-flow compressor. single entry axial-flow compressor.

Turbine blades are generally more susceptible to operating damage than compressor blades because of. the high probability of carbon deposits. exposure to high temperatures. less exposure to solution during engine pressure wash.

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

Turbine nozzle diaphragms located on the upstream side of each turbine wheel, are used in the gas turbine engine to. decrease the velocity of the heated gases flowing past this point. direct the flow of gases parallel to the vertical line of the turbine blades. increase the velocity of the heated gases flowing past this point.

Generally, when starting a turbine engine, the starter should be disengaged. after the engine has reached self-accelerating speed. only after the engine has reached full idle RPM. when the ignition and fuel system are activated.

What is the possible cause when a turbine engine indicates no change in power setting parameters, but oil temperature is high?. High scavenge pump oil flow. Engine main bearing distress. Turbine damage and/or loss of turbine efficiency.

What is the function of the stator vane assembly at the discharge end of a typical axial-flow compressor?. To straighten airflow to eliminate turbulence. To direct the flow of gases into the combustion chambers. To increase air swirling motion into the combustion chambers.

In a turbine engine with a dual-spool, axial-flow compressor, the compressor and high-pressure turbine are. each split into two sections. driven by a single shaft. driven by a single, high-pressure turbine.

Which of the following is the ultimate limiting factor of turbine engine operation?. Compressor inlet air temperature. Turbine-inlet temperature. Burner-can pressure.

In a dual axial-flow compressor, the first stage turbine drives. N(2) compressor. N(1) compressor. low pressure compressor.

Severe rubbing of turbine engine compressor blades will usually cause. bowing. cracking. galling.