PP 14

Cracked in a turbine blade 90 deg to the trailing edge is caused by the. Heat serious over temp. Metal fatigue from vibration.

Turbine blades are replaced. With one of the same weight, or the blade with 180 deg from it and 120 deg from it. With any blade of similar length.

What type of pump is not used in turbine engine. Piston pump. Gear pump.

Where is the oil temp. regular located?. In the return line to the tank of a dry sump system. In the pressure line to the bearings.

In a gas turbine engine combustion occurs at const. Constant pressure. Constant volume.

At a higher subsonic speed, the type of engine which affords the most efficient propulsive power is the. Turbofan. Turbojet.

A gas turbine engine utilized in a turboprop application has?. More turbine stages. Fewer turbine stages.

The gas generator section of a free turbine engine extracts approx. what % of the energy available from the combustion process. 66%. 50%.

Engines using a separate turbine to drive a reduction gearbox are called. Free turbine engines. Direct-drive engines.

When heated air leaves the combustion chamber, it passes through the turbine section where the press. Drops and volume increase. Increases and volume decreases.

Divergent duct, pressure inc and. Velocity dec. Velocity inc.

Stators in the turbine section of a gas turbine engine. Inc. velocity of the gas flow. Decrease gas velocity.

Eng. Manufacturers calculations of static thrust are based on a temp. of. 15 deg celcius. 10 deg celcius.

What is meant by shrouded turbine blades. Turbines blades are shaped do that their ends form a band or a shroud. Blades with removable tips.

The type of engine inlet duct used on subsonic acft is*. Divergent, fixed geometry. Convergent-divergent variable geometry.

In a turbine engine, the highest pressure is found. In the diffuser. In the turbine inlet.

High EGT, high fuel flow and low rpm at all engine power settings is most likely caused by. Turbine damage. Fuel pump wear.

The air inlet vortex dissipater used on some turbo jet engines. Minimize the ingestion of runway debris. Increase airflow at high altitude.

The mechanical blockage thrust reverser uses. Clamshell design. Cascade vane system.

On turbine engines, the type of bearing better equipped to support radial loads rather than thrust load is. Roller bearings. Ball bearings.

On a free turbine engine, engine control is required for. N2 only. N1 only.

If a minute cracked is found on a turbine disk. Is immediate cause for rejection of the turbine disk. Can be blended and reused.

Compressor blades which have reduced thickness at the tips are referred to as. Profile or squeeler blades. Thin-blade compressors.

In a reverse flow annular combustor, the main airflow enters the combustor from. The rear. The front.

A permanent elongation which occurs on turbine blades due to centrifugal force is. Creep. Stretch.

The primary airflow through a combustor. Is routed to the fuel nozzle area for combustion. Is routed only for cooling.

For turbine engines with a thrust augmentation system, water may be injected into the. Compressor inlet or into the combustion chamber. Turbine outlet.

The operation of an automatic fuel control unit on a turbojet is influenced by. Compressor discharge pressure. Oil pressure.

With no change in power setting parameters, if the engine oil temp. is high, this indicates. Engine main bearing distress. Low fuel pressure.

The capacity of the oil scavenge system must be ____ the capacity of the press. Sys. At least double. Equal to it.