NAVY AVIATION MACHINIST FINAL EXAM 2026/2027
QUESTIONS AND SOLUTIONS RATED A+
✔✔SAFETY- Hydromechanical Systems - ✔✔1. Hydromechanical systems operate at
extremely high pressure (3,000 psi)
2. A pin-hole leak at these pressures can force the fluid through your skin
3. Never attempt to repair system leaks with the system under pressure.
✔✔Power - ✔✔The rate of doing work or the rate of expanding energy
✔✔Motion - ✔✔The act or process of changing place or position
✔✔Velocity - ✔✔Rate of change of distance with the respect to time in a given direction
✔✔Acceleration - ✔✔Rate if change of velocity
✔✔Energy - ✔✔Ability to do work or bring about changes in matter
✔✔Intertia - ✔✔the property of a body to resist changes to its state of rest or motion
✔✔jet propulsion - ✔✔Propelling force generated in the direction opposite to the flow of
gas under pressure which is escaping through an opening called a jet nozzle
✔✔Standard Day - ✔✔59 degrees Fahrenheit with a barometric pressure of 29.92
inches of mercury. (14.7 psi) 0 humidity and 0 wind velocity
✔✔The Brayton Cycle - ✔✔Name given to the thermodynamic cycle of a gas turbine
engine to produce thrust.
✔✔What are the 4 continuous and constant events in the Brayton Cycle - ✔✔Intake,
Compression, Combustion and Exhaust
✔✔Thrust Classification - ✔✔Static and Net Thrust
✔✔Static Thrust - ✔✔Thrust produced when the aircraft or engine has no forward
motion
✔✔Net thrust - ✔✔Thrust available to power the aircraft in flight
✔✔Variables Affecting Thrust - ✔✔Revolutions Per Minute (RPM)
Humidity
Outside Air Temperature (OAT)
Barometric Pressure
, ✔✔Front Frame Section - ✔✔Location: Mounted on the front of the compressor
Description: Welded steel ring that houses the inlet guide vans (IGVS)
Purpose: Recieve air from the air inlet duct and pre-swirl the air (IGVS do this) in the
direction of rotation of the engine compressor rotor to prevent shock.
✔✔5 Components of the Compressor - ✔✔Casing, Rotor Assembly, Stator Assembly,
Exit Guide Vanes and the Diffuser
✔✔Compressor Section - ✔✔Location: Between the Front Frame and the Combustion
section
Purpose: To supply compressed air in sufficient quantities to satisfy the requirements of
the combustion section
✔✔Compressor Casing - ✔✔Outer housing for the compressor. Stator Assembly
mounted to this.
✔✔Compressor rotor assembly - ✔✔Compressor blades that accelerate the air
rearward. Attached by fir tree roots, dovetail or bulb. Locked in by peening, pins, lock
wire or keys. Assembly also include the compressor disk and compressor shaft.
✔✔Stator Assembly - ✔✔Consist of rows of stationary vanes dove tailed into split rings
and mounted to the compressor casing. Receive air form the preceding stage of rotor
blades and then compresses it.
✔✔Exit Guide Vanes - ✔✔Located at the compressor exit
Are stationary vanes with fixed vane angle and may consist of more than one rows
which straighten the compressor discharge to eliminate turbulence.
✔✔Diffuser - ✔✔Forms the compressor rear frame. Has a divergent designed duct to
develop a pressure wall to prevent reverse flow of combustion gases. Highest point of
pressure in the engine
✔✔Types of compresses - ✔✔Single Rotor- All blades rotate on one rotor
Dual Rotor (split spool)- There are two rotors in one engine
The last stage or stage of turbines turn the N-1 Compressor, while the first stage rotor
turns the N-2 Compressor
✔✔Compressor Air Flow - ✔✔Air inlet duct (Intake)> Inlet Guide Vanes> 1st Stage
Rotor Blades > 1st Stage Stator Vanes> Repeat> Last Stage of rotors> Exit Guide
Vanes> Diffuser> Combustion Section
✔✔Combustion Section - ✔✔Located between the Compressor section and turbine
section
Purpose to burn the fuel/air mixture adding heat energy to the mass airflow form the
compressor to drive the turbine which drive the compressor and accessories
QUESTIONS AND SOLUTIONS RATED A+
✔✔SAFETY- Hydromechanical Systems - ✔✔1. Hydromechanical systems operate at
extremely high pressure (3,000 psi)
2. A pin-hole leak at these pressures can force the fluid through your skin
3. Never attempt to repair system leaks with the system under pressure.
✔✔Power - ✔✔The rate of doing work or the rate of expanding energy
✔✔Motion - ✔✔The act or process of changing place or position
✔✔Velocity - ✔✔Rate of change of distance with the respect to time in a given direction
✔✔Acceleration - ✔✔Rate if change of velocity
✔✔Energy - ✔✔Ability to do work or bring about changes in matter
✔✔Intertia - ✔✔the property of a body to resist changes to its state of rest or motion
✔✔jet propulsion - ✔✔Propelling force generated in the direction opposite to the flow of
gas under pressure which is escaping through an opening called a jet nozzle
✔✔Standard Day - ✔✔59 degrees Fahrenheit with a barometric pressure of 29.92
inches of mercury. (14.7 psi) 0 humidity and 0 wind velocity
✔✔The Brayton Cycle - ✔✔Name given to the thermodynamic cycle of a gas turbine
engine to produce thrust.
✔✔What are the 4 continuous and constant events in the Brayton Cycle - ✔✔Intake,
Compression, Combustion and Exhaust
✔✔Thrust Classification - ✔✔Static and Net Thrust
✔✔Static Thrust - ✔✔Thrust produced when the aircraft or engine has no forward
motion
✔✔Net thrust - ✔✔Thrust available to power the aircraft in flight
✔✔Variables Affecting Thrust - ✔✔Revolutions Per Minute (RPM)
Humidity
Outside Air Temperature (OAT)
Barometric Pressure
, ✔✔Front Frame Section - ✔✔Location: Mounted on the front of the compressor
Description: Welded steel ring that houses the inlet guide vans (IGVS)
Purpose: Recieve air from the air inlet duct and pre-swirl the air (IGVS do this) in the
direction of rotation of the engine compressor rotor to prevent shock.
✔✔5 Components of the Compressor - ✔✔Casing, Rotor Assembly, Stator Assembly,
Exit Guide Vanes and the Diffuser
✔✔Compressor Section - ✔✔Location: Between the Front Frame and the Combustion
section
Purpose: To supply compressed air in sufficient quantities to satisfy the requirements of
the combustion section
✔✔Compressor Casing - ✔✔Outer housing for the compressor. Stator Assembly
mounted to this.
✔✔Compressor rotor assembly - ✔✔Compressor blades that accelerate the air
rearward. Attached by fir tree roots, dovetail or bulb. Locked in by peening, pins, lock
wire or keys. Assembly also include the compressor disk and compressor shaft.
✔✔Stator Assembly - ✔✔Consist of rows of stationary vanes dove tailed into split rings
and mounted to the compressor casing. Receive air form the preceding stage of rotor
blades and then compresses it.
✔✔Exit Guide Vanes - ✔✔Located at the compressor exit
Are stationary vanes with fixed vane angle and may consist of more than one rows
which straighten the compressor discharge to eliminate turbulence.
✔✔Diffuser - ✔✔Forms the compressor rear frame. Has a divergent designed duct to
develop a pressure wall to prevent reverse flow of combustion gases. Highest point of
pressure in the engine
✔✔Types of compresses - ✔✔Single Rotor- All blades rotate on one rotor
Dual Rotor (split spool)- There are two rotors in one engine
The last stage or stage of turbines turn the N-1 Compressor, while the first stage rotor
turns the N-2 Compressor
✔✔Compressor Air Flow - ✔✔Air inlet duct (Intake)> Inlet Guide Vanes> 1st Stage
Rotor Blades > 1st Stage Stator Vanes> Repeat> Last Stage of rotors> Exit Guide
Vanes> Diffuser> Combustion Section
✔✔Combustion Section - ✔✔Located between the Compressor section and turbine
section
Purpose to burn the fuel/air mixture adding heat energy to the mass airflow form the
compressor to drive the turbine which drive the compressor and accessories
