AMS 274 - Final Exam |124 Answered Questions
Frank Whittle - -Patented the first turbine engine (to function on a test stand)
-Turbofan (Patent) - -Another engine that Frank Whittle patented
-(The) Combustor - -Component that was the most challenging for Whittle to design when
designing the first turbine engine
-Sanford Moss - -GE Engineer known for his research on gas powered turbo-
superchargers
-Hans Von Ohain - -Patented and designed the engine used on the first propelled jet-
propelled flight
-GE (General Electric) - -The first USA turbine manufacturer to enter the "Jet Race"
-kinetic energy (and heat energy in the exhaust gases) into mechanical work - -Energy
flow of a turbine engine
-Rocket, Ramjet, Pulse-jet, Turbojet - -4 Types of Jet Engines
-Rocket - -Jet engine that carries its own oxygen supply
-Turbojet, Turbofan, Turboprop, Turboshaft - -4 Types of Turbojets
-Turbojet and Turbofan - -Engines that produce thrust
-Turboprop and Turboshaft - -Engines that produce torque
-IGV (Inlet Guide Vanes) - -Stationary airfoils that direct air into the compressor blades at
the optimum angle
-Nozzle Diaphragm - -Another name for Inlet Guide Vanes
-Diffuser - -Converts the kinetic(velocity) energy of the compressor discharge air into
pressure
-Annular, Can-Annular, Multi-Can - -3 types of combustors
-Multi-Can - -Older combustor containing multiple outer housings, each with its own
perforated inner liner
-Can-Annular - -Combustor more common for commercial aircraft, consisting of an outer
case containing multiple liners located radially about the axis of the engine
, -Annular - -Combustor that is most commonly used today; said to be the most efficient
designfrom the standpoint of thermal efficiency versus weightand for its shorter length
than the other types
-45 - -Percent of air leaving compressor that is used for combustion
-35 - -Percent of air leaving compressor that is used for cooling the combustor
-20 - -Percent of air leaving the compressor that is used for cooling the turbine
-Blending - -A hand method of re-contouring damaged blades and vanes; performed
parallel to the length of the blade to minimize stress points and to restore as smooth an
aerodynamic shape as possible to the surface
-Aerodynamic Blockage (Cascade/egg crate) and Mechanical Blockage (Clamshells) - -
Types of thrust reversers
-Compressor, Combustor, Turbine - -Main components of a turbojet engine
-Rotor --> Stator - -Order of components in the compression section (Rotor/Stator)
-Stator --> Rotor - -Order of components in the Turbine section (Rotor/Stator)
-Afterburner - -Supplements the normal thrust by increasing the acceleration of the air
mass through an additional temperature rise
-EGT (Exhaust Gas Temperature) - -Temperature taken at the turbine exit
-Hot Start - -Event that occurs during startup when exhaust temperature exceeds
prescribed limits
-Hung Start - -Event that occurs during startup when RPM does not increase to normal
idle value
-Lean-Die-Out - -A weak fuel to air mixture along with normal airflow through a turbine
engine
-EPR (Engine Pressure Ratio) - -Ratio of the pressure exiting the turbine section and the
pressure entering the compressor inlet
-Turbine Outlet / Compressor Inlet - -Formula for pressure ratio
-29.92 (Hg) - -Pressure on a standard day
-59(°F) - -Temperature on a standard day
Frank Whittle - -Patented the first turbine engine (to function on a test stand)
-Turbofan (Patent) - -Another engine that Frank Whittle patented
-(The) Combustor - -Component that was the most challenging for Whittle to design when
designing the first turbine engine
-Sanford Moss - -GE Engineer known for his research on gas powered turbo-
superchargers
-Hans Von Ohain - -Patented and designed the engine used on the first propelled jet-
propelled flight
-GE (General Electric) - -The first USA turbine manufacturer to enter the "Jet Race"
-kinetic energy (and heat energy in the exhaust gases) into mechanical work - -Energy
flow of a turbine engine
-Rocket, Ramjet, Pulse-jet, Turbojet - -4 Types of Jet Engines
-Rocket - -Jet engine that carries its own oxygen supply
-Turbojet, Turbofan, Turboprop, Turboshaft - -4 Types of Turbojets
-Turbojet and Turbofan - -Engines that produce thrust
-Turboprop and Turboshaft - -Engines that produce torque
-IGV (Inlet Guide Vanes) - -Stationary airfoils that direct air into the compressor blades at
the optimum angle
-Nozzle Diaphragm - -Another name for Inlet Guide Vanes
-Diffuser - -Converts the kinetic(velocity) energy of the compressor discharge air into
pressure
-Annular, Can-Annular, Multi-Can - -3 types of combustors
-Multi-Can - -Older combustor containing multiple outer housings, each with its own
perforated inner liner
-Can-Annular - -Combustor more common for commercial aircraft, consisting of an outer
case containing multiple liners located radially about the axis of the engine
, -Annular - -Combustor that is most commonly used today; said to be the most efficient
designfrom the standpoint of thermal efficiency versus weightand for its shorter length
than the other types
-45 - -Percent of air leaving compressor that is used for combustion
-35 - -Percent of air leaving compressor that is used for cooling the combustor
-20 - -Percent of air leaving the compressor that is used for cooling the turbine
-Blending - -A hand method of re-contouring damaged blades and vanes; performed
parallel to the length of the blade to minimize stress points and to restore as smooth an
aerodynamic shape as possible to the surface
-Aerodynamic Blockage (Cascade/egg crate) and Mechanical Blockage (Clamshells) - -
Types of thrust reversers
-Compressor, Combustor, Turbine - -Main components of a turbojet engine
-Rotor --> Stator - -Order of components in the compression section (Rotor/Stator)
-Stator --> Rotor - -Order of components in the Turbine section (Rotor/Stator)
-Afterburner - -Supplements the normal thrust by increasing the acceleration of the air
mass through an additional temperature rise
-EGT (Exhaust Gas Temperature) - -Temperature taken at the turbine exit
-Hot Start - -Event that occurs during startup when exhaust temperature exceeds
prescribed limits
-Hung Start - -Event that occurs during startup when RPM does not increase to normal
idle value
-Lean-Die-Out - -A weak fuel to air mixture along with normal airflow through a turbine
engine
-EPR (Engine Pressure Ratio) - -Ratio of the pressure exiting the turbine section and the
pressure entering the compressor inlet
-Turbine Outlet / Compressor Inlet - -Formula for pressure ratio
-29.92 (Hg) - -Pressure on a standard day
-59(°F) - -Temperature on a standard day
