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Consist of a multi-bladed ducted propeller driven by a gas turbine engine.
Consist of a multi-bladed ducted propeller driven by a gas turbine engine.
Uses a relatively large diameter ducted fan that produces thrust and provides intake air to the compressor.
Uses a relatively large diameter ducted fan that produces thrust and provides intake air to the compressor.
Developed to provide a compromise between the best features of the turbojet and the turboprop.
Developed to provide a compromise between the best features of the turbojet and the turboprop.
This arrangement of a turbofan is rarely used since it cannot contribute to air compression at the inlet.
This arrangement of a turbofan is rarely used since it cannot contribute to air compression at the inlet.
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In a dual compressor forward fan engine, the fan is an integral part of
the __________ compressor.
In a dual compressor forward fan engine, the fan is an integral part of the __________ compressor.
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_________ drives only the fan while the intermediate and forward
turbines drive a forward, low pressure compressor and a rear, high
pressure compressor, respectively
_________ drives only the fan while the intermediate and forward turbines drive a forward, low pressure compressor and a rear, high pressure compressor, respectively
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The fans of turbofan engines produce between _______ of the total thrust.
The fans of turbofan engines produce between _______ of the total thrust.
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Refers to the ratio of incoming air that bypasses the core to the amount of air that passes through the engine core.
Refers to the ratio of incoming air that bypasses the core to the amount of air that passes through the engine core.
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Bypass ratio is 1:1
Bypass ratio is 1:1
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Bypass ratio is 2:1 or 3:1
Bypass ratio is 2:1 or 3:1
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What is the ratio of a High bypass
What is the ratio of a High bypass
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Is a comparison of the thrust produced by the fan to the thrust produced by the engine core exhaust
Is a comparison of the thrust produced by the fan to the thrust produced by the engine core exhaust
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Offers a higher propulsive efficiency and better fuel economy
Offers a higher propulsive efficiency and better fuel economy
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Is the ratio of air pressure leaving the fan to the air pressure entering the fan.
Is the ratio of air pressure leaving the fan to the air pressure entering the fan.
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Fan pressure ratio on a typical low bypass fan is approximately
Fan pressure ratio on a typical low bypass fan is approximately
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High bypass fans fan pressure
High bypass fans fan pressure
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Utilize titanium, lightweight stainless stell, and composite materials to surpass the fuel economy by more than 15 percent.
Utilize titanium, lightweight stainless stell, and composite materials to surpass the fuel economy by more than 15 percent.
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Designers have achieved a 30:1 bypass ratio by incorporating single or dual propellers with composite blades that are 12 to 15 feet in diameter.
Designers have achieved a 30:1 bypass ratio by incorporating single or dual propellers with composite blades that are 12 to 15 feet in diameter.
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5 major sections of a gas turbine engine
5 major sections of a gas turbine engine
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Cold Section of GTE
Cold Section of GTE
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Hot section of GTE
Hot section of GTE
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is designed to conduct incoming air to the compressor with a minimum energy loss resulting from drag or ram pressure loss; that is, the flow of air into the compressor should be free of turbulence to achieve maximum
operating efficiency.
is designed to conduct incoming air to the compressor with a minimum energy loss resulting from drag or ram pressure loss; that is, the flow of air into the compressor should be free of turbulence to achieve maximum operating efficiency.
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To recover as much of the total pressure of the free airstream
as possible and deliver this pressure to the compressor.
To recover as much of the total pressure of the free airstream as possible and deliver this pressure to the compressor.
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the air inlet duct is located directly in front of the compressor and is mounted to the engine.
the air inlet duct is located directly in front of the compressor and is mounted to the engine.
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Inlets are positioned near the wing root area.
Inlets are positioned near the wing root area.
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an air inlet of this type allows the aircraft manufacturer to build a more aerodynamic aircraft, the increased length of the inlet does introduce some inefficiencies.
an air inlet of this type allows the aircraft manufacturer to build a more aerodynamic aircraft, the increased length of the inlet does introduce some inefficiencies.
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air inlet consists of a fixed geometry duct whose diameter progressively increases from front to back.
air inlet consists of a fixed geometry duct whose diameter progressively increases from front to back.
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Air entering the compressor on a turbine engine must flow slower than the speed of sound.
Air entering the compressor on a turbine engine must flow slower than the speed of sound.
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This divergent shape works like a venturi in that as the intake air spreads out, its velocity _________ and its pressure __________.
This divergent shape works like a venturi in that as the intake air spreads out, its velocity _________ and its pressure __________.
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When air traveling at supersonic speeds flows through a convergent duct, its velocity _________ and pressure ________.
When air traveling at supersonic speeds flows through a convergent duct, its velocity _________ and pressure ________.
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When air traveling at supersonic speeds flows through a divergent duct, its velocity _________ and pressure ________.
When air traveling at supersonic speeds flows through a divergent duct, its velocity _________ and pressure ________.
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t is designed specifically for obtaining very high aerodynamic efficiency when stationary or in slow flight.
t is designed specifically for obtaining very high aerodynamic efficiency when stationary or in slow flight.
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develop the majority of their thrust with propeller rather than jet propulsion
develop the majority of their thrust with propeller rather than jet propulsion
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typically smaller than those used on turbojet or turbofan engines.
typically smaller than those used on turbojet or turbofan engines.
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is a top priority among turbine engine operators and manufacturers
is a top priority among turbine engine operators and manufacturers
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This vortex can become strong enough to lift water and debris such as sand, small stones, or small hardware from the ground and direct it into the engine. To help alleviate this problem, what kind of device is installed?
This vortex can become strong enough to lift water and debris such as sand, small stones, or small hardware from the ground and direct it into the engine. To help alleviate this problem, what kind of device is installed?
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The component that forces air into the engine is the
The component that forces air into the engine is the
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This ratio is the outlet pressure divided by the inlet pressure.
This ratio is the outlet pressure divided by the inlet pressure.
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To be effective, a modern compressor must increase the intake air pressure
To be effective, a modern compressor must increase the intake air pressure
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is taken from any of the various pressure stages of the compressor
is taken from any of the various pressure stages of the compressor
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Types of Compressors
Types of Compressors
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Types of design of blade attachment
Types of design of blade attachment
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Centrifugal-flow compressor consists of
Centrifugal-flow compressor consists of
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Sometimes called a radial outflow compressor
Sometimes called a radial outflow compressor
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One of the earliest compressor designs and is still used today in some smaller engines and auxiliary power units
One of the earliest compressor designs and is still used today in some smaller engines and auxiliary power units
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is usually made from forged aluminum alloy, heat treated, machined, and smoothed for minimum flow restriction and turbulence.
is usually made from forged aluminum alloy, heat treated, machined, and smoothed for minimum flow restriction and turbulence.
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consists of a forged disk with integral blades, fastened by a splined coupling to a common power shaft.
consists of a forged disk with integral blades, fastened by a splined coupling to a common power shaft.
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two impellers are mounted back-to-back
two impellers are mounted back-to-back
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allows a higher mass airflow than that of a similar sized single-stage, single-sided impeller
allows a higher mass airflow than that of a similar sized single-stage, single-sided impeller
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the air is expelled into a divergent duct called a
the air is expelled into a divergent duct called a
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acts as a divergent duct where the air spreads out, slows down, and increases in static pressure.
acts as a divergent duct where the air spreads out, slows down, and increases in static pressure.
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diverts the flow of air from the diffuser, which is an integral part of the manifold, into the combustion chambers.
diverts the flow of air from the diffuser, which is an integral part of the manifold, into the combustion chambers.
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The task of this compressor is to raise air pressure rather than air velocity
The task of this compressor is to raise air pressure rather than air velocity
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are stationary blades located between each row of rotating blades and act as diffusers at each stage, decreasing air velocity and raising pressure.
are stationary blades located between each row of rotating blades and act as diffusers at each stage, decreasing air velocity and raising pressure.
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The set of stator vanes immediately in front of the first stage rotor blades are called
The set of stator vanes immediately in front of the first stage rotor blades are called
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These vanes direct the airflow into the first stage rotor blades at the best angle while imparting a swirling motion in the direction of engine rotation.
These vanes direct the airflow into the first stage rotor blades at the best angle while imparting a swirling motion in the direction of engine rotation.
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automatically reposition themselves to maintain proper airflow through the engine under varying operating conditions
automatically reposition themselves to maintain proper airflow through the engine under varying operating conditions
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These vanes straighten the airflow and eliminate any
swirling motion or turbulence
These vanes straighten the airflow and eliminate any swirling motion or turbulence
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Compressor blade tips are reduced in thickness by cut-outs, referred to as
Compressor blade tips are reduced in thickness by cut-outs, referred to as
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high pressure, high speed, or N2 compressor and is typically driven by a single stage high-pressure turbine at the front of the turbine section
high pressure, high speed, or N2 compressor and is typically driven by a single stage high-pressure turbine at the front of the turbine section
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called the low pressure, low speed, or N1 compressor
called the low pressure, low speed, or N1 compressor
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On many turbofan engines, the compressor section is divided into three sections and is referred to as a
On many turbofan engines, the compressor section is divided into three sections and is referred to as a
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In triple-spool compressor arrangement ________is referred to as the low speed, or N1 compressor
In triple-spool compressor arrangement ________is referred to as the low speed, or N1 compressor
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next in line is called the intermediate, or N2 compressor,
next in line is called the intermediate, or N2 compressor,
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is the high
pressure, or N3
compressor.
is the high pressure, or N3 compressor.
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were developed to combine the best features of centrifugal and axial compressors and eliminate some of their disadvantages.
were developed to combine the best features of centrifugal and axial compressors and eliminate some of their disadvantages.
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occur when the compressor blades' angle of
attack exceeds the critical angle of attack.
occur when the compressor blades' angle of attack exceeds the critical angle of attack.
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cause air flowing in
the compressor to slow down and
stagnate, sometimes reversing
direction.
cause air flowing in the compressor to slow down and stagnate, sometimes reversing direction.
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can significantly impair engine performance, cause loss of power, and can damage the engine
can significantly impair engine performance, cause loss of power, and can damage the engine
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is typically located
directly between the compressor diffuser
and turbine section.
is typically located directly between the compressor diffuser and turbine section.
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for gas turbine engines is the
high-energy capacitor discharge system, consisting of an
exciter unit, two high-tension cables, and two spark
igniters.
for gas turbine engines is the high-energy capacitor discharge system, consisting of an exciter unit, two high-tension cables, and two spark igniters.
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Ignition system produces how many sparks
Ignition system produces how many sparks
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accomplishes the important task of
draining the unburned fuel after engine shutdown.
accomplishes the important task of draining the unburned fuel after engine shutdown.
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Approximately__________ of the incoming air is designated as primary
Approximately__________ of the incoming air is designated as primary
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Approximately __________ percent of the incoming air is designated as secondary
Approximately __________ percent of the incoming air is designated as secondary
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Two types of Flame Out
Two types of Flame Out
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usually occurs at high altitude where low
engine speeds and low fuel pressure form a weak flame
that can die out in a normal airflow
usually occurs at high altitude where low engine speeds and low fuel pressure form a weak flame that can die out in a normal airflow
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occurs during rapid engine acceleration
when an overly-rich mixture causes the fuel temperature to
drop below the combustion temperature or when there is
insufficient airflow to support combustion.
occurs during rapid engine acceleration when an overly-rich mixture causes the fuel temperature to drop below the combustion temperature or when there is insufficient airflow to support combustion.
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Types of Combustion Chambers
Types of Combustion Chambers
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consists of a series of
individual combustor cans which act
as individual burner units
consists of a series of individual combustor cans which act as individual burner units
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This type of combustion chamber is
well suited to centrifugal
compressor engines
This type of combustion chamber is well suited to centrifugal compressor engines
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consists of a
housing and perforated
inner liner, or basket.
consists of a housing and perforated inner liner, or basket.
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