AS 311 - Exam 1
This does NOT include mathematical questions relating to AS 311, which will be on a separate deck.
118 flashcards · Other · by Nicholas Enoul
What device is pictured and what principle of turbine engine operations did it utilize? Hero's Aeolipile. Hot gas creates an equal and opposite reaction. Branca's Steam Turbine. Hot gas creates an equal and opposite reaction. Newton's Horseless Carriage. Hot gas creates motion by spinning a turbine. Da Vinci's Smoke Jack. Hot gas creates motion by spinning a turbine.
Hero's Aeolipile
What device is pictured and what principle of turbine engine operations did it utilize? Da Vinci's Smoke Jack. Hot gas creates motion by spinning a turbine. Newton's Horseless Carriage. Hot gas creates motion by spinning a turbine. Branca's Steam Turbine. Hot gas creates motion by spinning a turbine. Hero's Aeolipile. Hot gas creates an equal and opposite reaction.
Branca's Steam Turbine
How is this airplane related to the history of turbine engine development? First military turboprop engine. Reciprocating engines are fitted with turbochargers developed by Sanford Moss. First military turbine engine. First American airplane outfitted with turbine engine developed by Frank Whittle.
Reciprocating engines are fitted with turbochargers developed by Sanford (the boss) Moss
What airplane is pictured and how is it related to the history of turbine engine development? Gloster Meteor. First airplane with a turbofan engine. Gloster E28/29. First airplane with a turbine engine. Messerschmitt Me-262. First military airplane with a turbine engine. Heinkel He-178. First airplane with a turbine engine.
Heinkel He-178. First airplane with a turbine engine
What is Frank Whittle's direct contribution to the history of turbine engine development? First turbocharger. First turbojet engine. First turbine-powered commercial airplane. First turbine-powered airplane flight.
First turbojet engine.
What airplane is pictured and how is it related to the history of turbine engine development? DeHavilland Comet. First commercial airplane with a turbojet engine. DeHavilland Comet. First commercial airplane with a turbine engine. Boeing 707. First American airplane with a turbojet engine. Vickers Viscount. First commercial airplane with a turbine engine.
DeHavilland Comet. First commercial airplane with a turbine engine.
What kind of engine(s) are utilized on spacecraft? Rocket or ramjet Rocket Ramjet or scramjet Ramjet or pulsejet
Rocket
What type of engine compresses the incoming airflow without the use of a moving compressor? Turbojet Turboprop Ramjet Rocket
Ramjet
What type of engine is Engine #1? What benefits does Engine #1 have when compared to Engine #2? Engine #1 Engine #2 Answers: Turbojet engine - Decreased thrust to fuel ratio (specific impulse) Turbojet engine - Increased net thrust at almost all airspeeds; increased thrust-to-fuel (specific impulse) ratio; increased propulsive efficiency Turbo fan engine - Increased net thrust at almost all airspeeds; increased thrust-to-fuel (specific impulse) ratio; increased propulsive efficiency Turbo fan e…
Turbo fan engine - Increased net thrust at almost all airspeeds; increased thrust-to-fuel (specific impulse) ratio; increased propulsive efficiency
A turbojet's thrust _________ A. Is always greater than a reciprocating engine B. Is always less than a reciprocating engine C. Is not affected by airspeed D. Is greater than a reciprocating engine at high airspeeds
D. Is greater than a reciprocating engine at high airspeeds
A turbofan's propulsive efficiency _________ A. Decreases as airspeed increases B. Increases as airspeed increases C. Remains constant with airspeed D. Is not affected by airspeed
B. Increases as airspeed increases
What type of engine is used in this aircraft? Turbofan Turbojet Turboprop Turboshaft
Turboshaft
Assuming both engines produce the same thrust, which engine is most likely lighter (weighs less)? In other words, which engine most likely has a higher power-to-weight ratio? Engine #1 Engine #2 Answers: Engine #2: turboprop Engine #2: reciprocating Engine #1: ramjet Engine #1: turbofan
Engine #1: turbofan
What type of engine is used in this aircraft? Turbofan Turbojet Turboshaft Turboprop
Turboprop
What is one of the most basic differences between a turbojet and a turbofan engine? A. Turbojets have more compressor stages B. A turbofan has a bypass ratio C. A turbojet has a higher bypass ratio D. Turbofans have more turbine stages
B. A turbofan has a bypass ratio
The inlet of this aircraft moves (variable geometry) during flight. What is probably true about the aircraft? The aircraft is subsonic The aircraft must have a turbojet engine The aircraft is supersonic The aircraft utilizes stealth technology
The aircraft is supersonic
Air pressure in this engine's intake during a ground runup (static operations) is: A. Equal to ambient pressure B. Less than ambient pressure C. Steadily increasing D. Greater than ambient pressure
B. Less than ambient pressure
The first inlet is separated from the fuselage and the second inlet has small holes near the entrance. What is the common purpose for both of these design features? Answers: A. To create shockwaves that reduce intake air velocity B. To regulate the boundary layer and prevent turbulent inlet airflow C. To eliminate shockwaves that reduce intake air velocity D. To add high-energy air to the boundary layer
B. To regulate the boundary layer and prevent turbulent inlet airflow
What design feature must be present on a supersonic inlet? A. No special design features are required. B. A means of accelerating inlet airflow to at least M 1.0 C. A means of creating a shockwave to decrease the intake air velocity to subsonic speed D. All supersonic inlets must be variable geometry.
C. A means of creating a shockwave to decrease the intake air velocity to subsonic speed
What is the name and purpose of the movable door in this picture of a turboprop air inlet? Waste gate. Control engine RPM by controlling engine airflow. Internal separator. Vary airflow that reaches the compressor, thereby altering engine RPM. Variable geometry inlet. Create shockwave to reduce airflow velocity to less than M 1.0 Particle (inertial) separator. Protect the compressor from FOD and ice.
Particle (inertial) separator. Protect the compressor from FOD and ice.
What phenomenon is pictured and how can it be controlled? Compressor surge. Decrease engine RPM. Engine vortex. Blow-away jets or flat-bottom engine nacelle Compressor stall. Decrease engine RPM. Ground effect. Unavoidable consequence of proximity to the ground.
Engine vortex. Blow-away jets or flat-bottom engine nacelle
What is the purpose of a divergent engine inlet duct in a subsonic aircraft? A. Increase air flow velocity and decrease static pressure. B. Increase air flow velocity and increase static pressure. C. Decrease air flow velocity and decrease static pressure. D. Decrease air flow velocity and increase static pressure
D. Decrease air flow velocity and increase static pressure
How do most accessory gearboxes receive power? A. The electrical system B. The hydraulic system C. A drive chain. D. A drive shaft and a bevel gear
D. A drive shaft and a bevel gear
Accessories in the gearbox (e.g. fuel pump, oil pump, alternator) turn at a RPM that is: A. Always higher than the engine RPM B. Always lower than the engine RPM C. Always the same as the engine RPM D. Equal to, higher, or lower than the engine RPM.
D. Equal to, higher, or lower than the engine RPM.
What type of jet engine does not have an air intake or require an external air/oxygen source? In other words, what type of jet engine must carry its own oxidizer for combustion? A. Pulsejet B. Rocket C. Scramjet D. Ramjet
B. Rocket
What type of engine is pictured? Rotary Turbine Turboprop Reciprocating
Reciprocating
What type of engine has the highest power-to-weight ratio? A. Turbine B. Reciprocating
A. Turbine
What statement is true? A. Turbofan engines create the most thrust between "A" and "E" B. Turbojet engines create more thrust at all airspeeds C. Reciprocating engines create the least thrust at all airspeeds D. Reciprocating engines create the most thrust at airspeeds below "A"
D. Reciprocating engines create the most thrust at airspeeds below "A"
What conditions will yield the highest specific impulse (ISP)? A. High thrust and high fuel flow B. High thrust and low fuel flow C. Low thrust and low fuel flow D. Low thrust and high fuel flow
B. High thrust and low fuel flow NOTE: I don't think that the image has anything to do with this question, but it was together on Canvas.
Why does the turbofan with afterburner have a lower specific impulse than a turbofan without an afterburner? A. An afterburner increases fuel flow B. A plain turbofan goes faster C. An afterburner decreases fuel flow D. A plain turbofan decreases drag
A. An afterburner increases fuel flow NOTE: I don't think that the image has anything to do with this question, but it was together on Canvas.
Which statement is true regarding propulsive efficiency? A. A turboprop is always more efficient than a turbofan B. A turbojet is always less efficient than a turbofan C. A turbofan is always more efficient than a turboprop D. Bypass ratio does not affect efficiency
B. A turbojet is always less efficient than a turbofan
What type of engine is used to power the rotor on a helicopter? A. Turboshaft B. Turbojet C. Turbofan D. Turboprop
A. Turboshaft
What type(s) of engine(s) does/do not have a bypass ratio because all intake air is directed through the core of the engine? A. Turbofan B. Turbojet, turboprop, and turboshaft C. Only a turboprop D. All turbine engines have a bypass ratio
B. Turbojet, turboprop, and turboshaft
Textbook Question: What is the earliest indication, in history, of the presence of a jet propulsion device?
Hero's Aeolipile, 100-200 BC UNECESSARY SIDENOTE: The textbook states 100-200 BC, however, Heron of Alexandria was born around 10 AD, and was well known to have operated at around 60 AD. This means that he operated during Roman Egypt, not Ptolomeic. It seems to me that both the textbook and slides got this tidbit of information incorrectly, thusly, take everything (including this note), with a grain of salt.
Textbook Question: Whose first patent for a jet propulsion flight engine causes him to be recognized today as the father of the jet engine?
Sir Frank Whittle
Textbook Question: Which aircraft made the first purely jet-propelled flight?
The German Heinkel He-178
Textbook Question: Name America's first gas turbine-powered commercial airliner.
The Boeing 707 Pan Am 707 Picture from the Smithsonian's National Air and Space Museum in Chantilly Virginia (they also have a Concorde, Japanese Me 262 engine, a Space Shuttle, SR-71, and lots of other cool stuff there!)
Textbook Question: What purpose did the reciprocating engine serve in the Italian Caproni-Campini jet-propelled airplane?
The purpose of the reciprocating engine was to drive the compressor.
Textbook Question: What type of gas turbine was used to power the Vickers Viscount aircraft?
Turboprop
Textbook Question: What was the designation of the first jet-propelled fighter aircraft?
Messerschmitt Me-262
Textbook Question: What was the name of the first American jet-propelled fighter aircraft?
Airacomet P-59
Textbook Question: What was the designation of the Russian (Soviet) supersonic passenger liner comparable to the British/French Concorde?
Tupolev Tu-144
Textbook Question: Which of the four types of gas turbine engines would most likely be installed in a late-model business jet of the 500 m.p.h. class? Turbojet Turboshaft Turboprop Turbofan
4.Turbofan
Textbook Question: Name the western world's only supersonic transport
The Anglo-French Concorde Note: the only other supersonic transport of the time (which actually predated the Concorde) was the Soviet Tupolev Tu-144.
What type of compressor is present in this Rolls Royce Goblin engine? A. Turbojet B. Centrifugal C. This is not a turbine engine D. Axial
B. Centrifugal
What type of compressor is present in this engine? A. Radial out-flow B. Axial C. Axial and centrifugal D. Centrifugal
B. Axial
What engine component is immediately behind (aft of) the compressor and before (in front of) the combustor? A. Out-flow valve B. Diffuser C. Bleed valve D. Intake
B. Diffuser
What engine component is found within the yellow circle and what is its purpose? Swirl vane. Mix fuel and air mixture prior to entering the combustor. Diffuser. Decrease air flow velocity and increase static pressure before entering the combustor Stator vane. Direct airflow onto turbine blades. Inlet guide vane. Direct airflow onto turbine blades.
Diffuser. Decrease air flow velocity and increase static pressure before entering the combustor
The high-pressure stage of a 2-stage compressor is called: A. N2 B. N1 C. N1 D. C1
A. N2
What type of engine is present in this aircraft and does the engine have a free-power turbine? A. Turbojet or turbofan. No. B. Turboprop. No. C. Turboshaft. Yes. D. Turboprop. Yes.
C. Turboshaft. Yes.
What is the name and primary purpose of the blue blades in this image? A. Stator blades. Increase the static pressure and direct the airflow onto the rotor blades. B. Rotor blades. Increase the temperature and velocity of the intake air. C. Inlet guide vanes. Direct the inlet air onto the stator and rotor blades. D. Rotor blades. Increase the pressure of the inlet air.
D. Rotor blades. Increase the pressure of the inlet air.
Which statements are true of this compressor as compared to the other type of turbine engine compressor? A. It creates more drag and has a higher mass airflow B. It is cheaper and lighter C. It is more susceptible to FOD and has a longer spool up time D. It is more expensive and heavier
B. It is cheaper and lighter
What may a pilot do to induce a compressor stall? A. Descending too quickly B. Abrupt acceleration or deceleration C. Climbing too quickly D. Slow acceleration or deceleration
B. Abrupt acceleration or deceleration
What type of combustor is shown in this picture? A. Can-annular B. Cannular C. Annular D. Can
C. Annular Note: Answers A & B are trick questions! There is no difference between "Can-annular" and "Cannular" - which helps indicate that this combustor cannot be a cannular/can-annular design.
What is the purpose of the holes in this combustor? A. Only provide air for combustion B. Provide air for combustion, keep flame centered, and provide cooling for combustor and turbine blades C. Provide inlet ports for air/fuel mixture prior to combustion D. Only provide air for combustor cooling
B. Provide air for combustion, keep flame centered, and provide cooling for combustor and turbine blades
What type of combustor is pictured? A. Can B. Reverse flow C. Through-flow D. Axial flow
B. Reverse flow
The Pilatus PC-24 has a maximum cruising speed of approximately M 0.71. What design features should be present in the engine inlet? A. Variable geometry and convergent shape. B. Fixed geometry and convergent shape. C. Fixed geometry and divergent shape. D. Variable geometry and divergent shape.
C. Fixed geometry and divergent shape.
What is the purpose of a divergent inlet duct? A. It decreases velocity and increases static pressure. B. It increases velocity and decreases static pressure. C. It decreases velocity and decreases static pressure. D. Divergent inlet ducts are not used in modern aircraft designs.
A. It decreases velocity and increases static pressure.
What type of duct is installed on this Rolls Royce engine and what advantages or disadvantages are true of the inlet? Variable-geometry inlet. Inlet doors increase efficiency during transonic flight. Wide-body inlet. Decreases drag for transonic wide-body aircraft. Supersonic inlet. Low efficiency at low airspeeds...provides supersonic flow for supersonic compressors. Bellmouth inlet. High efficiency and high drag.
Bellmouth inlet. High efficiency and high drag. Note: One tip that helped me out is that almost all ground-installed engine testbeds use a Bellmouth inlet. This is because, when you're on the ground (gross thrust Fg), aerodynamic drag does not matter as much as it does when flying (net thrust Fn). Examples:
The Aerion AS2 is a prototype supersonic business jet. What design features must be present on the engine inlet? A. Only a divergent duct B. Only a convergent duct C. Variable geometry inlet with a convergent-divergent duct D. Convergent-divergent duct
D. Convergent-divergent duct Note: Even though the image shows what looks to be divergent inlets (inlet diameter increases as it goes back), the main principle is that, at supersonic speed, we need a way to lower inlet airspeed below Mach 1, so we have to answer the question in this way rather than answering based on the image alone.
What is one reason this engine nacelle is flat on the bottom? A. It dissipates ground effect vortices B. It reduces ice accumulation. C. It reduces compressor drag. D. The compressor fan is irregularly shaped.
A. It dissipates ground effect vortices
Why is there a gap between the engine inlet and the aircraft fuselage on this F-15 Eagle? A. It creates shockwaves and increases laminar airflow. B. It prevents shockwaves from forming and reduces turbulent airflow. C. It separates the high-energy boundary layer air and reduces laminar airflow. D. It separates the low-energy boundary layer air and reduces turbulent airflow.
D. It separates the low-energy boundary layer air and reduces turbulent airflow.
How are many accessory gearboxes driven? A. By a chain affixed to a flywheel. B. By a hydraulic pump and calibrated reduction valve. C. By a radial drive shaft and a bevel gear. D. By an electric motor and a high-current diode.
C. By a radial drive shaft and a bevel gear. Note: I am pretty sure that the only time the textbook ( at least for Exam 1) ever mentions a bevel gear is when it is related to accessory gearboxes.
What is the purpose of an accessory gearbox? A. To convert engine RPM to an optimum RPM for operating engine accessories. B. To convert accessory RPM to an optimum engine RPM to help turn the compressor. C. To convert engine hydraulic pressure to an optimum hydraulic pressure for operating engine accessories. D. To convert engine electrical current to an optimum electrical current for operating engine accessories.
A. To convert engine RPM to an optimum RPM for operating engine accessories.
You see a switch labeled "Inert Sep" on the instrument panel of a turboprop airplane. What does this switch control and what is the purpose for the system? A. Internal separation. Protects the combustor from excessive engine pressure. B. Inertial separator. Protects the compressor from FOD and ice. C. Internal separation. Divides the inlet air between the compressor and bleed air. D. Inertial separator. Reduces the airflow to the compressor to reduce engine pressure and temperature.
B. Inertial separator. Protects the compressor from FOD and ice.
What is the turbine section's primary purpose? A. Spin the compressor, propeller, and/or rotor B. Increase the exhaust gas pressure C. Decrease the exhaust gas velocity D. Decrease the exhaust gas pressure
A. Spin the compressor, propeller, and/or rotor
What is the N1 turbine's primary purpose? A. Spin the low pressure compressor B. Spin the high pressure compressor C. Increase exhaust gas pressure D. Spin the propeller or rotor
A. Spin the low pressure compressor
What is the name of the forward turbine section in this dual-spool turbojet engine? A. Free power turbine B. N2 high pressure turbine C. N2 low pressure turbine D. N1 high pressure turbine
B. N2 high pressure turbine Note: The turbine section in the back is what this question is referring to. Since the first section of a turbine is usually connected to the N2 compressor, this would have to be the N2 Turbine.
What is the name and purpose of the stationary blades at the exit of the combustion chamber? A. Turbine stage. Provide rotational energy to the compressor. B. N1 turbine. Provide rotational energy to the low pressure compressor. C. Turbine inlet guide vanes. Control airflow into the turbine. D. Turbine rotor blades. Extract energy from the exhaust gas.
C. Turbine inlet guide vanes. Control airflow into the turbine.
What turbine stage most likely spins the propeller in this Lancair Evolution turboprop? A. N1. Low pressure turbine. B. Ng. Free power turbine. C. The propeller is not spun by the turbine. D. N2. High pressure turbine.
B. Ng. Free power turbine. Note: According to the slides: "Free-power turbine: Drives gearbox, propeller, transmission"
By what method are turbine blades cooled? A. Bleed air from compressor section. B. Turbine blades are not cooled because higher temperatures create a more efficient turbine. C. Liquid cooled by coolant and radiator. D. Outside air that enters through gaps in the turbine case.
A. Bleed air from compressor section.
What is active clearance control? Cooling the turbine blades to ensure proper clearance between the turbine blade tips and the turbine case Altering the turbine RPM to ensure proper clearance between the turbine blade tips and the turbine case Cooling the turbine case to ensure proper clearance between the turbine blade tips and the turbine case Heating the turbine case to increase the gap between the turbine blade tips and the turbine case
Cooling the turbine case to ensure proper clearance between the turbine blade tips and the turbine case
What type of compressor(s) does this engine have? A. Reverse flow axial B. Axial and centrifugal C. Centrifugal only D. Axial only
B. Axial and centrifugal Note: The slides don't mention much (if at all) about axial-centrifugal compressors. If you want to learn more about these, the textbook entry is in Chapter 3 p 21 (3-21) under the "Combination Compressors" header. It isn't a long read, about one-two paragraphs, but pretty cool information overall.
What is the name and purpose of the blades on the inside of this compressor case? Variable rotor vanes. Compresses air flow and increases dynamic pressure. Stator blades or inlet guide vanes. Diffuses air flow, decreases velocity, increases static pressure, directs airflow onto rotor. Rotor. Compresses air flow and increases static pressure. Inlet guide rotor. Diffuses air to increase dynamic pressure and decrease static pressure.
Stator blades or inlet guide vanes. Diffuses air flow, decreases velocity, increases static pressure, directs airflow onto rotor.
The first three compressor stages on the left side of the image are the: A. N2 high pressure compressor B. N1 low pressure compressor C. N1 high pressure compressor D. N2 low pressure compressor
B. N1 low pressure compressor
What type of compressor is present in this engine and what are its benefits compared to the other type of compressor? A. Axial flow. Higher compression ratio, higher mass airflow, and decreased drag. B. Centrifugal flow. Higher compression ratio, higher mass airflow, and decreased drag. C. Centrifugal flow. Lower weight, lower cost, and faster spool-up time. D. Axial flow. Lower weight, lower cost, and faster spool-up time.
A. Axial flow. Higher compression ratio, higher mass airflow, and decreased drag.
Some compressor blades are twisted from root to tip. What is this called and what is its purpose? A. Composite. Provides uniform temperature. B. Washup. Decreases engine vibration. C. Camber. Provides uniform static pressure D. Stagger angle. Provides uniform air velocity.
D. Stagger angle. Provides uniform air velocity. Note: the textbook definition is: "A twist is present (called a stagger angle) from base to tip to maintain to maintain exit velocity of airflow at the same value along the blade length." (Ch. 3, p.15 [3-15])
What is the name and purpose of the component indicated by the red circle near the top of the image? A. Inlet guide vane. Provide uniform airflow velocity. B. Combustor diffuser. Increase static pressure. C. Combustor. Burn fuel and air mixture. D. High-pressure compressor. Increase static pressure.
B. Combustor diffuser. Increase static pressure. Note: If it is immediately behind the compressor, and in front of the combuster, it has to be a diffuser of some sort.
This compressor component is machined out of a single piece of metal. What is its name and benefit(s)? A. Combustor stator. Optimum airflow to the combustor. B. Blisk. Decreased weight. C. Mixed flow compressor. Increased strength. D. Stator-rotor combination disc. Decreased weight.
B. Blisk. Decreased weight. Note: Blade + Disk = Blisk :D
What condition may occur if you advance the throttle too quickly on a turbine engine? Why? A. No negative condition will occur. B. Compressor stall or surge due to combustor back pressure. C. Compressor overspeed due to increased rate of combustion. D. Compressor stall or surge due to increased mass airflow.
B. Compressor stall or surge due to combustor back pressure.
Outside air is directed through the compressor case in a series of ducts. What is the purpose of this cooling air? A. Shrinks the compressor case to maintain optimum compressor blade tip clearance. B. Shrinks the stator blades to maintain optimum stator blade tip clearance. C. Expands the compressor case to maintain optimum compressor blade tip clearance. D. Expands the rotor blades to maintain optimum rotor blade tip clearance.
A. Shrinks the compressor case to maintain optimum compressor blade tip clearance.
What type of combustor is present in this engine if the component in the yellow circle is the fuel injector? A. Mixed flow B. Through-flow C. Reverse flow D. Axial flow
C. Reverse flow
What is the name and purpose of this combustor component? The fuel injection nozzle is usually found protruding from the center of this component. A. Interconnector. Allows flame to propagate to different combustor chambers. B. Double annular combustor. Connects multiple annular combustor chambers. C. Air holes. Provide cooling air for combustor. D. Swirl vane. Mix fuel and air.
D. Swirl vane. Mix fuel and air.
What is/are the purpose(s) of the holes in the combustor liner? A. Allows the flame to propagate between combustion chambers and prevents excessive pressure. B. Allows only fuel to enter the combustor. C. Allows fuel/air mixture to enter the combustor. D. Aids combustion, protects the combustor liner from excessive temperature, and controls turbine inlet temperature.
D. Aids combustion, protects the combustor liner from excessive temperature, and controls turbine inlet temperature.
What condition may occur in a turbine engine if you fly above maximum manufacturer altitudes? A. Flameout due to rich mixture. B. Flameout due to lean mixture. C. Flameout due to excessive combustor back pressure. D. Flameout due to turbulent airflow entering the combustor.
B. Flameout due to lean mixture.
What is the primary purpose of the turbine section? A. Decrease the exhaust gas velocity to increase propulsive efficiency. B. Increase exhaust gas velocity to increase net thrust. C. Decrease exhaust pressure to decrease shockwave formation in the exhaust flow. D. Convert exhaust gas energy into rotational energy to spin the propeller, rotor, compressor fan, and/or compressor.
D. Convert exhaust gas energy into rotational energy to spin the propeller, rotor, compressor fan, and/or compressor.
What type of Turbine is pictured? A. Exhaust gas diffuser B. Axial flow turbine C. Combination turbine D. Radial inflow turbine
D. Radial inflow turbine
In what type of engine is this turbine usually found? A. Small turbojet engines B. Small turbofan engines C. Small turboprop or turboshaft engines D. Auxiliary power units
D. Auxiliary power units (APU)
What is the name and purpose of "A" in the picture? N2 turbine. Spins the low-pressure compressor (C). N1 turbine. Spins the low-pressure compressor (D). N2 turbine. Spins the high-pressure compressor (D). N1 turbine. Spins the high-pressure compressor (C).
N2 turbine. Spins the high-pressure compressor (D).
What is the name and purpose of the red blades at the top-right corner of the image? (Hint: Airflow is from right to left and the combustor is visible in the top-right corner of the image) Answers: A. Turbine inlet guide vanes. Direct airflow into the first stage turbine rotor. B. Turbine exit vanes. Direct air into the exhaust section. C. Free power turbine. Extract energy from the exhaust to spin the propeller or rotor. D. Compressor exit guide vanes. Direct air into the diffuser.
A. Turbine inlet guide vanes (TIGV). Direct airflow into the first stage turbine rotor.
What must be true of the turbine section in the turboprop engine in this Cessna Caravan? A. There must be a free power turbine. B. There must be at least 3 stages in the N1 turbine. C. There must be a N3 turbine. D. There must be a radial inflow turbine.
A. There must be a free power turbine.
What is the purpose of active clearance control? A. Maintain maximum distance between turbine blade tips and turbine case B. Ensure that turbine blade tips are always in contact with turbine case C. Provide cooling air to turbine blades D. Maintain optimum distance between turbine blade tips and turbine case
D. Maintain optimum distance between turbine blade tips and turbine case
How is compressor bleed air used in the turbine section? Heating of turbine case to maintain optimum blade-tip-clearance Cooling of turbine shaft to minimize friction and mechanical efficiency Cooling of both turbine blades and turbine case. Heating of turbine blades to maintain optimum blade-tip-clearance.
Cooling of both turbine blades and turbine case.
Textbook Question: What type of gas turbine engine does a helicopter use?
Turboshaft
Textbook Question: What type of compressor unit was in the gas turbine developed by Whittle?
Centrifugal Impellor Note: Centrifugal compressors are one of (if not the) oldest forms of compressor for turbine engines. This, I hope, will help out a bit :>
Textbook Question: Name the type of gas turbine most similar in design to the turboshaft engine.
Turboprop
Textbook Question: Which of the two forms of energy (potential and kinetic) is energy of motion?
Kinetic energy
Textbook Question: Which of Newton's laws states the principle of "action-reaction"?
Newton's 3rd Law
Textbook Question: What type of thermodynamic cycle of events is known as the Brayton cycle?
Continuous combustion cycle
Textbook Question: Bernoulli's principle describes the relationship between the velocity pressure and the static pressure of a fluid moving through a duct. Is this relationship direct or inverse?
An inverse proportion