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What type of starting system in high bypass turbofan engine?
High Bypass turbofan engines use pneumatics (air) for starting the engines.
What are the names of the jet turbo engines?
The term jet engine is loosely referring to an internal combustion airbreathing jet engine. A turbo, or turbocharger is a device, usually fitted to a car or truck, to increase an engine's efficiency by forcing more air into the combustion chamber. I can see how you might have confused the two, as they are both primarily based on a turbine-driven design.
What is the difference between high bypass and low bypass turbofan?
The difference between the low and high bypass turbofans is simply in the amount of air which goes into the engine versus the remainder that goes around (bypasses) the engine. In high bypass engines ( an engine on any large commercial jet) only 20% around 20% of air goes into the engine with 80% bypassing it. (The 80% generates most of the engine thrust) In low bypass engines, this ratio is much lower
What is the horsepower in a Jet engine on a 767?
The Boeing 767-300ER is powered by two (2) General Electric CF6-80C2B2 Gas Turbofan Jet Engines. The Boeing 767-300ER may also be powered by two (2) Pratt & Whitney PW4000 Turbofan Jet Engine Powerplants as well. But this answer will ONLY focus on the General Electric CF6-80C2B2 Gas Turbofan Jet Engine applicable to the Boeing 767-300ER airliner. Here are the technical specifications per GE CF6-80C2B2 Gas Turbofan Jet Engine: Maximum Static Thrust (Fg) = 51,590 Lbs Maximum Mass Airflow (Ms) = 1,650 Lbs/Sec Fan Bypass Ratio (FBR) = 5.31:1 Compressor Pressure Ratio (PR): 23:1 Compressor Efficiency (CE) = 75% There are two (2) different types of horsepower involved in Gas Turbine Jet Engines. 1.) Compressor Shaft Horsepower. This is the horsepower required to keep the compressor running on a gas turbine engine. The compressor sucks in air, compresses it to extremely high pressure, sends it to a combustion chamber(s) where it is mixed with kerosene jet fuel and ignited. The high velocity hot gases which exit the combustion chamber power a turbine(s) which is/are connected to the compressor by a shaft and in turn drive the compressor to keep the engine running. 2.) Thrust Horsepower. This is the overall horsepower of the aircraft while in flight consolidated with the net thrust rating of the turbine jet engines. Maximum static thrust is maximum thrust output while the aircraft and engine are held at rest and not permitted to move. Net thrust is the actual thrust used to move the aircraft which is the difference in exhaust jet velocity and forward aircraft speed times the mass airflow ingested into the engine, divided by gravitational acceleration. Net thrust is much lower than the static thrust rating of the engine. Total thrust horsepower is the aircraft flight speed divided into 375 then multiplied times total net thrust. Thrust horsepower does not exist if the engine and aircraft are not moving regardless to the power output or throttle setting of the engine(s). I will answer your question with two individual scenarios: Scenario #1: The first one will involve one CF6 Gas Turbofan Jet Engine held at rest on a jet engine stand in 60 degree F outside air temperature, not permitted to move while operated at Maximum Static Thrust power setting. In this scenario only Compressor Shaft Horsepower can be calculated. The Thrust Horsepower is ZERO since the engine is not moving in forward motion. Scenario #2: The second one will involve two (2) CF6 Turbofan Jet Engines while flying at 240 MPH on the Boeing 767-200ER airliner at maximum power right after the airliner goes airborne and gets off the ground, while flying in 45 degree F outside air temperature. In this scenario, both the Compressor Shaft Horsepower and Thrust Horsepower can be calculated. This Wiki Answer is going to be many pages long if I explain every little detail from here on, so I will just work out the calculations and produce the correct answers to these two individual scenarios: For Scenario #1: CDT (F) = [((((23^0.263) + (-1)) x (460 + 60))] / (0.75)) + (460 +60)] - [460] = 948.2 F Tr = 948.2 F - 60 F = 888.2 F Comp Ms = [(1) / (5.31)] x [1,650] = 310.73 Comp HP = [(888.2 x 0.24 x 310.73 x 778) / (550)] = 93,696.23 HP The engine will develop 93,696.23 Compressor Shaft Horsepower. For Scenario #2: CDT (F) = [((((23^0.263) + (-1)) x (460 + 45))] / (0.75)) + (460 +45)] - [460] = 907.57 F Tr = 907.57 F - 45 F = 862.57 F Comp Ms = [(1) / (5.31)] x [1,650] = 310.73 Comp HP = [(862.57 x 0.24 x 310.73 x 778) / (550)] = 90,992.52 HP V1 = [(240) x (22 / 15)] = 352 fps V2 = [(51,590 x 32.2) / (1,650)] = 1,006.8 fps Avg. Core & Fan Exhaust Nozzles NT = [((1,650) x (1,006.8 - 352)) / (32.2)] = 33,553.42 Lbt TNT = [(33,553.42 x 2)] = 67,106.84 Lbt THP = [(67,106.84) x (240 / 375)] = 42,948.38 HP 90,992.52 Compressor Shaft Horsepower will develop per engine. 42,948.38 Total Thrust Horsepower will develop amongst both engines. ---------------------End Wiki Answer----------------------
Where is the engine size marked on the engine?
normal on the front face of the engine or the right hand side of the engine
What type of engine is in the Boeing 737?
turbofan
Who invented the turbofan engine?
Gerhard Neumann
Which type of engine is used by F-16?
Pratt & Whitney F100 turbofan engine
How does an airplane accelerate?
An aircraft uses a turbofan engine to reach takeoff and cruising speed. Look up TURBOFAN on Google for more info!
What type of starting system in high bypass turbofan engine?
High Bypass turbofan engines use pneumatics (air) for starting the engines.
What is airplane engine called?
Piston, turbojet, turbofan, turboprop to name a few.
What are The differences between a turbofan and a propeller?
A propeller is completely external and is the main source of propulsion for a airplane with a piston or turbojet engine. A turbofan is more enclosed and provides some propulsion along with also cooling the jet engine that is the main source of propulsion.
What type of engine does the f-16 has?
Most F-16 have the F110-GE-100 afterburning turbofan
What kind of engine does a F-16 have?
The F-16 has 1 F110-GE-100 afterburning turbofan
What helps an airplane to move?
Thrust, typically created by a propeller attached to an internal combustion or turbine engine, or by a turbofan.
What has the author Ronald H Soeder written?
Ronald H Soeder has written: 'Effect of combined pressure and temperature distortion orientation on high-bypass-ratio turbofan engine stability' -- subject(s): Airplanes, Turbofan engines
Which engine is more efficient in jet engines. Turbo jet or the Turbo fan?
The term "Turbofan" is actually quite broad, but can be broken down into two categories…high and low bypass. The question you are really trying to ask is which engine type (high bypass or low bypass) turbofan engine is more efficient? High bypass engines are used on most commercial airplanes (except the Concord) and these engines are favorable because they have a balance of high thrust, and efficiency. Aircraft that need supersonic capabilities (like the Concord) use a low bypass turbofan engine. These engines produce the thrust required to propel a plane beyond the speed of sound, but at the cost of efficiency. They burn a lot of fuel in doing so. So one could draw the conclusion that high bypass turbofan engines are more efficient, but this would not be true. In order to propel a plane beyond the speed of sound the low bypass turbofan engine is the most efficient way of doing so. On the flipside, the high bypass turbofan engine is most efficient for practical air travel. Both engine types are very different, but each are specialized to achieve different goals.
