Search results
Results from the WOW.Com Content Network
Modern turbofans are a development of the turbojet; they are basically turbojets that include a new section called the fan stage. Rather than using all their exhaust gases to provide direct thrust like a turbojet, turbofan engines extract some of the power from the exhaust gases inside the engine and use it to power the fan stage.
Turbofans are the most efficient engines in the range of speeds from about 500 to 1,000 km/h (270 to 540 kn; 310 to 620 mph), the speed at which most commercial aircraft operate. [ 21 ] [ 22 ] In a turbojet (zero-bypass) engine, the high temperature and high pressure exhaust gas is accelerated when it undergoes expansion through a propelling ...
The type of jet engine used to explain the conversion of fuel into thrust is the ramjet.It is simpler than the turbojet which is, in turn, simpler than the turbofan.It is valid to use the ramjet example because the ramjet, turbojet and turbofan core all use the same principle to produce thrust which is to accelerate the air passing through them.
The physical size of the gearbox was 17 inches (430 mm) in diameter, [2] or no more than half the gearbox size of the PW-Allison 578-DX propfan demonstrator engine that Pratt & Whitney worked jointly on with Allison in the 1980s. The gearbox consisted of 40 components, weighed 500 lb (230 kg), and shared a 3-U.S.-gallon (11-liter) oil tank with ...
Turbofans are usually more efficient than turbojets at subsonic speeds, but at high speeds their large frontal area generates more drag. [21] Therefore, in supersonic flight, and in military and other aircraft where other considerations have a higher priority than fuel efficiency, fans tend to be smaller or absent.
TSFC or SFC for thrust engines (e.g. turbojets, turbofans, ramjets, rockets, etc.) is the mass of fuel needed to provide the net thrust for a given period e.g. lb/(h·lbf) (pounds of fuel per hour-pound of thrust) or g/(s·kN) (grams of fuel per second-kilonewton). Mass of fuel is used, rather than volume (gallons or litres) for the fuel ...
Data from FAA Type Certificate Data Sheet, E-306 General characteristics Type: Single-spool turbojet Length: 188.9 in (4,798 mm) with thrust reverser/suppressor Diameter: 31.6 in (803 mm) Dry weight: 3,213 lb (1,457 kg) with thrust reverser/suppressor Components Compressor: 17-stage axial flow Combustors: can-annular Turbine: 2× gas generator power stages Fuel type: Aviation kerosene Oil ...
The engine has a wide-chord swept fan, two-stage low-pressure compressor and counter rotating high-pressure compressor based on a titanium impeller, for a 2,050 lbf (9.1 kN) takeoff thrust. [5] The HF120 engine's components interact with greater efficiency by incorporating 3D aerodynamic design, and its effusion-cooled combustor design emits ...