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Compressor stalls were a common problem on early jet engines with simple aerodynamics and manual or mechanical fuel control units, but they have been virtually eliminated by better design and the use of hydromechanical and electronic control systems such as full authority digital engine control. Modern compressors are carefully designed and ...
VR is the speed at which the nose is lifted off the runway, a process known as rotation. V2 is the single-engine safety speed, the single engine climb speed. [12] The use of these speeds ensure that either sufficient thrust to continue the takeoff, or sufficient stopping distance to reject it will be available at all times. [citation needed]
In aviation, a flameout (or flame-out) is the run-down of a jet engine or other turbine engine due to the extinguishment of the flame in its combustor.The loss of flame can have a variety of causes, such as fuel starvation, excessive altitude, compressor stall, foreign object damage deriving from birds, hail, or volcanic ash, severe precipitation, mechanical failure, or very low ambient ...
Low-speed pre-ignition; O. Overspeed; V. Vapor lock; W. Wet stacking This page was last edited on 13 December 2016, at 09:52 (UTC). Text is ... Engine problems.
During low-speed flight, controllable flaps close the bypass duct and force air directly into the compressor section of the turbojet. During high-speed flight, the flaps block the flow into the turbojet, and the engine operates like a ramjet using the aft combustion chamber to produce thrust. The engine would start out operating as a turbojet ...
Rolls-Royce Avon early jet engine showing 1 of 2 sets of 3 valves at the top and 1 of 2 valves at the bottom which release some air from the compressor, pressure ratio 7.45:1, for starting and low speed running. Also visible at the front is the row of bearings for the variable inlet guide vanes.
Turbofan engines with a bypass ratio of less than 2 (usually less than 1). These engines were commonly used on narrow body jet airliners of the 1960s and 1970s, some business jets from the same time period, and on modern fighter aircraft.
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 ...