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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.
The Pratt & Whitney J52 (company designation JT8A) is an axial-flow dual-spool turbojet engine originally designed for the United States Navy, [2] in the 40 kN (9,000 lbf) class. It powered the A-6 Intruder and the AGM-28 Hound Dog cruise missile. As of 2021 the engine was still in use in models of the A-4 Skyhawk.
The first test run of the TFE731 occurred in 1970 at Garrett's plant in Torrance, California. [2] The first production model, the TFE731-2, began rolling off the assembly line in August, 1972, and was used on the Learjet 35/36 and Dassault Falcon 10, both of which entered production in 1973.
The Boeing KC-135 Stratotankers were all originally powered by turbojet engines. With the demise of many airline 707s, the United States Air Force took the opportunity to buy the surplus airframes and use the engines to re-fit the KC-135As used by the Air National Guard and reserve squadrons with the civilian JT3D (designated TF33-PW-102). Over ...
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 ...
The PW 300 series has been developed in partnership with MTU who are responsible for the low pressure turbine. The first variant, the PW305A, has the following configuration and was designed with a core flexible enough for engines with take-off thrusts from 20 kN to 31 kN (4,500 to 7,000 lb): a single-stage fan driven by a three-stage low pressure turbine, supercharging a four-stage axial ...
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 ...