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Motore turbogetto General Electric J47
1948 - 1956



The GE J47 turbojet engine was developed by General Electric starting from the J35 engine and it was the first axial-flow turbojet approved for commercial use in the United States. Between 1948 and 1956 more than 30000 units have been built in several versions, with and without afterburner, and the engine underwent constant development with significant benefits in terms of power, reliability and increase of maintenance intervals.

Technical specifications

ManufacturerGE Aviation, General Electric, Massachussets, USA, from 1948 to 1956
Descriptionturbojet engine
Compressor12-stage axial flow
Compression ratio5.0
Airflow42 kg/s at 7950 rpm at sea level, in static conditions
Combustor8 tubular direct-flow inter-connected chambers, steel-sheet made
Turbineaxial single-stage type; distributor with 64 internally cooled vanes; SAE 4340 steel-made impeller core with an outer welded ring in Timken 16-25-6 alloy, in which 96 blades are inserted with sawtooth connection; inlet turbine gas temperature 870 C, outlet temperature 690 C at 7950 rpm
Ejectorfixed geometry propelling nozzle
Fuel feeding systemdouble fuel system with two gear pumps Pesco 2P-739-F, equipped with a barometric control system and a Pesco system for water injection in the combustion chambers
Fueljet fuel
Lubrication systemforced by a feeding gear pump and 4 scavenge gear pumps, with an oil cooler integrated in the storage tank
Maximum static thrust23140 N at 7950 rpm, at sea level
Maximum continuous thrust21030 N at 7630 rpm, at see level in static conditions
Thrust in cruise condition16470 N at 7000 rpm, at sea level in static conditions
Fuel specific consumption1.05 kg/daN/h
Diameter933 mm
Length3662 mm
Mass1134 kg
Mass-to-thrust ratio0.49 kg/daN


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Testi e immagini di Giuseppe Genchi
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