General Electric J73

Design and Development

An engine, uprated from the J47, was required for the F-86H. The mass flow was increased by relocating accessories from the centre of the compressor inlet to the underside of the engine. This allowed a reduction in blade hub diameter, which together with an increase in tip diameter, gave a bigger area for air to enter the compressor. The area through the combustion chambers also had to be increased. This was done by replacing the multiple individual chambers with a single annular casing with individual flame tubes or cans known as cannular.

The pressure ratio was increased and variable inlet guide vanes fitted to prevent low-RPM problems (rotating stall/blade flutter) with the higher design pressure ratio. A 2-stage turbine was required.

A low boost (10% at take-off) afterburner was fitted. It was known as a tailpipe augmentation (TPA) system.

Variants

J73-GE-1

J73-GE-3

9,200 lbf (40.92 kN) for the North American F-86H Sabre

J73-GE-5

Applications

North American F-86H Sabre

Republic YF-84J Thunderstreak, two prototypes

Specifications (J73-GE-5)

Data from Flight.

General characteristics

Type: Turbojet

Length: 200 in (5 m)

Diameter: 39.5 in (1 m)

Dry weight: 3,650 lb (1,656 kg)

Components

Compressor: 12 stage, axial flow, variable inlet guide vanes

Combustors: 10 cannular combustion chambers

Turbine: 2 stage

Performance

Maximum thrust: 9,500 lbf (42 kN) dry, 12,500 lbf (55.6 kN) with afterburner

Overall pressure ratio: 7.5:1

Air mass flow: 155 lb/s (70 kg/s)

Specific fuel consumption: 0.9 lb/(h lbf) (dry power)

Thrust-to-weight ratio: 3.4 lbf/lb