General_Electric_J73 Knowpia

J73
	Cutaway of a J73 at the NMUSAF
Type	Turbojet
National origin	United States
Manufacturer	General Electric
Major applications	North American F-86H Sabre
Number built	870
Developed from	General Electric J47
Developed into	General Electric J79

The General Electric J73 turbojet was developed by General Electric from the earlier J47 engine. Its original USAF designation was J47-21, but with innovative features including variable inlet guide vanes, double-shell (inner and outer) combustor case, and 50% greater airflow was redesignated J73. Its only operational use was in the North American F-86H.

Design and development edit

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.^[1]

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.^[2]^[3]

A low boost (10% at take-off) afterburner was fitted. It was known as a tailpipe augmentation (TPA) system.^[3]

Nuclear powered edit

Four J73 engines were converted to produce thrust using nuclear energy instead of jet fuel. Testing was done in 1957 at the Atomic Energy Commission's National Reactor testing station. The engines were modified to pass the compressor air through a heat exchanger, in which heat was transferred from a nuclear reactor, before entering the compressor turbine at 1,400 degrees F.^[4]

Variants edit

F-86H Sabre

J73-GE-1
J73-GE-3: 9,200 lbf (40.92 kN) for the North American F-86H Sabre.
J73-GE-5: Variant intended for a proposed Advanced F-89.^[5]

Applications edit

YF-84J Thunderstreak

North American F-86H Sabre
Republic YF-84J Thunderstreak, two prototypes

Specifications (J73-GE-3) edit

Data from Flight 9 April 1954 : Aero Engines 1954,^[6] Aircraft engines of the World 1953^[7]

General characteristics

Type: non-afterburning turbojet

J73-GE-5 with afterburning

Length: 200 in (5,080 mm)
Diameter: 39.5 in (1,003 mm)
Dry weight: 3,600 lb (1,630 kg)

Components

Compressor: 12 stage, axial flow, variable inlet guide vanes
Combustors: 10 cannular combustion chambers
Turbine: 2 stage axial turbine
Fuel type: MIL-F-5624A / JP-4
Oil system: dry sump, pressure spray with gear pumps

Performance

Maximum thrust: 9,000 lbf (40 kN)

J73-GE-5 - 9,500 lbf (42 kN) dry, 12,500 lbf (56 kN) with afterburner

Overall pressure ratio: 7.5:1
Air mass flow: 155 lb/s (70 kg/s)
Specific fuel consumption: 0.9 lb/(lbf⋅h) or 25 g/(kN⋅s)
Thrust-to-weight ratio: 2.5

J73-GE-5 - 2.64 dry, 3.47 with afterburner

References edit

^ "Aero Engines 1957". Flight: 133. 26 July 1957.
^ Johnsen, Irving A.; Bullock, Robert 0. (1965). NASA SP-36 : AERODYNAMIC DESIGN OF AXIAL-FLOW COMPRESSORS (PDF). Washington D.C.: NASA. pp. 27a, 44. Archived from the original (PDF) on 20 July 2018. Retrieved 24 February 2019.{{cite book}}: CS1 maint: numeric names: authors list (link)
^ ^a ^b Seven Decades of Progress: A Heritage of Aircraft Turbine Technology. Fallbrook: Aero Publishers. 1979. p. 82. ISBN 9780816883554.
^ https://archive.org/details/Aviation_Week_1957-03-18/page/n13/mode/2up, p.27
^ "Standard Aircraft Characteristics: Advanced F-89" (PDF). US Air Force. 3 December 1951. Retrieved 30 December 2018.
^ "Aero Engines 1954 : The World's Leading Aero-engine Constructors and their Products Reviewed". 9 April 1954: 457. Retrieved 24 February 2019. {{cite journal}}: Cite journal requires |journal= (help)
^ Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 82–83.