F-86's J47 WATER-INJECTION TURBOJET OPERATION DATA AND maintenance manual

[m13katyusa2020]

F-86's J47 WATER-INJECTION TURBOJET OPERATION DATA AND maintenance manual.
General characteristics Type: turbojet (/wiki-Turbojet)
Length: 145 inches (370 cm) (with tailcone)
Diameter: 36.75 inches (93.3 cm) maximum
Dry weight: 2,554 pounds (1,158 kg) dry, equipped Components
Compressor: 12-stage axial compressor (/wiki-Axial_compressor)
Turbine (/wiki-Turbine): single-stage axial
Fuel type: JP-1 (/wiki-JP-1), JP-2 (/wiki-Jet_fuel#Military_jet_fuels), JP-3 (/wiki-JP-3), JP-4 (/wikiJP-4) or MIL-F-5572 gasoline
Oil system: pressure feed spray with scavenge Performance
Maximum thrust (/wiki-Thrust): 5,970 lbf (26.56 kN) at 7950 rpm ; 6,970 lbf (31.00 kN) with water injection
Overall pressure ratio (/wiki-Overall_pressure_ratio): 5.35
Air mass flow: 92 lb/s (42 kg/s)
Specific fuel consumption (/wiki-Thrust_specific_fuel_consumption): 1.014 lb/(lbf⋅h) (28.7 g/(kN⋅s))
Thrust-to-weight ratio (/wiki-Thrust-to-weight_ratio): 2.34 at take-off dry power

Added: J47 Operation Manual thanks to mikejohnson96:

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Please download the following pdf attachment:

 

[m13katyusa2020]

F-86's J47 WATER-INJECTION TURBOJET OPERATION DATA AND maintenance manual.
General characteristics Type: turbojet (/wiki-Turbojet)
Length: 145 inches (370 cm) (with tailcone)
Diameter: 36.75 inches (93.3 cm) maximum
Dry weight: 2,554 pounds (1,158 kg) dry, equipped Components
Compressor: 12-stage axial compressor (/wiki-Axial_compressor)
Turbine (/wiki-Turbine): single-stage axial
Fuel type: JP-1 (/wiki-JP-1), JP-2 (/wiki-Jet_fuel#Military_jet_fuels), JP-3 (/wiki-JP-3), JP-4 (/wikiJP-4) or MIL-F-5572 gasoline
Oil system: pressure feed spray with scavenge Performance
Maximum thrust (/wiki-Thrust): 5,970 lbf (26.56 kN) at 7950 rpm ; 6,970 lbf (31.00 kN) with water injection
Overall pressure ratio (/wiki-Overall_pressure_ratio): 5.35 Air mass flow: 92 lb/s (42 kg/s)
Specific fuel consumption (/wiki-Thrust_specific_fuel_consumption): 1.014 lb/(lbf⋅h) (28.7 g/(kN⋅s))
Thrust-to-weight ratio (/wiki-Thrust-to-weight_ratio): 2.34 at take-off dry power
View attachment 670609

For materials of the engine, refer to Basic Aircraft Materials and treatment:

Basic Aircraft materials chemical composition, treatment and properties books and manuals thread

was written by George_F.Titterton, who was a top-grade engineer of Grumman Company. He was a knowledgable engineer, who was gone in 1998, at an age of 95 years old. Disclaimer: This item is shared for reference, for non-profitable use only. This manuals and blueprints are not meant to be used...

ww2aircraft.net

 

[m13katyusa2020]

J33 engine is a very early jet engine.

General characteristics

• Type: centrifugal compressor turbojet
• Length: 72 in (183 cm)
• Diameter: 41.5 in (105 cm)
• Dry weight: 850 lb (386 kg)

Components

• Compressor: single-stage double-sided centrifugal
• Combustors: 10 reverse-flow can
• Turbine: single-stage axial
• Fuel type: kerosene (AN-F32) or 100/130 gasoline
• Oil system: pressure spray, wet sump with scavenge cooling and filtration

Performance

• Maximum thrust: 1,650 lbf (7.33 kN)
• Overall pressure ratio: 3.8:1
• Air mass flow: 33 lb (15.0 kg)/second at 16,000 rpm
• Turbine inlet temperature: 1,220 °F (660 °C)
• Specific fuel consumption: 1.2 lb/(lbf⋅h) (34 g/(kN⋅s))
• Thrust-to-weight ratio: 1.94:1

Public J33 training manual in this folder:

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J33 training manual:

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A Russian scientist's book on an encyclopedia of Soviet Turbines:

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(This is an introduction only)

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Disclaimer: These items are shared for reference, sharing for non-profitable use only.
This manuals and blueprints are not meant to be used for current update material for certification / repair, but make an excellent reference for the scholar, collector, modeler or aircraft buffs .... For proprietary reasons we generally only provide civil manuals and blueprints on long-out-of-production Aircraft / Engines / Helicopter. The information is for reference only and we do not guarantee the accuracy or currency of any manuals.

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