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

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m13katyusa2020

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Mar 26, 2022
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:
alternate link:

another alternate link with access code 1234

1653390784569.png
Please download the following pdf attachment:
 

Attachments

  • T.O.2J-J47-26-Technical-Manual-Field-Mainenance-and-Replacement-J47-Turbojet-Engines-Changed-2...pdf
    62.2 MB · Views: 245
Last edited:
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:
 
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

Public J33 training manual in this folder:

alternate link with access code 1234

J33 training manual:

alternate link with access code 1234

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

Other theory introductions on basic theory of turbines:
(This is an introduction only)

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.


Reference herein to any specific commercial products by trade name, trademark, manufacturer, or otherwise, is not meant to imply or suggest any endorsement by, or affiliation with that manufacturer or supplier. All trade names, trademarks and manufacturer names are the property of their respective owners.
 

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