Specifications (J402-CA-400)

General characteristics

• Type: Turbojet
• Length: 29 in (74 cm)
• Diameter: 12.5 in (32 cm)
• Dry weight: 101.5 lb (46 kg)

Components

• Compressor: Single stage axial compressor single stage centrifugal compressor
  
• Combustors: Annular
• Turbine: Single stage high pressure turbine

Performance

• Maximum thrust: 660 lbf (2.9 kN)
• Overall pressure ratio: 5.6:1
• Fuel consumption: 1.2 lb/lbf-hr
• Thrust-to-Weight Ratio=: 6.5:1

MANUFACTURER: Boeing

DESIGNATION (Military): T50-BO-12.

ENGINE TYPE: Turboshaft. Dual-Shaft.

COMPRESSOR TYPE: Two-stage (axial and centrifugal), single-entry compressor.

TURBINE TYPE: Single stage, axial-flow turbine.

COMBUSTOR TYPE:Two reverse-flow combustion chambers.

POWER (take-off) RATING: 365 shp at 59°F.

BASIC DRY WEIGHT: 267 lbs.

APPLICATION: Navy Model QH-50D Drone.

Allied Signa Garret l JFS 100

Model JFS 100-13 Gas Turbine Engine

Model and type
JFS 100-13. Turboshaft, ( free turbine), The gas generator incorporates a 1-stage centrifugal compressor, annular combustor,1-stage axial flow turbine. The power turbine incorporates an axial flow turbine wheel assembly, a planetary reduction gear system an over running clutch system.

Compressor
Air inlet in front of unit. Single stage radial outflow, Single-entry impeller mounted on main shaft supported in 2 ball bearings. air mass flow 1.6 Ib/sec/72,500 rpm.

Combustor
Annular fuel manifold assembly, and five simplex fuel nozzles.

Turbine (Gas generator)
Hollow nozzle vanes.1-stage axial flow turbine. Maximum temperature 1850 F (1000)C.

Turbine (power)
Axial flow free turbine wheel attached to main gear train pinion and reduction gear.

Exhaust
Fixed area single outlet, exhausted downward.

Power take-off
Reduction gearbox at rear of unit. Output shaft 3,000 rpm.

Fuel system
Allied-signal-integral fuel system. pump, governor, internal relief valve, and flow control.

Ignition System
Bendix air-gap, ignition system. 1 igniter.

Lubrication
Sump type, Pressurized system.

Width and height
11.9 in and 12.0 in

Length
22.0 in

Weight
82.0 Ib

Power weight
1.09 shp/Ib

Fuel spec
Kerosene, or Jet-A

Fuel consumption
1.3 Ib/shp-hr

Oil spec; consumption
MIL-L-7808: 0.02phr

Rating
90 shp @ 60,400 power turbine rpm.



Manufacturer:    The Boeing Co., Commercial Airplane Division, Turbine Program
Model:    502-6
Type:    Turboshaft
Power:    160 bhp normal maximum (continuous)
Air Compressor:    Single stage, centrifugal
Burners:    Two: through-flow type
Turbine Stages:    Two: compressor and output turbines
Compressor Turbine Speed:    36,500 rpm normal maximum (continuous)
Compressor Turbine Rotation:    Counterclockwise, viewed from shaft end
Overspeed Limit:    3,210 to 3,290 rpm output shaft speed
Fuel:    Kerosene or Jet-A
Oil:    MIL-L-7808 OR MIL-L-23699
Electrical System:    24 Vdc
Weight:    200+ lbs (252 lbs stated in manual)
Dimensions:    43″L x 23″W x 23″H

Operating Limits:

Condition    Minimum    Normal    Maximum
Turbine RPM    Cranking    4,000 rpm    5,000 rpm    5,000 rpm
Idling    14,500 rpm    15,000 rpm    15,000 rpm
Rated Speed    —–    —–    36,500 rpm
Momentary    —–    —–    37,500 rpm
Turbine Oil Pres.    Rated Speed    35 psi    50 psi    70 psi
Auto. Shutdown    18 psi    20 psi    20 psi
Fuel Pressure    Starting    50 psi    100 psi    200 psi
Rated Speed    —–    350 psi    500 psi
Idling Speed    10 psi    10-50 psi    50 psi
Exhaust Temp.    Continuous    —–    1150F(621C)    1225F(663C)
Auto. Shutdown    —–        1300F(704C)