TM 1-1520-238-T-4
4–10
Change 4
4–3.
EQUIPMENT DATA
4–3
Item
Engine Characteristics/Data
Models
T700–GE–701
T700–GE–701C
Type of engine
Turboshaft
Output power (T700–GE–701)
1698 shaft horsepower (SHP), intermediate
rated power (IRP), at sea level, 15 degrees
Celsius standard day conditions at 20,900
rpm Np
Output power (T701–GE–701C)
1800 shaft horsepower (SHP) at sea level, 15
degrees Celsius standard day conditions at
20,900 rpm Np
Type of compressor
Combined axial/centrifugal
Number of compressor stages
6 stages (5 axial, and 1 centrifugal)
Variable geometry
Inlet guide vanes, stage 1 and 2 stator vanes
Type of combustion chamber
Single annular chamber with axial flow
Gas generator turbine stages
2
Power turbine stages
2
Direction of engine rotation (gas generator and power turbine
rotors)
Clockwise (aft looking fwd)
Engine weight (dry) T701
Engine weight (dry) T701C
438.5 lbs. maximum
456 lbs. maximum
Engine length
47 inches
Max engine diameter
25 inches
Fuel:
Primary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . JP–4 (MIL–T–5624), NATO Code F–40, or
JET B
Alternate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . JP–5 (MIL–T–5624), or JP–8 (MIL–T–83133),
NATO Code F–44, or NATO Code F–34,
JET A, or JET A–1
