ENGINE PARAMETERS
1. Model............................. General Electric
CJ610-1—2,850 pounds thrust
General Electric CJ610-4—2,850 pounds
thrust
General Electric CJ610-6—2,950 pounds
thrust
General Electric CJ610-8A—2,950
pounds thrust
2. Type........................... Axial-flow turbojet
3. Compressor .................. Eight-stage, axial
flow with variable
interstage bleed
4. Turbine .................................... Two-stage
5. Engine main bearings ..................... Three
6. Engine rotation ............. Clockwise when
viewed from rear looking
forward; at 100%, 16,500 rpm
7. Fuel............................... Consult the AFM
for a list of approved fuels.
8. Oil................................. Consult the AFM
for a list of approved oils.
9. Engine length ........... Approximately 40.5
inches from front frame
through exhaust cone flanges
10. Engine diameter
(maximum) .................... Approximately
17.56 inches
11. Engine weight .................. Approximately
389 pounds
ENGINE
GENERAL
The CJ610 series engine is a single-spool
turbojet designed as a power unit for small- to
medium-sized corporate airplanes.
MAJOR SECTIONS
For descriptive purposes, the engine (Figure
7-1) is divided into seven major sections,
as follows:
1. Front frame
2. Compressor
3. Mainframe
4. Combustion
5. Turbine
6. Exhaust
7. Accessory
Front Frame
The front frame (Figure 7-2) admits air to the
compressor, directing air to the first-stage
rotor blades. The No. 1 bearing is mounted in
the front frame.
The front frame includes an inner and outer
shell joined by fifteen hollow struts. A mani-
fold around the front frame allows eighth-
stage bleed air to flow through the struts, the
bullet nose, and the inlet guide vanes for anti-
ice protection.
7-2
FOR TRAINING PURPOSES ONLY
LEARJET 20 SERIES PILOT TRAINING MANUAL
FlightSafety
international
ANTI-ICING
MANIFOLD
SUMP
COVER
BULLET
NOSE
ACTUATING RING
NO. 1 BEARING
CARBON SEAL
SHROUD
AND SEAL
INLET
GUIDE
VANE
Figure 7-2.
Front Frame Section