General Electric CF34

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CF34
Canadair CL-600-2B19 Regional Jet CRJ-200LR, UTair Aviation AN2213397.jpg
A CF34 installed on a Bombardier CRJ200
Type Turbofan
National origin United States
Manufacturer General Electric
First run 1982[1]
Major applications Bombardier Challenger 601/604/605
Bombardier Challenger 850
Bombardier CRJ
Embraer E-Jets
Comac ARJ21
Developed from General Electric TF34
Developed into General Electric NG34[2]
A CF34-8 mounted on the #2 pylon of GE's Boeing 747-100 flight test aircraft at Mojave Airport in 2002.

The General Electric CF34 is a civilian turbofan developed by GE Aircraft Engines from its TF34 military engine. With more than 5,600 engines in service (as of 2012), the CF34 is used on a number of jet airliners, including the Bombardier CRJ series, the Embraer E-Jets, and the Chinese ARJ21 under development.[3][4]

Design and development[edit]

CF34 engine mounted on an Embraer E-190

The original engines comprise a single stage fan, driven by a 4-stage low pressure (LP) turbine, supercharging a 14-stage HP compressor, driven by a 2-stage high pressure (HP) turbine, with an annular combustor. Later higher thrust versions of the CF34 feature an advanced technology core, with only 10 HP compressor stages. Latest variants, the -10A and -10E, were derived from the CFM56 engine family, and have a radically different HP spool, comprising a 9 stage compressor driven by a single stage turbine. The LP spool has 3 core booster stages behind the fan. Static thrust is 18,500 lbf for the -10E variant.


Applications[edit]

Recent versions of the CF34 feature chevrons on the core nozzle outlet.
The CF34 powers the Embraer E-jets; here a People’s Viennaline Embraer ERJ-170-100.
CF34-1
CF34-3A
CF34-3A1
CF34-3A2
CF34-3B
CF34-3B1
CF34-8C1
CF34-8C5
CF34-8C5A1
CF34-8C5B1
CF34-8E
CF34-10A
CF34-10E

Specifications[edit]

CF34-1 CF34-3 CF34-8 CF34-10
Length 103 in (2.6 m) 121.2 in (3.08 m) - 128 in (3.3 m) 90 in (2.3 m) - 145.5 in (3.70 m)
Diameter 49 in (1.2 m) 52 in (1.3 m) - 53.4 in (1.36 m) 57 in (1.4 m)
Dry weight 1,625 lb (737 kg) - 1,670 lb (760 kg) 2,408 lb (1,092 kg) - 2,600 lb (1,200 kg) 3,700 lb (1,700 kg)
Compressor 1 fan
14 HP stages
1 fan
10 HP stages
1 fan + 3 LP stages
9 HP stages
Turbine 4 LP stages
2 HP stages
4 LP stages
2 HP stages
4 LP stages
1 HP stage
Thrust
at sea level
9,220 lbf (41.0 kN) 13,790 lbf (61.3 kN) - 14,510 lbf (64.5 kN) 18,285 lbf (81.34 kN) - 20,000 lbf (89 kN)
Thrust-to-weight
ratio
5.6:1 5.3:1 5.2:1
Overall pressure ratio
at max. power
21:1 28:1 - 28.5:1 29:1
Bypass ratio 6.2:1 5:1 5:1

See also[edit]

Related development
Comparable engines
Related lists

References[edit]

External links[edit]