Airplane Engines - Decreasing Fuel Consumption and Exhaust Gas Emissions in Transportation - page 151

temperature [°C]

30 126 580 1 400 875 (max 950) 575

pressure [kPa]

101.4 235.8 201.3 284.1 234.4 162.1

1 2 3 4 5 6 7

1. spiner cone
2. Low Pressure Compressor (LPC) containing 4 grades
3. Variable Bypass Valves (VBV) containing 12 valves
4. High Pressure Compressor and
Variable Stator Vanes (HPC and VSV)

5. thrust reverser
6. combustion chamber
7. High Pressure Turbine and Low Pressure Turbine
(HPT and LPT)

Fig. 10.4 Temperature and pressure at the main measuring points in the engine type CF6-50 E/C 2

Table 10.3 Main operation
parameters of the engine type
CF6-80C2B1F

Parameters Values

Total thrust 226.85 kN (51,000 lbf)

9,300 kp h -1 (660,905 pdl h -1 )

Fuel flow

RPM N1 fan speed 3,433 (100%)

RPM N2 core speed 9,827 (100%)

685 kg s -1 (1,510 lb s -1 ) Air flow

558 kg s -1 (1,230 lb s -1 )

Fan air flow

127 kg s -1 (280 lb s -1 ) Prim air flow

Bypass ratio 4.4:1

Compression-ratio 29.4:1

EGT 887C (1,629F) (max 950C

(1,712F) up to 2 min)

Turbine inlet temperature 1,400C (2,552F)

Table 10.3 shows the main operation parameters. Fuel flow in engines of the
1990s has been approximately 2.5-2.6 kg s -1 (5.5-5.7 lb) [ 22 ]. The ratio of fuel
flow in jet engines has been continuously decreasing in the last years. Modern
engines consume less than 2.0 kg s -1 (4.4 lb s -1 ) of fuel. The TSFC attaches ranges
from approximately 17.1 g (kN s) -1 , i.e., 0.605 lb (lbf h) -1 to 8.696 g (kN s) -1 ,

i.e., 0.307 lb (lbf h) -1 .