Thrust specific fuel consumption

Thrust specific fuel consumption (TSFC) is an engineering term that is used to describe the fuel efficiency of an engine design with respect to thrust output. TSFC may also be thought of as fuel consumption (grams/second) per unit of thrust (kilonewtons, or kN). It is thus thrust-specific, meaning that the fuel consumption is divided by the thrust.

TSFC or SFC for thrust engines (e.g. turbojets, turbofans, ramjets, rocket engines, etc.) is the mass of fuel needed to provide the net thrust for a given period e.g. lb/(h·lbf) (pounds of fuel per hour-pound of thrust) or g/(s·kN) (grams of fuel per second-kilonewton). Mass of fuel is used rather than volume (gallons or litres) for the fuel measure since it is independent of temperature.[1]

Specific fuel consumption of air-breathing jet engines at their maximum efficiency varies more or less inversely with speed, which means that the fuel consumption per mile or per km can be a more appropriate comparison for aircraft that travel at very different speeds.

This figure is inversely proportional to specific impulse.

Significance of SFC

SFC is dependent on engine design, but differences in the SFC between different engines using the same underlying technology tend to be quite small. Increasing overall pressure ratio on jet engines tends to decrease SFC.

In practical applications, other factors are usually highly significant in determining the fuel efficiency of a particular engine design in that particular application. For instance, in aircraft, turbine (jet and turboprop) engines are typically much smaller and lighter than equivalently powerful piston engine designs, both properties reducing the levels of drag on the plane and reducing the amount of power needed to move the aircraft. Therefore, turbines are more efficient for aircraft propulsion than might be indicated by a simplistic look at the table below.

SFC varies with throttle setting, altitude and climate. For jet engines, flight speed also has a significant effect upon SFC; SFC is roughly proportional to air speed (actually exhaust velocity), but speed along the ground is also proportional to air speed. Since work done is force times distance, mechanical power is force times speed. Thus, although the nominal SFC is a useful measure of fuel efficiency, it should be divided by speed to get a way to compare engines that fly at different speeds.

For example, Concorde cruised at Mach 2.05 with its engines giving an SFC of 1.195 lb/(lbf·h) (see below); this is equivalent to an SFC of 0.51 lb/(lbf·h) for an aircraft flying at Mach 0.85, which would be better than even modern engines; the Olympus 593 was the world's most efficient jet engine.[2][3] However, Concorde ultimately has a heavier airframe and, due to being supersonic, is less aerodynamically efficient, i.e., the lift to drag ratio is far lower. In general the total fuel burn of a complete aircraft is of far more importance to the customer.

Units

Specific Impulse (by weight)
 Specific Impulse (by mass)
 Effective exhaust velocity
 Specific Fuel Consumption
SI =X seconds =9.8066 X N·s/kg =9.8066 X m/s =101,972 (1/X) g/(kN·s) / {g/(kN·s)=s/m}
Imperial units =X seconds =X lbf·s/lb =32.16 X ft/s =3,600 (1/X) lb/(lbf·h)

Typical values of SFC for thrust engines

Specific fuel consumption (SFC), specific impulse, and effective exhaust velocity numbers for various rocket and jet engines.
Engine type Scenario SFC in lb/(lbf·h) SFC in g/(kN·s) Specific impulse (s) Effective exhaust velocity (m/s)
NK-33 rocket engine Vacuum 10.9 308 331[4] 3250
SSME rocket engine Space shuttle vacuum 7.95 225 453[5] 4440
Ramjet Mach 1 4.5 130 800 7800
J-58 turbojet SR-71 at Mach 3.2 (Wet) 1.9[6] 54 1900 19000
Eurojet EJ200 Reheat 1.66–1.73 47–49[7] 2080–2170 20400–21300
Rolls-Royce/Snecma Olympus 593 turbojet Concorde Mach 2 cruise (Dry) 1.195[8] 33.8 3010 29500
Eurojet EJ200 Dry 0.74–0.81 21-23[7] 4400–4900 44000–48000
CF6-80C2B1F turbofan Boeing 747-400 cruise 0.605[8] 17.1 5950 58400
General Electric CF6 turbofan Sea level 0.307[8] 8.7 11700 115000
typical subsonic cruise, 80% throttle, min SFC[9]
Turbofan efficiency
GE90 36.1%
PW4000 34.8%
PW2037 35.1% (M.87 40K)
PW2037 33.5% (M.80 35K)
CFM56-2 30.5%
TFE731-2 23.4%

See also

References

  1. ↑ Specific Fuel Consumption
  2. ↑ Supersonic Dream
  3. ↑ "The turbofan engine", page 5. SRM University, Department of aerospace engineering
  4. ↑ "NK33". Encyclopedia Astronautica.
  5. ↑ "SSME". Encyclopedia Astronautica.
  6. ↑ Nathan Meier (21 Mar 2005). "Military Turbojet/Turbofan Specifications".
  7. 1 2 "EJ200 turbofan engine" (PDF). MTU Aero Engines. April 2016.
  8. 1 2 3 Ilan Kroo. "Data on Large Turbofan Engines". Aircraft Design: Synthesis and Analysis. Stanford University.
  9. ↑ Ilan Kroo. "Specific Fuel Consumption and Overall Efficiency". Aircraft Design: Synthesis and Analysis. Stanford University.
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