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2011-02-08 19:48:05
2011-02-08 19:48:05

The Boeing 767-300ER is powered by two (2) General Electric CF6-80C2B2 Gas Turbofan Jet Engines.

The Boeing 767-300ER may also be powered by two (2) Pratt & Whitney PW4000 Turbofan Jet Engine Powerplants as well.

But this answer will ONLY focus on the General Electric CF6-80C2B2 Gas Turbofan Jet Engine applicable to the Boeing 767-300ER airliner.

Here are the technical specifications per GE CF6-80C2B2 Gas Turbofan Jet Engine:

Maximum Static Thrust (Fg) = 51,590 Lbs

Maximum Mass Airflow (Ms) = 1,650 Lbs/Sec

Fan Bypass Ratio (FBR) = 5.31:1

Compressor Pressure Ratio (PR): 23:1

Compressor Efficiency (CE) = 75%

There are two (2) different types of horsepower involved in Gas Turbine Jet Engines.

1.) Compressor Shaft Horsepower. This is the horsepower required to keep the

compressor running on a gas turbine engine. The compressor sucks in air,

compresses it to extremely high pressure, sends it to a combustion chamber(s)

where it is mixed with kerosene jet fuel and ignited. The high velocity hot gases

which exit the combustion chamber power a turbine(s) which is/are connected to

the compressor by a shaft and in turn drive the compressor to keep the engine


2.) Thrust Horsepower. This is the overall horsepower of the aircraft while in

flight consolidated with the net thrust rating of the turbine jet engines. Maximum

static thrust is maximum thrust output while the aircraft and engine are held at rest

and not permitted to move. Net thrust is the actual thrust used to move the

aircraft which is the difference in exhaust jet velocity and forward aircraft speed

times the mass airflow ingested into the engine, divided by gravitational

acceleration. Net thrust is much lower than the static thrust rating of the engine.

Total thrust horsepower is the aircraft flight speed divided into 375 then multiplied

times total net thrust. Thrust horsepower does not exist if the engine and aircraft

are not moving regardless to the power output or throttle setting of the engine(s).

I will answer your question with two individual scenarios:

Scenario #1:

The first one will involve one CF6 Gas Turbofan Jet Engine held at rest on a jet engine stand in 60 degree F outside air temperature, not permitted to move while operated at Maximum Static Thrust power setting. In this scenario only Compressor Shaft Horsepower can be calculated. The Thrust Horsepower is ZERO since the engine is not moving in forward motion.

Scenario #2:

The second one will involve two (2) CF6 Turbofan Jet Engines while flying at 240 MPH on the Boeing 767-200ER airliner at maximum power right after the airliner goes airborne and gets off the ground, while flying in 45 degree F outside air temperature. In this scenario, both the Compressor Shaft Horsepower and Thrust Horsepower can be calculated.

This Wiki Answer is going to be many pages long if I explain every little detail from here on, so I will just work out the calculations and produce the correct answers to these two individual scenarios:

For Scenario #1:

CDT (F) = [((((23^0.263) + (-1)) x (460 + 60))] / (0.75)) + (460 +60)] - [460] = 948.2 F

Tr = 948.2 F - 60 F = 888.2 F

Comp Ms = [(1) / (5.31)] x [1,650] = 310.73

Comp HP = [(888.2 x 0.24 x 310.73 x 778) / (550)] = 93,696.23 HP

The engine will develop 93,696.23 Compressor Shaft Horsepower.

For Scenario #2:

CDT (F) = [((((23^0.263) + (-1)) x (460 + 45))] / (0.75)) + (460 +45)] - [460] = 907.57 F

Tr = 907.57 F - 45 F = 862.57 F

Comp Ms = [(1) / (5.31)] x [1,650] = 310.73

Comp HP = [(862.57 x 0.24 x 310.73 x 778) / (550)] = 90,992.52 HP

V1 = [(240) x (22 / 15)] = 352 fps

V2 = [(51,590 x 32.2) / (1,650)] = 1,006.8 fps Avg. Core & Fan Exhaust Nozzles

NT = [((1,650) x (1,006.8 - 352)) / (32.2)] = 33,553.42 Lbt

TNT = [(33,553.42 x 2)] = 67,106.84 Lbt

THP = [(67,106.84) x (240 / 375)] = 42,948.38 HP

90,992.52 Compressor Shaft Horsepower will develop per engine.

42,948.38 Total Thrust Horsepower will develop amongst both engines.

---------------------End Wiki Answer----------------------


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