M15c2

15問 • 9ヶ月前

ユーザ名非公開

通報

問題一覧

Newton’s 2nd law used to

calculate the amount of thrust produced by the engine

Thrust can be increased by increasing

air mass flown to engine or gases acceleration through the engine.

Thrust in a gas turbine engine is produced by

Compressor (increase air pressure) and Combustor (increase gases acceleration)

The output of the engine when the aircraft in flight is called

net thrust

ESHP

SHP + Jet Thrust. Addition of SHP to jet thrust. 1hp=745.7

Propulsive efficiency

is the ability of engine to drive the aircraft in flight

The specific fuel consumption

thrust produced per pound of fuel consumed

At 400 knots

Ram effect increase

thrust increase with small increase in RPM

at higher engine speeds

As altitude increase air pressure (density) & temperature

decrease

Aircraft altitude & ambient temperature

affect the inlet air density

Gas turbine engine efficiency increases at altitude

due to drag decrease.

As temperature increase air density decrease

which negatively effect engine thrust and vice versa

Lower temperature gives

greater mass flow and greater thrust

The highest air pressure at

compressor outlet

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問題一覧

Newton’s 2nd law used to

calculate the amount of thrust produced by the engine

Thrust can be increased by increasing

air mass flown to engine or gases acceleration through the engine.

Thrust in a gas turbine engine is produced by

Compressor (increase air pressure) and Combustor (increase gases acceleration)

The output of the engine when the aircraft in flight is called

net thrust

ESHP

SHP + Jet Thrust. Addition of SHP to jet thrust. 1hp=745.7

Propulsive efficiency

is the ability of engine to drive the aircraft in flight

The specific fuel consumption

thrust produced per pound of fuel consumed

At 400 knots

Ram effect increase

thrust increase with small increase in RPM

at higher engine speeds

As altitude increase air pressure (density) & temperature

decrease

Aircraft altitude & ambient temperature

affect the inlet air density

Gas turbine engine efficiency increases at altitude

due to drag decrease.

As temperature increase air density decrease

which negatively effect engine thrust and vice versa

Lower temperature gives

greater mass flow and greater thrust

The highest air pressure at

compressor outlet