Question
In: Mechanical Engineering
What is the typical thurest for small jet engine ?
What is the typical thurest for small jet engine ?
Solutions
samet mamat answered 2 years agoRelated Solutions
Is the thrust generated typical of a small jet aircraft engine? I got -99 N explain...
Is the thrust generated typical of a small jet aircraft
engine?
I got -99 N
explain and give me a source
Is the thrust generated typical of a small jet aircraft engine? I got -99 N explain...
Is the thrust generated typical of a small jet aircraft engine?
I got -99 N explain and give me a source
a. If the intensity of sound from a jet engine is 10 W/m 2 at a...
a. If the intensity of sound from a jet engine is 10 W/m 2 at a
distance of 30 m, how far away from the jet do you have to be for
the intensity to be 0.1 W/m 2 ?
b. Suppose that you hear a clap of thunder 5 s after seeing the
lightning stroke. If the speed of sound in the air is 343 m/s and
the speed of light in air is 3 × 10 8 m/s,...
Imagine a diverging channel in place of the jet engine. Air enters the channel supersonically and...
Imagine a diverging channel in place of the jet engine. Air
enters the channel supersonically and accelerates further in the
diverging geometry. The exit velocity is an even faster jet which
would provide thrust to the aircraft. In this design no energy is
required in the form of combustion. Would this design work? If yes,
why, and if not, why not? Use equations to explain your physics
based arguments. You can use a quantitative example to make your
point.
A jet propulsion engine has an air that enter the compressor at 100 kPa and 290K....
A jet propulsion engine has an air that enter the compressor at
100 kPa and 290K. The pressure ratio across the compressor is 14
and the turbine inlet temperature is 1500K. When the air leaves the
turbine, it enters the nozzle and expands to 100kPa. Determine the
pressure at the nozzle inlet and the velocity of the air leaving
the nozzle
Important notes: Please be neat and write legibly, it’s
important that I understand your writing and follow your thoughts....
In your first assignment as a new engineer at a large jet engine manufacturer, you are...
In your first assignment as a new engineer at a large jet engine
manufacturer, you are part of a team investigating a new generation
of lightweight turbine engines for regional jet liners. In order to
increase efficiencies and improve performance, lightweight
materials with significant toughness are needed. However, the
operating conditions include high temperatures and high stresses.
Of the three categories of composites, which one would you select
for further investigation in an engine inlet application where
temperatures in the...
A jet engine flies at 205 m/s at an altitude where the pressure is 0.466atm and...
A jet engine flies at 205 m/s at an altitude where the
pressure is 0.466atm and the temp is 249K. The pressure recovery
factor across the intake is 1.0 and the compressor pressure ratio
is 30. Assume isentropic turbomachinery.
A) determine flight mach number
B) determine stagnation pressure and temp at the inlet of the
intake
C) determine the stagnation pressure and temp after the
compeessor
D) determine the stagnation temp change across the turbine
drivibg the compressor
Air passes through a jet engine nozzle operating at steady state. The flow at the nozzle...
Air passes through a jet engine nozzle operating at steady
state. The flow at the nozzle inlet has a temperature of 900° F.
The nozzle inlet has an area of 5 ft2. The flow at the nozzle
outlet has a temperature of 875° F, a specific volume of 90 ft3/lb,
and a velocity of 600 ft/s. The nozzle outlet has an area of 2 ft2.
Model the air as an ideal gas with constant specific heats.
Evaluate the specific heats...
The air mass flow rate of a jet engine is 10 kg/s. The stagnation enthalpy at...
The air mass flow rate of a jet engine is 10 kg/s. The
stagnation enthalpy at the exit of the turbine is 918 kJ/kg and the
excess air is 4.5.
(a) What should be the mass flow rate of fuel injected in the
afterburner, such that the stagnation enthalpy at the end of the
afterburner is 1700 kJ/kg?
(b) What is the excess air in the afterburner?
(c) What is the maximum temperature in the afterburner?
thermo II question A jet engine does not produce shaftwork; how is power produced?
thermo II question
A jet engine does not produce shaftwork; how is power
produced?
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