1. AE 1350
Lecture Notes #13

2. Topics to be discussed Propellers Gas Turbines Rockets Turbojet
Turboprop
Turbofan
Rockets

3. How does a propeller work?
It captures a stream of air molecules, adds energy to the particles.
Particles approach the propeller with low velocity.
They leave with higher velocity, and energy.
This change in momentum of the particles is caused by the
rearward force exerted by the propeller on the particles.
There is an equal and opposite reaction - the particles exert a forward
force on the blades. This is called thrust.

4. As the propeller turns.. V V+v V+2v
Streamlines contract as they approach the propeller.
Velocity of the particles steadily increases.

5. Thrust Generated V V+v V+2v
Mass flow rate = r A (V +v) where A is the propeller disk area.
Momentum flow rate = mass flow rate times velocity
Thrust = Rate at which Momentum flows out-
Rate at which momentum flows in
= rA(V +v) (V +2v) - rA (V +v) V = 2rA(V +v)v
Thrust is increased if the disk area A is large, and/or if the
excess velocity v is large.

6. Power Consumed V V+v V+2v
Mass flow rate = r A (V+v) where A is the propeller disk area.
Energy flow rate = 1/2 times (mass flow rate) times (velocity squared)
Rate at which energy is added to the fluid =
Rate at which energy flows out- Rate at which momentum flows in
= 1/2rA(V+v) (V +2v)2 - 1/2 rA (V +v) V2
= 2 rA(V + v)2 v = T(V +v)
Notice that power consumed will be high for a given thrust T and
forward velocity V, if v is high.

7. Propeller Thrust vs. Power Consumed
T = 2r A (V +v)v
P = T(V +v) = TV + Tv
The first term TV is useful work done by the propeller to
overcome drag.
The second term, Tv, called induced power, represents excess
energy we dump into the wake, as the propeller accelerates the
flow a higher velocity.
To keep the power minimum, this excess energy must be kept small.
Propulsive efficiency = Useful Power/Total Power
= TV /(TV +Tv) = V /(V +v)
where T = 2rA(V +v)v
Thumb Rule the propeller designer:
Keep disk area A as large as possible, v as small as possible.

8. There is a limit to the Disk Area
If we make the disk area too large, the blade radius and diameter will be high.
Tip will spin at too high a speed.
If cruise speed is also high, shocks will form on the blades.
Additional power will be needed to overcome the drag on the blades caused by the shock waves.
Noise will also go up.
These factors have limited the use of propellers to aircraft that have relatively lower thrust requirements or low subsonic cruise speeds (Mach 0.6 or less).

9. How is the propeller or fan turned?
With a
piston engine (as in a car) or a
gas turbine engine

10. Radial Piston Engines
These engines now belong in a museum...

11. Gas Turbine Engines - Turbofan
The fan acts like a propeller, provides the majority of thrust.

12. Turbine Engines How They Work
Turbine engines have four major sections:
Gearbox — uses shaft power to turn a generator and other accessories.
Compressor — draws in outside air and increases the pressure of the air.
Combustor — mixes fuel with the air. This mixture is ignited and directed to the turbine section.
Turbine — extracts energy from the heated air to turn the fan, compressor, and gearbox via the common shaft and produces direct thrust through the exhaust nozzle.

13. Low Bypass Ratio Turbofan
JT8D Characteristics Fan tip diameter: 54.0 inches Length, flange to flange: inches Takeoff thrust: 21,000 pounds of thrust Bypass ratio: 1.74-to-1 Overall pressure ratio: 18.2 to Fan pressure ratio: 1.91
Engine Models JT8D-standard JT8D-217/219
Planes Powered by JT8D Boeing Boeing / McDonnell Douglas DC-9 Boeing MD-80

14. High Bypass Ratio Turbofan
Fan tip diameter: 112 inches Length, flange to flange: inches Takeoff thrust: 86, ,000 pounds
Bypass ratio: 5.8-to-1 to 6.4-to-1 Overall pressure ratio: Fan pressure ratio:
Engine Models PW PW PW Planes Powered by PW Boeing /-300

15. Turbojet Engines The fan produces very little thrust.
Remember from the propeller theory that thrust depends on disk area.
Most of the thrust is produced by the jet coming out of the nozzle.
Assuming that the jet exits the nozzle at ambient pressure,
T = Mass Flow Rate times change in velocity
= Mass flow rate times (Exit Velocity - Inlet Velocity)
Turbojets dump a lot of excess energy into the exhaust and are inefficient.

16. Turboshaft Engines
The engine core operates in the same manner as in turbojet or turbofan engines.
Turbines turn the engine shaft.
The power from the engine
shaft may be used to spin
a propeller (turboprop),
or a rotor (helicopter),
or a power generator
Gear Box
Propeller or
Rotor
Core

17. Supersonic Combustion Ram Jet SCRAMJET Engines
In this engine, compressors are not used.
Shock waves in front of the aircraft and inside the inlet
slow down the flow and increase the pressure.
The flow inside the entire engine, including the compressor,
is supersonic.
An aerospace plane will use a SCRAMJET engine.

18. Jet Engines and Piston Engines Need Air...
Jet engine and piston engine aircraft carry only the fuel.
They need air (or oxidizer) for combustion of the fuel and generation of energy.
For this reason, these are called air-breathing engines.
These devices stop working outside the atmosphere.
In our next lecture, we will study rocket engines.

19. Solid and Liquid Fuel Rocket Motors

20. Liquid Fuel Rocket Motor http://www. execpc. com/~culp/space/propulsn
Uses separate liquid fuel and oxidizer, which are combined only at the moment of combustion.
Pumps are required to get the fuel & oxidizer to the motor quickly enough to develop desired thrust.
This makes liquid fuel rockets more complicated.
Liquid fuel rockets can be turned off and then turned on again.
On the space shuttle, they can be throttled for more or less thrust.
So liquid fuel rockets are more controllable.

21. Rocket Motor Thrust Thrust = (Mass Flow Rate) * Vjet
+ (pexit - p) Aexit

22. Impulse Thrust varies with time.
Rockets are instead rated according to their impulse:
The above integral is done over the time period when the rocket
starts firing and when it stops.