Referat Turbofan Engine

In meinem Englisch-Referat Turbofan Engines bin ich noch auf ein paar

Fehler gesto?en!!

Darum schicke ich die verbesserte Version: The Turbofan Engine

Dear Professor and classmates.

My presentation today treats the Turbofan Engine. In the course of my presentation, I'll use some abbreviations, which you can find on the blackboard. My presentation is structured in six parts:

1. General design

2. The fan

3. The compressor

4. The burner

5. The Turbine

6. Increase in performance

1. General Design:

Generally, there are two types of Turbofan Engines:

* Dual-spool turbofans: Here, the LPC and LPT are situated on the one spool and the HPC, the HPT and the fan with an reduction gear on the other spool

* Triple-spool turbofans: Here the fan s got an own spool with a LPC.

A typical Turbofan Engine is the Trent 0 from Rolls-Royce. I will describe this topic by means of this Engine.

A Turbofan Engine consists of the following main parts:

2. The fan:

The fan with a diameter of ' is actually half compressor - half propeller. It is responsible for the high efficiency of this engine type at high subsonic speeds, because it pushes most of the intaken air around the other components. The relation of the air that goes around the engine and the air that goes through the engine is called bypass ratio.

In this case it's 92 to

3. The compressor:

Most Turbofan Engines use axial flow compressors, because of their axial direction of airflow, which causes only small losses. But there is also a disadvantage: the high complexity of the compressor construction, which you can see on the foil.

A compressor stage consists of a single row of fixed compressor blades, the

stator, and rotating compressor blades, the rotor. The stator case is made of stainless steel, Titan or cast magnesium and is divided into two halves. The rotor is the most complicated part of the compressor. It has to

transmit a power of several thousand hp. The rotor consists of a number of disks, which are attached to a cylinder. These disks hold the compressor blades made of forged Titan.

The design of the blades is close to the design of an aircraft wing. The only difference is the blade twist. The twist enables a constant

axial-velocity over bladeheight.

The Trent 0 has a eight stage low pressure compressor with variable geometry. That means the angle of attack of the stator blades can be adjusted to allow an optimal airflow. The high-pressure compressor has six stages and a maximal rotation speed of 5 3 rpm.

4. The burner:

In the burner fine atomized propellant is mixed to the highly-compressed air and then burnt. The problem is that the air comes with about 50 m/s from the HPC. But the combustion process requires a speed of only a few meters per second, because when the air velocity is too high the flame will be blown out. So the first part of the burner is a swirl vane combined with a diffuser, the so-called primary zone. In the primary zone 0 - % of the incoming air is mixed with the fuel. The rest of the air is led into the

air casing to cool the chamber, otherwise the material would melt, because of temperatures up to 0 0 C.

The burners can be divided into three groups: Can-Type Burner:

This one is the oldest type of burner. The combustion chambers are placed around the engine axis. The disadvantage of this design is the bad airflow characteristic.

Annular-Type-Burner:

A very effective space-utilisation enable annular-type-burners, because there is only one combustion chamber, which is located concentrically around the engine axis.

The advantage of this kind of construction is the lower fuel consumption up

to -2 %.

Can-Annular-Type-Burner:

This most common burner is a combination of the two previous burner-types. The secondary air supply occurs from a common air casing, while the primary air flows in through mouthpieces.

5. The Turbine

The task of the turbine is to provide the power to drive the compressors, the fan and the accessories, like the oil pump or the lubrication system.

The turbine is actually a turned-around compressor, so it withdraws the hot gas-stream energy.

As in the case of the compressor, there are two types of turbine designs, the high-pressure turbine and the low-pressure turbine. Because of the enormous heat stress, the turbine and stator blades have to be cooled. The cooling air comes from the cold by-pass-stream. The cooling-air main leads through the blades and enters it at the hub and exits at the tip. The

material the blade is made of in the most cases is the alloy NIMONIC 15

with the following components: Ni 7 9 , Co 1 %, Cr 1 %, Al 5%, Ti %, Mo

5%, C 1 %, Zr 0 4%, B 1 %.

But there are also other materials such as Udimet , B1900, Iconel 3 or

Waspaloy.

6. Increase in performance

There are two techniques to increase the performance of an engine. The first, the afterburner, is only used at military turbojet engines, because

of the enormous fuel consumption.

The most suitable solution for civil applications is the water injection. A water-methanol mixture is injected into the airflow to reduce its temperature by vaporizing, because the lower the temperature, the higher the density and the mass-flow. And high mass-flow means high thrust.

I hope you've enjoyed my report and thank you for paying attention.