Claims: I Claim:
1.A specially designed cost effective aircraft engine 100, that increases the performance of conventional jet engines with increased efficiency, by adding a new technology called Drag Torque Turbine.
2.The system as claimed in claim 1 has Drag Torque turbines 103 and 106 that replaces the conventional turbines in the conventional jet engines.
3.The system as claimed in claim 1, has a low pressure compressor 102 and high pressure compressor 105, with inlets as 104 and 107, that helps to increase the compression ratio of 100.
4.The system as claimed in claim 1 has a shaft 110 that is connected to Fan 101, Compressors 102, 105 and Drag Torque Turbines 103, 106 that helps in air intake by rotating the Fan 101.
5.The system as claimed in claim 1 has a diffuser 108 to input the high pressure high velocity air in to the combustion chamber in a steady manner for effective combustion.
6.The system as claimed in claim 1 has a combustion chamber 109, to perform combustion.
7.The system as claimed in claim 1 has a nozzle 111 at the rear end to push out the combust air of high temperature and pressure.
8.The system as claimed in claim 1 is a cost efficient or less complex system as it has no conventional turbines.
9.The system as claimed in claim 1 generates high pressure and temperature inside.
10.The system as claimed in claim 1 reduces the engine size. , Description:DESCRIPTION
CROSS-REFERENCE TO RELATED APPLICATIONS AND PRIORITY
The present application does not claim priority from any other patent application.
TECHNICAL FIELD OF INVENTION
This invention relates to a specially designed cost effective aircraft engine that increases the performance of conventional jet engines by adding a new technology called Drag Torque Turbine.
BACKGROUND OF INVENTION
There are no limits for human enthusiasm to conquer the sky and sky was not the limit for humans. Right from Wright brothers, the inventors of first airplane, researches and experiments and trials in the field of airplanes are going on to invade time and to reach the faraway destinations.
Aircrafts with Jet Engine was such an invention to fly at higher speeds. Jet engine is a machine that works on a pushing force called thrust. A Jet Engine normally comprise of an Inlet, Compressor, Diffuser, Combustion Chamber, Turbine, shaft and an outlet.
Air is taken through the inlet and is then compressed, it is then mixed with the fuel and is burned by a spark in the combustion chamber, the gas thus formed as expanded is then released through the outlet which in turn gives a forward thrust.It is this high temperature expanded air that creates the thrust for the aircraft movement.As the expanded gases is formed it is passed through the turbine, a fan like structure, which rotates the shaft and the shaft rotates the compressor leading for fresh air to come in through the inlet and the process continues to generate the motion for the AirCrafts.
The main part of a Jet Engine is the turbine and it is a fan like structure with blades, shaft or axle and some sort of machine. Normally the turbine works as a windmill that scoops up the energy from the heated air from the combustion chamber and converts it in to kinetic energy to rotate the shaft to get more air intake.
To get the said work done by turbine we have to spend a lot of money on the same. Not only the money, the turbine blade construction also is challenging. The turbine section should be constructed in such a way as to withstand the high temperature generated there in the turbine section. If the turbine cant withstand this high temperature, which is formed as a result of air combustion inside the combustion chamber, the whole system may fail. So in conventional engines the turbine blades or turbine sections are made using special super alloys with very high melting point to withstand this high temperature. If the temperature increases beyond the melting point of those alloys the entire system may collapse.So special care should be taken to limit the temperature with in the melting point of these alloys.
Recently studies are going on to come out with various alloy mixtures with greater melting points to cope up very high temperature inside the jet engines especially in the turbines, as the efficiency or speed of jet engines have direct relation to the temperature develops in the turbine section as a result of air combustion from the combustion chamber.
The thought of generating high temperature and there by more thrust and efficiency for the Aircraft engines, without much complex construction, led to the invention of a cost effective aircraft engine that increases the performance of conventional jet engines by adding a new technology called Drag Torque Turbine.
INTENTION OF THE INVENTION
When an aircraft is considered, the thrust that causes the movement of aircraft is generated by the Engine, the power plant for an aircraft. This thrust could only be generated if the engine works well. In most of the cases the engine fails to generate that thrust or fails to work properly due to the damages in the turbines inside the engine.This turbine damages happens mainly when the turbine fans or associated parts couldn’t withstand the high temperature generated in this region.
To make the turbine withstand this temperature, generally these turbines are made of special alloys or are designed particularly to withstand a particular limited temperature lower than that it can actually withstand and it is time consuming and is not cost efficient.
Further in conventional engines the thrust generated is not the total outcome of the system. That means a small part of the combust air is used to rotate the turbine and there to rotate the shaft so as to get fresh air in to the compressor. And the structure itself is bulky.
Hence the intention of this invention is to design a cost effective aircraft engine that can withstand high temperature ranges to increase the performance or efficiency of conventional jet engines by adding a new technology called Drag Torque Turbine.
FOCUS AND OBJECTIVE OF THE INVENTION
Aircrafts are one of the prestigious inventions of the 20th century. If there were no such invention, human kind may take weeks to travel across a country and months to reach transatlantic and transpacific nations, were it actually would have taken minutes to travel by Aircrafts.
So Aircrafts are very interesting invention of mankind to invade time. Always humans think of getting their destinations as soon as possible and hence the speed of Aircrafts plays an important role.
Researches and experiments are going on to increase the speed of the aircrafts so that people can travel from one place to another in less time.
The main defect that was identified was, the failure of engines when the temperature, that causes the required thrust for the aircraft movement, increases beyond a limit.
So there is the need of such an innovation that can prevent engine failures when temperature inside engines are increased to a higher level.
The thought of achieving greater speed with increased efficiency and improved fuel consumption, possibly by reducing the engine size so as to carry along much more passengers, than it actually can, was the primary focus of the invention.
The other important objectives of the invention are:
A.To design a less complex aircraft engine when compared to the conventional aircraft engines.
B.To develop a cost effective aircraft engine that increases the performance when compared to the conventional aircraft engine.
C.To build higher pressure inside the engine as compared to normal engines.
D.To design an engine with higher compression ratio.
E.A system that increase Rotations per minute(rpm) as the pressure increases.
F.To design an aircraft engine that generates high temperature due to the combustion of highly compressed air.
G.To make high expansion force from the chamber after combustion of highly compressed air in the combustion chamber.
H.A new form of aircraft engine design that replaces conventional turbine by drag torque turbine or D-T Turbine.
I.A system that uses boundary layer effect to build high pressure inside and there by higher expansion force.
SUMMARY OF INVENTION
The invention can be summarized as a specially designed cost effective aircraft engine that increases the performance of conventional jet engines by adding a new technology called Drag Torque Turbine.
The new engine design includes Fan, Low pressure Compressor, Low Pressure Drag Torque Turbine(DT Turbine), High Pressure Compressor, High Pressure Drag Torque Turbine (DT Turbine), Diffuser, Combustion Chamber and Nozzle.
The DT Turbines are a set of discs, with holes, serially arranged on a rotor shaft inside a casing with disc spacer in between the discs. The casing of the disc sets are connected to an air connection with a nozzle attached for the intake of air, and an exhaust end cap, with holes, attached on the other side for the exit of the intake air, after passing through the discs.
The holes of the disc and exhaust end cap are important to build the maximum pressure inside the DT Turbine. There will be pressure variations as per the no.of holes or diameter of holes in the discs and exhaust end cap.
Inside the engine the low pressure and high pressure compressors and the Drag Torque turbine are arranged in the form of a sandwich that is the first DT turbine is placed in between the low pressure and high pressure compressors and the second DT turbine is placed in the aft position (rearmost part of engine) of the high pressure compressor, the compressors are connected with the DT turbines, that is the low pressure compressor is connected with the first DT turbine and the high pressure compressor is connected with the second DT turbine so that the parts are connected to each other.The engine has no moving parts in the aft position of the combustion chamber.
Initially the engine is started with the help of an auxiliary power unit (APU).When the APU starts rotate, the compressor starts rotating and the air is compressed in the low pressure compressor and this compressed air is go to the first DT turbine nozzle in a tangential way. The velocity of that air tends to make a circulation inside the discs of the DT turbine so a shear force makes the rotor shaft to rotate. The pressure increases inside the DT turbine and the exhaust gas is exit from the DT turbine in an axial way, after that the gas is again compressed in the high pressure compressor and the compressed gas is again passed through the second DT turbine. The compressed gas is then ignited with fuel inside the combustion chamber (CC). In the DT jet engine there is no conventional turbine as in the conventional engine and hence no need to worry about the engine failures due to the high temperature develops in the rear part of the conventional engines where the turbines are usually placed.
Further there are no separate cooling systems inside the new engine design. The bypass air through the Fan is used as the cooling system for this particular design.Thus can achieve a high efficient, improved fuel consuming engine with a reduced size as compared to the conventional aircraft engines.
DESCRIPTION OF INVENTION
The particular invention is meant for designing a cost effective aircraft engine that increases the performance of conventional jet engines by adding a new technology called Drag Torque Turbine.
The system includes Fan, Low pressure Compressor, Low Pressure Drag Torque Turbine(DT Turbine), High Pressure Compressor, High Pressure Drag Torque Turbine (DT Turbine), Diffuser, Combustion Chamber and Nozzle.
The low pressure and high pressure compressors and the Drag Torque turbine are arranged in the form of a sandwich that is the first DT turbine is placed in between the low pressure and high pressure compressors and the second DT turbine is placed in the aft position (rearmost part of engine) of the high pressure compressor, the compressors are connected with the DT turbines, that is the low pressure compressor is connected with the first DT turbine and the high pressure compressor is connected with the second DT turbine so that the parts are connected to each other.
The size of the Low pressure region (low pressure compressor and low pressure DT Turbine) is bigger compared to the High Pressure region (High pressure Compressor and High Pressure DT Turbine) to maximize the compression of inputted air and so as to get maximum compression ratio.
Further there is a shaft connecting the Fan, low pressure compressor, low pressure DT Turbine and High Pressure Compressor and High Pressure DT Turbine.
In the aft position of the combustion chamber there are no moving parts. The conventional Turbine in the conventional engine are completely removed in this new design.
To start the engine working, Initially an auxiliary power unit (APU) is used. When APU is initiated the Fan is rotated to input fresh air in to the system. The inputted Fresh air is compressed inside the low pressure compressor and the compressed air is moved to the low pressure DT Turbine through the low pressure DT Turbine’s nozzle in a tangential way.
The DT Turbines are a set of discs, with holes, serially arranged on a rotor shaft inside a casing with disc spacer in between the discs. The casing of the disc sets are connected to an air connection with a nozzle attached for the intake of air, and an exhaust end cap, with holes, attached on the other side for the exit of the intake air, after passing through the discs.
The holes of the disc and exhaust end cap are important to build the maximum pressure inside the DT Turbine. There will be pressure variations as per the no.of holes or diameter of holes in the discs and exhaust end cap.
Inside the Low Pressure DT Turbine, when the air from the low pressure compressor is inputted tangentially, the velocity of the air increases. This velocity is converted to kinetic energy in the disc and creates a circulatory vortex that will generate a shear force making the discs to rotate.The discs are arranged on a rotor shaft. The shaft is also rotated when the discs are rotated. The output of the low pressure DT turbine is then forwarded to the High Pressure Compressor.
The power output of the DT Turbine mainly depends on the no.of discs inside, spacing between the discs and the velocity of the inlet fluid.
By increasing the no of discs we can increase the pressure build inside and can achieve thrust equivalent to or more than that of the conventional jet engines.
At the High Pressure Compressor the air input is the compressed air from the Low pressure region. The high Pressure region, the high pressure compressor and high pressure DT Turbines, is of lesser size compared to the low pressure region. And hence when the outputted air from the low pressure region enters the high compression region there will be no pressure drop as the size of components plays major role in pressure generation.
The pressurized air is then again compressed in the high pressure compressor and is tangentially inputted in to the high pressure DT Turbine. The process repeats in the high pressure DT Turbine as in the low pressure DT Turbine.
The highly compressed air from the High Pressure DT Turbine is then inputted to the combustion chamber. There this high pressure air is mixed with fuel and is ignited. When combustion happens, as the air inside the combustion chamber is of high pressure, there will be high expansion force inside the combustion chamber leading to high temperature and there by higher force.
The combust air is then pushed out through the nozzle at the rear end causing the forward movement of the aircraft.
As the Fan, compressors and DT Turbines are connected to a shaft, and as the shaft rotates as a result of the rotation of the discs in the DT Turbine, the fan is also rotated and fresh air is inputted for the next compression - combustion cycle to generate continuous thrust.
By the sandwich arrangement of the compressor and DT Turbine it is possible to increase the shaft work from the DT turbine and there by the pressure generated inside and compression ratio can be increased leading to higher RPM( rotations per minute).
As the RPM increases compression ratio and combustion efficiency increases and hence great power is generated using less amount of fuel.
At the rear end of this particular design there are no moving parts and hence there is no loss in the generated thrust in any means. Further in this particular design the conventional turbine in the conventional jet engine is removed completely. And hence chances of engine failure as a result of turbine failure, due to the heavy temperature generated there in the turbine, can be avoided and can achieve higher efficiency compared to the conventional jet engines.The size of the engine is also reduced as the turbine system in the conventional aircraft engines are removed in this new design.
BRIEF DESCRIPTION OF THE ACCOMPANYING DRAWINGS
The invention can now be described with the help of accompanying drawings.
Figure 1 illustrates the engine design 100 with main parts as Fan 101, Low pressure Compressor 102, Low pressure DT Turbine 103, low pressure DT Turbine Inlet Nozzle 104, High Pressure Compressor 105, High Pressure DT Turbine 106, High pressure DT Turbine Inlet Nozzle 107, Diffuser 108, combustion chamber 109, Shaft 110, Nozzle at the rear end 111.
DENOTES OF THE DRAWING
The invention as such, is marked as 100. The next 11 consecutive numbers are used to denote the different features of the invention, with the help of Figure 1.
The different features of the invention 100 are marked as follows.
The system 100 involves a Fan 101 which is connected to a low pressure compressor 102, a low Pressure DT Turbine 103, a high Pressure Compressor 105, a High Pressure DT Turbine 106 through a shaft 110.
The air is taken through 101 and is compressed at 102 and 105.
The output of 102 and 105 are inputted to 103 and 106 through low pressure DT Turbine Inlet Nozzle 104 and High pressure DT Turbine Inlet Nozzle 107 respectively.
The shaft 110 is rotated due to shear force developed in the DT Turbines 103 and 106.
The Diffuser 108 is the divergent section of the engine after the compressor 106 and before the combustion chamber 109. The 108 directs the air flow in to 109 for combustion.
The combust high pressure high temperature air is pushed out through the nozzle 111 at the rear end.
DETAILED DESCRIPTION OF INVENTION
The invention can now be described in detail.
The Figure 1 describes the entire system 100. The system includes a Fan 101 which is connected to a low pressure compressor 102, a low Pressure DT Turbine 103, a high Pressure Compressor 105, a High Pressure DT Turbine 106 through a shaft 110.
Once the system is initiated by an auxiliary power unit (APU) the air is inputted to the system through 101.
The inputted air is then compressed at 102 and the output from 102 is forwarded to 103 through 104.
Inside 103 there are some discs arranged in a shaft. When the output of 102 enters 103 the high velocity air causes a shear force on discs and thereby rotates the discs inside 103 leading to the rotation of shaft 110.
The outputted compressed air from 103 is then moved to 105 and is compressed again and tangentially moved to 106 through 107. The same shear force is again generated in 106 and rotates the shaft 110 attached to it.
The highly compressed high pressure high velocity air from 106 is then directed to 108. In 108 the velocity of air is reduced with out loosing its high pressure and is inputted to 109 steadily without extinguishing the flame there in 109 for combustion of fuel mixed air. In 109 the fuel mixed high pressure air is burned to generate power or Thrust.
The hot expanded gas from 109 is then pushed out through 111.
The 110 is connected to the 101 and 102, 103 and 105, 106 and hence when the discs at the 103 and 106 is rotated the 110 is rotated and there by 101 rotates and scoops up fresh air again to repeat the whole process and thereby helps in the movement of the aircraft.