WO2013179301A2

WO2013179301A2 - Conveyor belt converted, closed work space, valved, exhaust gas evacuating, gas turbine embodiments

Info

Publication number: WO2013179301A2
Application number: PCT/IN2013/000304
Authority: WO
Inventors: Lappasi Sundararajan VIDHYASAGAR
Original assignee: Vidhyasagar Lappasi Sundararajan
Priority date: 2012-05-29
Filing date: 2013-05-09
Publication date: 2013-12-05
Also published as: WO2013179301A3

Abstract

A conveyor belt rotor is converted to highly efficient 'all gas turbine' with added structures, a rotor cover secured to rotor tightly; an evacuation means to remove exhaust gas and a valve to prevent back flow of gas, which tends to cause opposite rotation. A combustion gas set up and an arc of plate to rotate under it are added to it to function as combustion gas turbine for cyclic acceleration of spin of axis of rotor; since the combustion space is cleared off all gas in every cycle the embodiment achieves volumetric and combustion efficiencies higher than present combustion engines. Another kind of combustion gas set up using a cylinder-piston set up added to the 'all gas turbine' to function as combustion gas turbine where also the combustion space is cleared off all gas before next cycle. In this embodiment, instead of the conveyor belt rotor, a cylinder-piston set up with crank mechanism to achieve spin of the axis is added, which makes it another kind of combustion gas turbine. In the last embodiment discharge of compressed charge and its ignition occurs in the work space of the rotor of all gas turbine.

Description

COMPLETE SPECIFICATION

Title of the invention

Conveyor belt converted, closed work space, valved, exhaust gas evacuating, gas turbine embodiments

Field of the invention

The present invention relates to the field of gas turbines including combustion gas turbines to attain higher gas, combustion and thermal efficiencies.

Background art

[01] The aim of gas turbines, including combustion gas turbine, is to achieve spin of an axis/shaft efficiently. Piston engine, Wankel engine and other rotor (axial flow and tangential flow) engines are such turbines. In all of them, the spin of the axis is achieved when a working gas applies a collision force on work surface/s and work. So, efficiency of these turbines depends basically on the 'gas efficiency' of the working gas, which is a measure of how much of the working gas works to achieve the spin. If the turbine is combustion gas one then three more efficiencies count:

i. Volumetric efficiency ii. Combustion efficiency iii. Thermal efficiency

[02] Combustion gas piston engine, axial flow rotor (combustion gas jet engine and non- combustion gas wind mill) and Wankel engines are the most commonly used types of gas turbines. Their efficiencies to-day after more than 100 years of research:

1. Volumetric efficiency: 70 to 90%

1. Combustion efficiency: 90%.

2. Thermal efficiency: 33%. (33% is lost as heat through the cooling system. 33% is lost in exhaust gas as kinetic and heat energy.)

3. Gas efficiency: 50%.

Tangential flow rotor gas turbines have been tried but failed in practice both as combustion and non-combustion turbines due to lower efficiencies. So, there are lots of losses in gas turbines that have been used so far. Reducing the losses significantly has been extremely difficult. So, a new design of whole gas turbine including combustion gas turbine is needed.

Object/aim of the invention

[03] The aim is to design such a gas turbine to achieve high efficiency in all the types of efficiencies said above. It is based on three features from the analysis of structure and function of the commonly used turbines.

1. Axial flow rotor:

Scientists have derived that its maximum theoretical gas efficiency, called 'Betz limit', can only be 59%. So this rotor cannot be used to construct efficient gas turbines.

2. Combustion engines like internal combustion piston engine and rotor engines like Wankel engines for cyclic acceleration of spin of axis:

Their thermal and gas efficiencies can be increased to 50% and 85% respectively by increasing the (optimum) compression ratio. But we do not increase the ratio because the combustible charge gets compressed more, which results in problems like pre- ignition, detonation and structural damage. So, a solution to get increased efficiencies is to keep the compression stroke in optimum ratio - 'charge compression ratio' - but increase the compression ratio for the power stroke - the 'power or work ratio'. Many attempts like Miller cycle engines and Atkinson cycle engines have been made but significant efficiencies have not been achieved. The failure seems to be due to attempts to achieve the two ratios in the same space.

3. Identify the causes of possible losses and construct the turbine accordingly to prevent them.

Brief description of the prior art

No prior art seems to be available.

Brief description of the drawings

[04] Fig.1 shows face-side view of the conveyor belt (2) converted to a rotor with blades (3) attached to the belt. Fig.2 shows face-side view of the rotor cover enclosing the gracing it to prevent gas escape, having openings for gas flow and a valve function.

Fig.3. shows cross section of the full gas turbine to function as an 'all gas turbine' taken through the rim aspect.

Fig.4. shows upper part of cross section of the 'all gas turbine' showing alternate type of valve - a hinged one-way valve - to prevent flow of working gas towards the succeeding blade causing opposite rotation.

Fig.5 shows a combustion chamber to be placed over the inlet flow pathway of the 'all gas turbine' to function as combustion gas turbine.

Fig. 6 shows a cross section of the combustion gas turbine taken through the rim aspect. It shows a combustion gas set up and a cylinder-piston set up to withdraw combustible charge, compress it and send it into the combustion chamber. An arc of plate (19) spins through the rim gaps, which makes the combustion chamber open and closed with respect to rotor work spaces cyclically.

Fig.7 shows a different combustion chamber to be placed on the 'all gas turbine' to make it function as different type of combustion gas turbine.

Fig.8 shows a cross section of this combustion gas turbine taken through the rim aspect. The combustion gas set up consists of combustion chamber and a cylinder-piston set up for compression of combustible charge.

Fig.9 is a cross section of a combustion gas turbine where a cylinder-piston set up, for working gas to work, is added, instead of the 'all gas conveyor-belt turbine, to the combustion set up said in embodiment of fig.8.

Fig.10 shows a cross section of a combustion gas embodiment where discharge of compressed charge and its combustion occur in the work space of the rotor of the all gas turbine.

Detailed description

[05] A gas turbine has many parts. The description describes mainly those parts needed for the inventive features of the embodiments. The embodiments are described in terms of turbine function. But it would be apparent to those skilled in the art that they are applicable for related purposes like propeller and turbo-propeller functions. 1. 'AH gas turbine' - conveyor belt rotor gas turbine for any kind of gas

Its construction is described in terms of possible gas losses in any gas turbine.

[06] One cause of loss is that the working gas doesn't get sufficient time to do full work; before it does full work, it flows out or gets pushed out as exhaust gas.

To reduce this loss the inventor uses a conveyor belt, converting it into a rotor. A conveyor belt consists of two or more axes/shafts with pulleys or toothed gears on which a continuous belt can run. If the axes are spun by some energy the belt rotates; it also makes a linear motion through a distance. Conversely, if the belt is rotated by some means the axes will spin. This is achieved by attaching blades to the belt and a working gas made to flow tangentially on to them. Fig. l shows two axes/shafts (4) with toothed gears on which a belt (2) runs. Blades (3) are attached to the belt and a working gas flows (1) tangentially to work on the blades. The space between two blades is One work space'.

So, a blade will travel a linear distance also while gas works on it. The more linear distance the blade can travel more time the gas gets to do more work. With the conveyor belt-rotor it is possible to make the blades travel required distances by spacing the axes in required distances. It is one of the key features of the invention.

[07] Another cause of loss is that working gas escapes before doing any work or before doing full work.

To prevent this loss the inventor uses a 'rotor cover' for the rotor (Fig.2). The rotor can be considered to have two oval faces joined at their circumferences by a rim. The working gas can escape through the faces and the rim. The escape through the faces is prevented by two 'face plates' (9), one at one face. The escape through the rim is prevented by a 'rim plate' (8) joining the circumferences of the face plates. The plates (9 and 8) are secured onto the rotor such that there is no gap between them and the rotor; so the working gas cannot not escape away from the rotor and flow from one work space into another. This is another key feature of the invention.

The space between two blades is 'one work space' and it is a closed space now. The friction between the edges of the blades, belt and the plates can be minimized variously. The axes shafts are taken through face plates with bearings so that they spin smoothly. The rim plate has an opening 'inlet opening' (7) for inflow of the fresh working gas tangential to the rotor blades and another opening Outlet opening' (10), for outflow of the gas after work, the exhaust gas.

Fig. 3 shows a cross section of the full embodiment taken through the rim.

On the inlet opening (7) in the rim plate there is a pathway, 'inlet flow pathway' (12) for directed flow of working gas through the inlet opening (7) onto rotor and over the outlet opening (10) there is Outlet flow pathway' (13) for directed outflow of exhaust gas. In the fig. the rotor will spin clockwise.

In terms of turbine function, the space inside the rotor cover can be considered to be of two regions, a turbine region where the working gas enters through inlet opening, works and gets out as exhaust gas through the outlet opening and a non-turbine -region, extending from the outlet opening to the inlet opening, where no work occurs.

[08] Another cause of loss is the presence of gas (e.g. the energetic exhaust gas) in work spaces when they come under the fresh working gas. It reduces free flow of working gas on to and its good work on the work surfaces.

To reduce this loss the inventor uses an 'evacuating set up' like the exhaust fan (11) in the outlet opening or pathway. It removes much of the exhaust gas from the work spaces. So, they are near vacuum when they come under the inlet opening; so good working gas flow and its good work get achieved. It is another key feature of the invention.

[09] The last cause of loss: While the working gas works on the leading blade some of it also works on the succeeding blade, which tends to cause opposite rotation. This readily occurs in tangential flow rotors with single axis from which multiple blades arise radially. In inventor's basic embodiment, the all gas turbine, also, this loss can occur.

The inventor gives two ways to prevent this flow towards the succeeding blade. Fig.2 and 3 show one way. The rim plate has a slit (6 in fig. 2) through which a plate (5 in fig.2 and 3) can go into and out of the rotor work spaces at correct timings. The plate 5 goes out through the slit to allow a rotor blade enter into the turbine region to come under the inlet opening. As soon as the blade has passed it goes in and prevents the back flow. Fig.4 shows another way near the inlet opening. It consists of a plate/screen hinged (14) at the rim plate near the inlet opening. It moves up and down at correct timings to allow a blade travel un-obstructed into the turbine region.

[010] A cycle of work:

The working gas flows through the inlet pathway (12) and through the inlet opening (7) into the. closed rotor work space, works on the leading blade until the blade reaches the outlet opening achieving maximum work, where it is exhaust gas. It then flows out through the outlet pathway, the flow being facilitated by the exhaust fan there. So, the work space is near vacuum when it comes under the inlet opening again. The vacuum facilitates the inflow of working gas and its work on the blade in the next cycle.

It can be seen that all the four possible gas losses are prevented greatly, so the turbine achieves high gas efficiency.

Combustion gas embodiments

[Oi l] One main cause of loss in producing a combustion gas is the presence of energetic combustion gas in combustion space when combustible charge is brought in and ignited. It results in lower volumetric and fuel and combustion efficiencies.

One necessity in producing a combustion gas is the need to compress the combustible charge to take it to its ignition point.

2. A type of combustion gas set up added to the 'all gas turbine', above to function as combustion gas turbine

[012] Fig.5 shows a 'combustion chamber' (15) to be placed above the inlet flow pathway (12) of the first embodiment. The gap between the two structures is of two types, rim gap (16) and face gap (17). The two face gaps are closed so that combustion charge and combustion gas cannot escape through them.

[013] Fig.6 shows the cross section of the full embodiment taken through the rim aspect. An arc of a plate (18), 'rotary plate', is connected to the axis of the rotor, so it rotates at the speed of the rotor. It is connected such that it rotates through the rim gaps (16). When the gap, 'rotary plate's gap' between the rim edges (19 and 20) of the rotary plate is under the combustion chamber, the chamber is open and when the plate comes under the chamber, the chamber is closed.

When the 'rotary plate's gap' is under the combustion chamber either or both the rim gaps will be open, so gas can escape out through them. So, valves (21 and 22) are provided at these rim gaps so that they open and close the rim gaps as the rotary plate's 'rim ends/edges' enter and leave the gaps.

[014] Compressed combustible charge is made available in the combustion chamber by a cylinder-piston set up. When the piston in the cylinder (23) withdraws (its suction stroke) 'combustible charge' is sucked from a source through pathway (24) with valve 26 getting opened and valve 27 closed. When the piston makes the reciprocal motion towards the cylinder top it compresses the charge with the valve 26 getting closed. When charge is compressed to the required degree valve 27 opens and the charge flows into the combustion chamber through pathway (25).

[015] A cycle of work:

A cycle of work is described from the time when the combustion chamber is closed with respect to rotor as in fig.6 and the rotor is started to rotate. The compressed combustible charge is brought into the combustion chamber by the cylinder-piston set up. When the rim edge (20) of the rotary plate comes under the combustion chamber the valve (21) closes its rim gap. Combustion is started. When the rim edge leaves from under the combustion chamber the valve (22) closes its rim gap.

So, combustion charge and/or combustion gas cannot escape through the rim gaps and the combustion gas flows through closed space to the closed work spaces of the rotor.

When almost all the combustion gas has flown out of combustion chamber - the magnitude of the 'rotary plate gap' is such that all the gas flows out - the rim 19 of the rotary plate enters under the combustion chamber (after valve 21 opens); so, combustion chamber begins to get closed. When this rim edge (19) goes through the other rim gap after valve 22 opens the rotary plate closes the combustion chamber completely.

Meanwhile the combustion gas flows to rotor, works, becomes exhaust gas, gets evacuated by the exhaust fan in outlet opening (10). So, empty work spaces come under the inlet opening in the next rotation. The presence of near vacuum in the rotor work spaces when they come under the inlet opening facilitates (i) complete flow of combustion gas from combustion chamber, (ii) good work of the gas on the blades.

The near vacuum in the closed combustion chamber helps in bringing the compressed combustion charge and near complete combustion of the charge, resulting in higher combustion efficiency.

3. Another type of combustion gas set up added to the 'all gas turbine' above to function as combustion gas turbine

[016] The two face walls and one rim wall of the inlet flow pathway (12) of the first embodiment is extended to a certain length. In effect we get a chamber (Fig. 7) with two face walls (29a and 29b), one rim wall (28) and three openings (30, 31 and 32). It is the ' combustion chamber' .

Fig.8 shows the cross section of the whole embodiment taken through the rim aspect.

1. One opening 'Cylinder opening' (30), opposite the rim wall: To this opening a 'Cylinder (33) - piston (34) set up' is attached. A 'piston-lock' (35) mechanism is provided in the cylinder to allow and prevent the motion of the piston from the top centre position towards bottom dead centre position at correct timings.

2. One opening at the top, 'Inlet opening of combustion chamber' (31) for inflow of combustible charge from a source through a pathway (38). It has a one-way valve (36) that controls the flow of the charge into the combustion chamber.

3. One opening Outlet opening of combustion chamber' (32) at the junction of combustion chamber and inlet flow pathway (12) of the first embodiment - for outflow of combustion gas from combustion chamber on to the rotor. It has a one-way valve (37) for the control of the outflow.

[017] A cycle of work:

Description of a cycle of working is begun when the combustion chamber is almost empty of gas and the piston in the 'cylinder-piston set up' is at the top dead centre position. Valve 37 is closing opening 32 closed. Valve 36 also is closing its opening 31. The 'piston-lock' mechanism is released, so the piston can move towards the bottom dead centre position, the 'suction stroke'. As the piston begins to move the valve 36 of combustion chamber opens allowing flow of combustible charge through the opening 31 into the combustion chamber and into the cylinder. As the piston begins the reciprocal motion from the bottom dead centre position the valve 36 closes its opening 31. So, now the charge is in a closed space. So, the combustible charge gets compressed; when the piston is at the top dead centre position again the charge is fully compressed. Since this cylinder-piston set up achieves compression of the charge it can also be called, 'compression cylinder set up'. At this point the charge is ignited (structures for it are not shown in fig.). Combustion gas begins to get formed. The piston-lock mechanism locks the piston in the top dead centre position, so the combustion gas cannot work on the piston 34 (power stroke is prevented). Valve 37 opens its opening, so the combustion gas flows on to the rotor and work is achieved. After all the gas has flown out of combustion chamber the valve 37 closes its opening and the cycle ends.

4. A cylinder-piston set up added to combustion gas set up in the second type of combustion gas turbine to function as combustion gas turbine

[018] Fig.9 shows a cross section of the embodiment. The idea is to attach a cylinder (39) - piston (40) set up with crank mechanism (44) to the combustion set up of the third embodiment, so that the combustion gas works on the piston (40) of this set up (power stroke) and achieves the spin of the axis, the crank shaft (45). So, this cylinder-piston set up can be called, 'the power cylinder set up'. The cylinder 39 has 'exhaust gas opening' (41) just above the bottom dead centre position of the piston of this set up for outflow of exhaust gas. An exhaust gas outflow pathway (43) is attached to the opening 41 for directed outflow of exhaust gas. An evacuation set up like an exhaust fan (42) is placed in exhaust opening 41 or pathway 43 for removal of as much exhaust gas as possible.

[019] Work in a cycle:

Description of a cycle begins when the combustion chamber is almost empty of gas and the piston in the 'compression cylinder set up' is at the top dead centre position. Valve 37 is closing its opening 32. Valve 36 also is closing its opening 31. The 'piston-lock' mechanism in 'compression cylinder set up' is released, so the piston can move towards the bottom dead centre position, the 'suction stroke'. As the piston begins to move the valve 36 of combustion chamber opens allowing flow of combustible charge through the opening 30 into the combustion chamber and into the cylinder. As the piston begins the reciprocal motion from the bottom dead centre position the valve 36 closes its opening 31. So, now the charge is in a closed space. So, the combustible charge gets compressed; when the piston is at the top dead centre position again the charge is fully compressed. At this point the charge is ignited (structures for it are not shown in fig.). Combustion gas begins to get formed. The piston-lock mechanism 34 locks the piston in the top dead centre position, so the combustion gas cannot work on this piston (power stroke prevented) in the 'compression cylinder set up'. Valve 37 opens its opening, so the combustion gas flows on to piston 40 in the 'power cylinder set up', the piston being now in the top dead centre position. As the gas works this piston reaches its bottom dead centre position, when the gas becomes exhaust gas. Exhaust gas flows out through exhaust opening 41. The cylinder makes the reciprocal motion towards the top dead centre position.

Note that in every cycle of working, the combustion chamber becomes almost empty for good inflow' of combustible charge in it and its good combustion; the 'power cylinder set up' becomes almost empty of exhaust gas for good work of combustion gas; one can make the set up such that the piston travels required distance for maximum work of the gas.

5. Combustion gas set up integrated into the all gas turbine to function as combustion gas turbine.

[20] Fig. 10 shows a cross section of the embodiment taken through the rim aspect. A compression set up like cylinder-piston compresses the combustible charge and discharges it into work space of the all gas turbine near the valve to prevent the back flow of gas either through the rim plate or face plate of the rotor. Near the point of discharge means for ignition of the charge like spark plug or injection of fuel are provided.

A 'compression charge set up', a cylinder-piston set up' as given embodiment 2, (Fig.6) is attached to the main rotor either to the rim plate (8) or to the face plate (9) near the valve set up 5 or 14 of 2^nd and 3^rd embodiment. When the piston is withdrawn the charge to be compressed flows, from a source, into the cylinder 23 through the pathway 24 with its valve 26 opened. When the piston moves towards the top, with valve 26 closed, the charge is compressed; after required compression, valve 27 opens, the compressed charge flows through the pathway 25 in to the work space of the main rotor; after the flow, valve 27 of pathway 25 closes.

[21] Work in a cycle:

Description of a cycle begins when the valve 5 (or 14) of the main rotor had opened the path for the rotor blade and the blade has passed beyond it. The valve 5 closes such that back flow (reverse flow) of gas is prevented. After the blade passes the point of insertion of pathway 25, the valve 27 opens and compressed charge is pushed from the 'compression set up, in to work space inside the rotor. Just as rotor blade passes the point of insertion of spark ignition set up, valve 27 closes and ignition is started. In case of compression ignition as soon the rotor blade passes the point of insertion for fuel injection, fuel is injected. The combustion gas produced works on the rotor blade. After work, it flows out through the outlet opening 10.

Claims

Claims While the embodiments have been illustrated and described they are to be considered as illustrative and not restrictive in character, it being understood that only preferred embodiment has been shown and described and that all changes and modifications that come within the spirit of the invention are desired to be protected. I claim

1. A gas turbine, comprising conveyor belt converted into bladed rotor, rotor cover, exhaust gas evacuation set up, valve to prevent the back flow of gas, to function as efficient all gas turbine, further comprising combustion gas set up added to all gas turbine to function as combustion gas turbine, further comprising a cylinder-piston set up added to the combustion gas set up to function as combustion gas turbine, further comprising combustion gas set up integrated into all gas turbine to function as combustion gas turbine.

2. As claimed in claim 1, the rotor cover consists of face plates and rim plate gracing the rotor to make work spaces between blades closed spaces to prevent escape of gases.

3. As claimed in claim 1, exhaust gas evacuation set up consists of means like exhaust fan to remove exhaust gas from work spaces to get more efficiency.

4. As claimed in claim 1, the valve consists of means like a plate or screen to prevent back flow of gas tending to cause loss making opposite rotation.

5. As claimed in claim 1, a combustion gas set up consists of:

a combustion chamber for burning combustible charge;

an arc of plate that rotates under the combustion chamber to make the chamber open and closed with respect to the rotor;

valves that open and close the gaps to allow the arc of plate to go through and prevent gas loss;

a cylinder-piston set up connected to the combustion chamber for compression and flow of combustible charge into the combustion chamber.

6. As claimed in claim 1, a different combustion gas set up consisting of:

a combustion chamber on the rotor for combustion of fuel a cylinder-piston set up for compressing the combustible charge; a lock mechanism to allow and prevent the piston motion;

valve at one opening of the combustion chamber for controlled flow of combustible charge into the combustion chamber;

valve at another opening of combustion chamber for controlled flow of combustion gas into the rotor.

7. As claimed in claim 6, a cylinder-piston set up added to combustion set up consisting of:

a cylinder- piston with crank mechanism and crank shaft to achieve the needed spin of axis, the crankshaft;

a exhaust gas opening with a pathway in the cylinder for outflow of exhaust gas; an evacuation set up like exhaust fan in the exhaust gas opening or pathway for quicker and more outflow of exhaust gas.

8. As claimed in claim 1, combustion gas set up integration consists of:

a means like cylinder-piston to compress charge and discharge it into all gas turbine

a means like spark plug to ignite the charge near the point of discharge of the charge.

Dated this Signature: