RU2805548C1 - Method for gas generation and engines (embodiments) - Google Patents

Abstract

FIELD: gas turbine engines.

SUBSTANCE: gas generation method is implemented in an engine containing a turbine, a compressor, two combustion chambers (CC) and a cylinder with a freely moving piston. During the working stroke in the first CC, the burnt mixture is pumped into the turbine and into the cylinder. The piston, moving, compresses and forces air from the second half of the cylinder into the second CC, where it is then held. The first CC and cylinder are purged, the exit from the cylinder is locked, the first CC and cylinder are filled with compressor air, and the working stroke in the second compressor is implemented in a similar way. The gas turbine engine operating according to the proposed method contains a compressor, a turbine, two combustion chambers, a cylinder with a freely moving piston, the length of which is equal to half the cylinder. The cylinder's outer terminals are connected to the combustion chambers through locking devices (LDs), and its central terminal is connected to the turbine through an LD. During the working stroke in the first CC, the gas flow is injected into the turbine and into the cylinder, displacing air from there into the second CC, which is closed and the air is kept. After exhaust, the first CC and the free part of the cylinder are purged, filled with air and kept there. The working stroke in the second CC is implemented in a similar way. According to another embodiment, the gas turbine engine operating according to the proposed method contains a compressor, two turbines, two compressor stations and a channel in which a freely moving piston can be installed, the ends of the channel are connected through locking devices, respectively, to the left compressor station and the left turbine, as well as to the right compressor station and with the right turbine. During the power stroke, the burnt mixture from the first CC is injected into the first turbine and into the air channel, the air is compressed and displaced into the second CC, which is closed, and the air is kept. The first CC and the channel are blown and filled with air which is kept there. The working stroke in the second CC is implemented in a similar way.

EFFECT: objective of the invention is to develop a method for generating gases and engine circuits operating according to this method, containing a minimum number of moving parts

3 cl, 2 dwg

Description

Field of technology

The present invention relates to gas turbine engines (GTE), preferably of medium and low power.

The purpose of the invention is to develop a method for generating gases and engine circuits containing a minimum number of structural elements and moving parts.

A detonation internal combustion engine is known, patent RU 2066383 C1, l.1, containing at least a block of twin cylinders with separating pistons forming gas cavities with combustion chambers and hydraulic cavities communicated with each other and with a hydraulic turbine using working fluid lines, characterized in that the combustion chambers of the engine cylinders are equipped with detonators. The invention relates to automobile transport and is intended for use as a power plant for cars. The objective of the invention is to create an engine with high quality characteristics through the use of detonation combustion.

The known engine has the following disadvantages:

The transmission of force to the turbine using fluid at high speeds is associated with significant turbulence of this fluid and, consequently, with a significant loss of power. The combustion chamber in the cylinder, separated by a piston from the cavity with liquid, has a low temperature, which reduces the efficiency of fuel combustion. The mechanism required to synchronize the movement of the pistons adds complexity to the engine design. The use of a known engine without detonators does not eliminate these disadvantages. Detonation combustion of fuel contributes to the formation of shock waves in the liquid and the occurrence of cavitation, leading to the destruction of turbine blades.

A rotary piston engine is known, patent RU 2516044 C2, l.4, containing a housing, a rotor with a cylindrical shoulder located in the end caps, a combustion chamber, a fuel injector, a high-pressure air compressor and a recuperative heat exchanger for heating the air after the compressor with the heat of exhaust gases, characterized in that the cylindrical shoulder of the rotor is made in the form of a profile cam, and in the groove of the housing a frame is installed in the form of two guide plates, inside of which a radial blade is located, and an upper cover, while a spring-loaded piston connected to the blade and two spring-loaded stops with a gap of 0.2...0.5 mm relative to the upper end of the blade, and in the blade itself and the guide plates, as well as in the end covers and housing, there are channels for air sealing the rotor; in addition, the engine is equipped with two thermally insulated combustion chambers of periodic action , while in each chamber there are intake and exhaust valves equipped with an electromagnet and a servo drive, a fuel injector with a pneumatic drive and a piston for changing the geometric volume of the chamber, and two receivers are installed on the air supply line from the compressor to the engine: one receiver, with a built-in electric heater, is installed after the recuperative heat exchanger and connected to the combustion chambers, and the second receiver is installed before the recuperative heat exchanger, while a pneumatic system in the form of pressure reducing valves, receivers and solenoid valves, which is interconnected with the intake and exhaust valves of the combustion chambers, is connected to the compressed air supply line after the second receiver, pneumatic drives of fuel injectors, as well as channels for supplying sealing air in the end caps, housing, frame guide plates and radial blade channels.

The problem being solved is to increase the efficiency of the engine over a wide range of its operation and increase its service life.

The known engine has the following disadvantages:

The implementation of the sequence of its operation is achieved through the use of a large number of auxiliary equipment, including pneumatic units, electric heaters, receivers, as well as through a developed gas pipeline system, which leads to design complexity, reduced engine reliability and heat leakage in numerous channels. The specified degree of air compression (0.8-1.0 MPa) is insufficient to implement the diesel engine operating mode. The engine does not have the ability to quickly change operating modes, for example, when working with different types of fuel.

The closest set of features to the claimed invention is a rotary internal combustion engine, patent RU 2464431 C2, (prototype), containing a housing with cylindrical cavities made in it, two rotors placed in them and rotating on a straight shaft, movable plates of a gate partition placed in the groove of the housing with the possibility of constant contact with the surfaces of the rotors due to springs, two combustion chambers with nozzles for fuel injection and spark plugs, inlet and outlet openings on both sides of the gate plates, serving together with the rotors and housing in the formation of expansion chambers and compression chambers working fluid, characterized in that the shaft axis is located on the central part of the housing, two movable plates of the gate partition are placed in radial grooves and their movement is carried out by means of a spring together with the piston cylinder from the pressure when supplying the burning fuel mixture from the combustion chambers, while the rotors are made in in the form of cylinders eccentrically mounted on a shaft with rotation of their outer surfaces due to bearings relative to the base forming cylinders of the rotors with the ability to provide sequential processes of suction, compression, combustion and exhaust by each rotor alternately with the transfer of compressed air from one rotor to another and with one cycle of operation for each rotation of the shaft.

The invention is aimed at simplifying the design, increasing durability, and increasing efficiency.

The known engine has the following disadvantages:

Rotors operate in the combustion chamber under large temperature differences, which contributes to accelerated wear of bearings in the rotors and instability of the gap between the cylinder and the rotor. Vane plates in rotor devices are subject to accelerated wear because they operate at high temperatures and are subject to significant bending forces from the rotors at high rotor speeds. All gas channels converge towards the camshaft cams and diverge from it, which leads to lengthening of the channels. Intake of fresh air and injection of hot gases into the rotor device through the same channel is undesirable, since the fresh air is heated and the hot gases are cooled, which reduces the efficiency of the engine. The presence of a camshaft and a drive to it complicates the engine design. There are no possibilities for promptly changing operating modes and for holding the burning mixture until it is completely burned.

When examining the distinctive features of analogues of the invention, an engine containing a minimum number of structural elements and moving parts was not identified.

Essence

The technical problem to be solved by the claimed invention is the development of a method of operation and circuits of engines operating according to the proposed method, containing a minimum number of structural elements and moving parts. The technical result of the development is the method of operation and circuits of gas turbine engines containing a minimum number of structural elements and moving parts.

The solution to the technical problem of developing a method of engine operation was achieved in a gas turbine engine (GTE), containing two combustion chambers, a turbine, and a cylinder with a piston. During the working stroke in the first combustion chamber (CC), the burnt mixture is pumped into the turbine and into the cylinder with compressor air, the piston under the pressure of this mixture additionally compresses and displaces air from the cylinder into the second CL, the second CL is locked and the air is kept. The first compressor and cylinder are purged with air outlet into the turbine, the exit from the cylinder is locked, the first compressor and cylinder are filled with air compressed in the compressor and kept there. The next working stroke is implemented in the second CS.

The solution to the technical problem of developing an engine operating according to the proposed method was achieved in a gas turbine engine containing two combustion chambers, a turbine connected through locking devices (SD) to the combustion chambers, a cylinder with a piston, the left outermost outlet of the cylinder is connected through the SG to the output of the first CS , the right extreme output of the cylinder is connected through a charger to the output of the second CS, the middle output of the cylinder is connected through a charger to the turbine inlet. The piston in its extreme position in the cylinder is located between the outer and central terminals of the cylinder. During the power stroke, for example, in the left CV, the piston, moving to the right half of the cylinder, compresses and displaces air into the right CL, which is locked and the air is held. The remaining gas in the left half of the cylinder is removed after purging. Compressor air is injected into the left CS and the left half of the cylinder and is kept there. The right combustor contains air prepared for the working stroke, in which there are practically no exhaust gas impurities. The next working stroke is implemented with the participation of the right CS.

The solution to the technical problem of developing an engine operating according to the proposed method was achieved in another version of the gas turbine engine, containing two combustion chambers, two turbines, a channel, the leftmost input of which is connected through the first charger to the output of the first compressor and through the second charger is connected to the input of the first turbine , the right extreme input of the channel is connected through the third charger to the output of the second CS and through the fourth charger it is connected to the input of the second turbine.

In this embodiment, the engine can operate without a piston. During the power stroke, for example, in the first combustor, a flow of exhaust gases is pumped into the first turbine. Part of this flow penetrates the gas channel, compresses and displaces air from it into the right CS. When the mixing zone of exhaust gases and air approaches the right combustor, it is closed and the air compressed in it is kept. The second charger is closed, the first combustion chamber and the channel with air outlet into the second turbine are purged. The entrance to the second turbine is closed, compressor air is pumped into the first compressor and the channel and maintained. In the second CS, a working stroke is implemented with the exit of the burnt mixture into the second turbine and into the gas channel. Further, the working stroke is implemented in a similar way.

Other variants of gas turbine engines operating according to the proposed method of gas generation are also possible.

For example, in an engine containing one turbine, there may be no channels between the turbine and the first and second compressors. The exhaust gases in this engine will be forced into the turbine through the free half of the cylinder.

The essence of the invention is illustrated in the drawings, which are given as examples to explain the method of operation of a gas turbine engine on devices developed to implement this method.

In fig. Figure 1 shows a diagram of the first version of the gas turbine engine.

In fig. Figure 2 shows a diagram of the second version of the gas turbine engine.

The gas turbine engine according to the first option (Fig. 1) operates as follows:

The engine contains the first KS 1, the second KS 2, turbine 3, cylinder 4 with piston 5. The compressor output is connected through CU6 to KS1 and through CU7 connected to KS2.

Before the start of the working stroke, for example, in KS1, piston 5 in cylinder 4 is located in the extreme left position. All memories are closed. In KS2 and on the right side of the cylinder there is compressor air. KS1 contains air prepared for the working stroke. At the beginning of the working stroke, fuel is injected into KS1 and ignited, after the necessary exposure of the burning mixture, ZU8, ZU10 and ZU12 are opened. The burnt mixture is pumped through ZU8 into turbine 3 and through ZU10 into cylinder 4. Piston 5, moving to the right, compresses and pumps compressor air from the right side of cylinder 4 through ZU12 into KS2. When the specified pressure is reached in KS2, CU12 is closed and the air is kept in. Upon completion of the working stroke in KS1, lock CU8, open CU6 and CU11 and blow KS1 with air exiting into turbine 3. Close CU11 and continue to pump compressor air into KS1 and into the left side of cylinder 4. Close CU6 and keep compressor air in KS1 and in the left cylinder parts. The next working move with the participation of KS2 is implemented in a similar way.

The gas turbine engine in another version (Fig. 2) operates as follows:

The engine contains a first combustion chamber KS2-1, a second combustion chamber KS2-2, a first turbine 2-3, a second turbine 2-4, a channel 2-5, the leftmost input of which is connected through ZU2-6 to the output of KS2-1 and through ZU2 -7 is connected to the input of turbine 2-3, the right extreme input of channel 2-5 is connected through ZU2-8 to the output of the second combustion chamber KS2-2 and through ZU2-9 is connected to the input of the second turbine 2-4. Shut-off devices ZU2-10 and ZU2-11 are connected between the compressor and combustion chambers KS2-1 and KS2-2. Before the start of the working stroke, for example, in KS2-1, it contains air prepared for the working stroke, in channel 2-5 and in KS2-2 there is compressor air. All memories are closed. With the start of the working stroke, the working mixture in KS2-1 is ignited. After the necessary exposure of the burning mixture, ZU2-6, ZU2-7 and ZU2-8 are opened. The flow of burnt gases is pumped into turbine 2-3, and part of this flow is pumped into channel 2-5, displacing compressor air from there through ZU2-8 into KS2-2. When the specified pressure is reached in KS2-2, ZU2-8 is closed and the air in KS2-2 is maintained. Close ZU2-7, open ZU2-10 and ZU2-9 and blow through KS1 and channel 2-5 with air exiting into turbine 2-4. Close ZU2-9 and pump compressor air into KS2-1 and into gas channel 2-5. Next, the working stroke is performed in the same way in KS2-2.

Information confirming the possibility of implementing the invention to obtain the specified result is as follows:

The amount of air in the channel must be sufficient to compress it in the combustor to a certain pressure before the mixing zone of air and gases reaches the entrance to the combustor.

The piston in its extreme position in the channel should be located directly between the outer end outlet in the channel and between its central outlet, in order to reduce the admixture of exhaust gases. The weight of the piston must be extremely light.

There should be buffer cavities and pressure sensors at both ends of the channel. In the engine diagram (Fig. 2), there may be no piston in the channel. In this case, the diameter of the gas channel should be minimal, and its length should be slightly increased to reduce the length of the zone where the exhaust gases mix with air.

Coordinated operation of gas turbine engine components can be carried out using an electronic control unit (CU) and with the necessary sensors.

Locking devices can preferably be made in the form of a shaft with holes for the passage of gases, the rotation of which is carried out by an electromagnetic device according to signals from the control unit.

The gas turbine engine can be started after spinning up the compressor, for example, using a starter.

When working with different types of fuel, the required degree of compression in the compressor can be adjusted by changing the pressure at the outlet of the controlled compressor.

An increase in the power of a gas turbine engine can be achieved by increasing the number of steam generators connected to the turbine inputs.

The engine speed can be adjusted by delaying injection into the combustion chambers.

A rotor-blade device can be used as a turbine.

Information sources:

1. Patent RU 2066383 C1. Detonation internal combustion engine. IPC F02B 71/04.

2. Patent RU 2495262 C2. A method for creating a multi-cylinder liquid internal combustion engine and an IPC engine F02B 75/00, F01B 11/08, F02B 71/04.

3. Patent RU 2516044 C2. Rotary piston engine. IPC F02B 55/02, F01C 1/356, F02B 19/02, F16J 15/40.

Claims (3)

1. The method for generating gases is implemented in a gas turbine engine containing two combustion chambers and a turbine mounted on an output shaft, characterized in that it additionally contains a cylinder with a piston; during the working stroke in the first combustion chamber, the burnt mixture is pumped into the turbine and into the cylinder with compressed compressor air, the piston under the pressure of this mixture displaces the air from the cylinder into the second combustion chamber, where it is further compressed, the second combustion chamber is locked and the air is kept; the first combustion chamber and the cylinder are purged with air outlet into the turbine, the exit from the cylinder is locked, the first combustion chamber and the cylinder are filled with compressor air and kept there; the next working stroke is implemented in the second combustion chamber. 2. A gas turbine engine operating according to the method of claim 1, containing two combustion chambers, a turbine, the inputs of which through locking devices can be directly connected to the outputs of the first and second combustion chambers, characterized in that the left outermost outlet of the cylinder is connected to the output through a locking device of the first combustion chamber, the right outermost outlet of the cylinder is connected through a locking device to the outlet of the second combustion chamber, the middle outlet of the cylinder is connected through a locking device to the turbine inlet, the piston in one of the extreme positions in the cylinder is located between the outer and central outlets of the cylinder. 3. A gas turbine engine containing two combustion chambers and two turbines, characterized in that it additionally contains a channel in which a freely moving piston can be installed, the leftmost input of the channel is connected through the first locking device to the output of the first combustion chamber and through the second locking device is connected to to the inlet of the first turbine, the right extreme inlet of the channel is connected through the third shut-off device to the output of the second combustion chamber and through the fourth shut-off device is connected to the inlet of the second turbine; with the start of the working stroke, the burnt mixture in the first combustion chamber is pumped into the first turbine, and part of this flow is pumped into the channel, displacing compressor air from there into the second combustion chamber, where the compressed compressor air is closed and held; the first combustion chamber and the channel are purged with air exiting into the second turbine, the first combustion chamber is closed and compressor air is pumped into it and into the gas channel; the next working stroke is performed in the second combustion chamber.

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