RU2774091C1 - Gas turbine engine - Google Patents

Abstract

FIELD: engine technology.

SUBSTANCE: invention relates to gas turbine engines. A gas turbine engine containing a control unit, two alternately operating combustion chambers with fuel injectors and spark plugs, a compressor whose output through shut-off devices is connected to the inputs of the first and second combustion chambers, whose outputs through shut-off devices are connected respectively to the first and second inputs of the turbine, additionally contains a cylinder with a freely moving piston, four taps of the cylinder are connected respectively to the first combustion chamber, to the first turbine input, to the second turbine input and to the second combustion chamber.

EFFECT: invention provides an increase in the efficiency of the engine and an increase in its working life.

1 cl, 3 dwg

Description

Technical field

The present invention relates to engine building, in particular to gas generators for gas turbine plants. The claimed invention is directed to the development of a gas generator having 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 that the combustion chambers of the engine cylinders are equipped with detonators. The invention relates to motor vehicles and is intended for use as a power plant for vehicles. 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 by means of a liquid at high speeds of its movement is associated with a significant turbulence of this liquid and, consequently, with a significant loss of power. The combustion chamber in the cylinder, separated by a piston from the liquid cavity, has a low temperature, which reduces the efficiency of fuel combustion. The mechanism required to synchronize the movement of the pistons complicates the design of the engine. The use of a known engine without detonators does not eliminate these disadvantages. When the engine is operated with detonators, the detonation ignition of the fuel contributes to the occurrence of shock waves in the liquid and the occurrence of cavitation, leading to the destruction of the turbine blades.

A known method for creating a multi-cylinder liquid internal combustion engine and a device for its implementation, patent RU 2495262 C2, l.2, which contains a hydraulic system consisting of a turbine and cylinders that supply the turbine from the external combustion chamber with liquid under pressure from the gases of the burning fuel mixture and the preparation system and ignition of the combustible mixture, characterized in that the liquid engines are combined into one unit, the cylinders of which are paired into flow blocks, looped onto a common turbine, alternately filled with liquid cut off from the flow deflected into the paired cylinder, while the outflow of liquid occurs under the pressure of gases from external combustion chamber from the first cylinder, the flow returns to it again, displacing gases while the twin cylinder is erupted, and the subsequent block of the four-cylinder engine is activated when the pressure in the cylinder of the previous block is reduced by half, that is, inversely proportional to the number of engine blocks.

Known engine has the following disadvantages: due to the significant inertia, the engine is not effective with frequent changes in operating modes. With an increase in the fluid flow rate, the additional engine power to overcome turbulence increases, so the known engine is not efficient at high turbine speeds. When fluid is passed from one pipe to another, hydraulic shocks are possible. The exhaust valves are connected to a liquid vapor condenser that is returned back to the cylinder from the liquid reservoir, which complicates the design of the engine. Chemical additives from exhaust gases pollute the fluid and increase its chemical activity. The design of the engine is characterized by increased complexity.

The closest set of features to the claimed invention is a rotary piston engine, patent RU 2516044 C2, l.4 (prototype), containing a housing with a cylindrical cavity, a rotor with a cylindrical ledge located in the bearings of the end caps, a high-pressure air compressor and a recuperative heat exchanger for heating the air after the compressor with the heat of the exhaust gases; in addition, the engine is equipped with two thermally insulated intermittent combustion chambers, while in each chamber there are intake and exhaust valves equipped with an electromagnet and a servo drive, and a fuel injector with a pneumatic drive, and two receivers are installed on the air supply line from the compressor to the engine: one receiver with the built-in electric heater is installed after the recuperative heat exchanger and connected to the combustion chambers, and the second one is installed before the recuperative heat exchanger.

The problem to be solved is to increase the efficiency of the engine in 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 work is achieved through the use of a large number of auxiliary equipment, including pneumatic units, an electric heater, a receiver, as well as due to a developed gas pipeline system, which leads to a more complex design, a decrease in engine reliability and heat leakage in numerous channels. When examining the distinguishing features of analogues of the invention, a gas turbine engine containing a minimum number of structural elements and moving parts was not identified.

Disclosure of the essence of the invention

The problem to be solved by the claimed invention is the development of a gas turbine engine containing a minimum number of structural elements and moving parts.

The solution of the task of developing the simplest design of a gas turbine engine has been achieved in a gas turbine engine containing a turbine, a control unit, two alternately operating combustion chambers (CC) with fuel injectors and spark plugs, a compressor, the output of which is connected to the inputs through locking devices (SD) the first KS2 and the second KS3, the outputs of which are connected through locking devices, respectively, to the first and second inlets to the turbine, additionally containing a cylinder with a freely moving piston, four cylinder outlets are connected, respectively, to the first combustion chamber, to the first inlet to the turbine, to the second inlet to the turbine and with a second combustion chamber.

The essence of the invention lies in the fact that during the working stroke in the first CC the main flow of burning gases is directed to the turbine. Part of the flow gases are directed to the cylinder. The pressure of gases shifts the piston to the opposite side of the cylinder filled with compressor air. Air is injected into the second CC, compressed, locked in the CC and kept until the next working stroke. The piston is designed to transmit pressure to the air in the cylinder and to separate from the mixing of gases and air.

The essence of the invention is illustrated in the drawings, which are given as examples to explain the operation of a gas turbine engine (GTE).

In FIG. 1 shows a diagram of a GTE variant.

In FIG. 2 is a time diagram of pressure p versus time t in the first combustion chamber.

In FIG. 3 is a time diagram of pressure p versus time t in the second combustion chamber.

The gas turbine engine contains a control unit (CU), a compressor (not shown in the diagram), a turbine 1, two alternately operating combustion chambers KS2 and KS3 with fuel injectors and spark plugs; the compressor outlet through the shut-off devices ZU8 and ZU9 is connected to the inputs of the first KS2 and the second KS3, the outputs of which are connected through the shut-off devices ZU4 and ZU5, respectively, to the first and second inlets to the turbine 1. The engine contains a cylinder 11 with a freely moving piston 12, four cylinder outputs are connected respectively with the first combustion chamber KS2, with the first entrance to the turbine 1, with the second entrance to the turbine 1 and with the second combustion chamber KS3.

Before the start of the working stroke, compressed hot air is located in the first KS2. Compressor air is located in the second KS3 and in the gas channel 11. A dose of fuel is injected through the nozzle 10 into the CC2, and after its ignition and the necessary exposure, the ZU4, ZU 13 and ZU 14 are opened. The burnt air-fuel mixture is injected through the ZU4 into the turbine 1, fig. 2 2-3, and into the cylinder 11. Under the pressure of this mixture, the piston 12, moving in the cylinder 11, displaces air from it through the memory 14 into the second KS3. When the predetermined pressure in the CC3 is reached, the memory 14 is locked and compressed hot air is maintained until the next working stroke in the CC3, Fig. 3, 1-2. At the end of the working stroke in KS2, ZU8 and ZU7 are opened and KS2 and cylinder 11 are blown with compressor air with its exit into turbine 1, Fig. 2, 3-4. ZU7 is locked and air is continued to be pumped into KS2 and into cylinder 11. When the predetermined pressure in KS2 is reached, ZU8 is closed and compressed hot air is kept in KS2 and in cylinder 11 until the working stroke in KS3, fig. 2 4-5, which is implemented after some exposure, depending on the frequency of working strokes. Fuel is injected into KS3 and a working stroke is implemented in it, Fig. 3 3-4, with additional injection of air from the cylinder into KS2 and its subsequent holding, fig. 2 5-6. Next, a similar sequence of operations is implemented with the participation of KS2.

Information confirming the possibility of carrying out the invention with obtaining the indicated result of the proposed gas turbine engine device is as follows:

The volume of the cylinder cavity must be such that after the air is forced out of it into the combustion chamber, the pressure of this air is sufficient to ignite the injected dose of fuel. The ends of the piston in one of the extreme positions in the cylinder should be located in close proximity between the extreme outlet and the second outlet closest to it from the cylinder. The piston must be of extremely low weight. Both ends of the cylinder should have buffer cavities and pressure sensors.

The coordinated operation of the GTE units can be carried out using an electronic control unit and with the necessary sensors.

The 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.

Starting the GTE can be carried out after the compressor spins up, for example, using a starter.

When working with different types of fuels, the required compression ratio in the combustion chamber can be controlled by changing the pressure at the compressor outlet. The ignition of a poorly flammable working mixture before the start of the working stroke can be carried out with the necessary advance for its complete combustion. An increase in GTE power can be achieved by increasing the number of CS pairs connected to the turbine inlets.

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

A rotary-vane device can be used as a turbine.

Sources of information

1. Patent RU 2066383С1. Detonation internal combustion engine. IPC F02B71/04.

2. Patent RU 2495262С2. A method for creating a multi-cylinder liquid internal combustion engine and an engine. IPC F02B75/00, F01B11/08, F02B71/04.

3. Patent RU 2516044С2. Rotary piston engine. IPC F02B55/02, F01C1/356, F02B19/02, F16J15/40.

Claims (1)

A gas turbine engine containing a control unit; two alternately operating combustion chambers with fuel injectors and spark plugs; a compressor, the output of which is connected through locking devices to the inlets of the first and second combustion chambers, the outlets of which are connected through the locking devices, respectively, to the first and second inlets to the turbine, characterized in that it additionally contains a cylinder with a freely moving piston, four cylinder outlets are connected respectively to the first a combustion chamber with a first turbine inlet, a second turbine inlet and a second combustion chamber.

Images