RU2055996C1 - Gas-turbine engine - Google Patents

Abstract

FIELD: manufacture of automobiles. SUBSTANCE: located on cylinder bottom wall are fuel feeding device and electric spark generating source. Nozzle unit is mounted on shaft of gas-turbine engine and is made in form of diaphragm with nozzle openings. EFFECT: enhanced reliability. 1 dwg

Description

 The invention relates to gas turbine engines. This engine can be used where piston carburetor or gas internal combustion engines are currently used: in cars, light aircraft, and small-sized power plants.

 Carburetor and gas piston internal combustion engines are well known. The main structural element of these engines is one or more cylinders with pistons connected by a crank mechanism with a crankshaft. At the bottom of each cylinder there are valves for fuel inlet in the form of gasoline vapors mixed with air, or a mixture of combustible gas with air. At the bottom of each cylinder, valves are also made for the release of exhaust gaseous products of fuel combustion. Ignition of the fuel is carried out by an electric spark using a device called a candle installed in the bottom of each cylinder.

 The disadvantage of carburetor and gas reciprocating internal combustion engines is their complexity, which is due, in particular, to the presence of a crankshaft and crank mechanism, which makes the engines cumbersome.

 Also known devices, called gas turbine engines, adopted as a prototype, in which gaseous or light liquid fuel (for example, kerosene) is continuously burned in the combustion chamber during operation, and the resulting gaseous products of fuel combustion with high temperature are directed to the blades of a gas turbine, which makes mechanical work.

 The disadvantage of gas turbine engines is that it is economically advantageous to use them only in high-power devices: in the engines of large aircraft, ships, railway locomotives and for driving compressors when pumping gas or oil through gas and oil pipelines. They are also used in power plants to obtain the missing energy during peak loads.

 A big drawback of gas turbine units is that they usually have a lower efficiency compared to internal combustion engines of 14-18% for simple gas turbine units and 27-37% for multistage gas turbine units with a heat recovery system for heating the air used to burn fuel.

The insufficiently high efficiency is due to the fact that the temperature of the gas entering the gas turbine blades in stationary installations usually does not exceed 750-1100 ^о С, since at higher temperatures the turbine blades cannot work for a long time.

 The aim of the invention is to increase the efficiency of a gas turbine engine while simplifying its design.

 This is achieved due to the fact that in a gas turbine engine containing a combustion chamber with a device for supplying fuel to it, a turbine with a nozzle assembly mounted on the engine shaft, the combustion chamber is made in the form of a cylinder and the engine is equipped with a source of electric spark formation, while on the wall of the cylinder bottom a device for supplying fuel and a source of electric spark are placed, and the nozzle assembly is located on the engine shaft and is made in the form of a diaphragm with nozzle openings.

 The essence of the invention lies in the fact that in the working cylinder of a carburetor or gas internal combustion engine, instead of a piston, a gas turbine (or a cascade of two or three turbines) is installed, the shaft of which is located along the axis of the cylinder. In this case, one end of the shaft is brought out through the bearing in the center of the bottom of the cylinder and connected to the device driven by the engine through the coupling, and the other end of the shaft is mounted in the bearing of a special diaphragm installed inside the cylinder, with holes directing the gaseous products of fuel combustion to the gas blades turbines.

 The advantage of this engine compared to the well-known gas turbine is the possibility of burning fuel at a higher temperature, since during a short explosive combustion of fuel the gas turbine blades and the engine shaft do not have time to warm up to high temperature, similar to how the piston does not have time to warm up in the cylinder of an internal combustion engine and during the subsequent inlet of the combustible mixture into the combustion chamber, the blades of the gas turbine will be able to cool.

 A higher combustion temperature makes it possible to realize greater efficiency than a previously known gas turbine engine and make it such as that of an internal combustion engine. In addition, this makes it possible to simplify the design of a gas turbine engine, since a system of heating the air with fuel combustion products is not required to obtain a sufficiently high efficiency. As a result, at the same power, the weight of the engine decreases.

 The design of the proposed gas turbine engine is also significantly simpler than that of traditional internal combustion engines due to the lack of a crank mechanism and crankshaft.

 The drawing shows a diagram of the proposed gas turbine engine, a longitudinal section.

 The engine consists of a cylinder 1 with a bottom 2, in which valves 3 and 4 are made for the intake of vapors of gasoline and air or combustible gas mixed with air through nozzles 5 and 6 from the carburetor. One valve 3 or 4 is enough for the engine to work, but several valves provide a more uniform distribution of fuel throughout the volume of cylinder 1. At the bottom of cylinder 2, a device 7 for igniting fuel with an electric spark is installed. The shaft of the engine 8 is installed along the axis of the cylinder 1 and is fixed at one end in the bottom 2 of the cylinder by means of the bearing 9 and the second end in the diaphragm 10 with the bearing. Openings 11 are made in the diaphragm 10 through which the gaseous products of fuel combustion are sent to the blades of a gas turbine 12 mounted on the shaft 8. To divert the products of fuel combustion from the engine into the environment, the open end 13 of cylinder 1 is used. In order to ensure more uniform rotation even on the shaft 8 of the engine, a flywheel can be installed 14. The connection of the shaft 8 of the engine with the device driven by the engine in motion is carried out by the coupling 15.

 The operation of the engine is as follows.

 Inside the cylinder 1 through the nozzles 5 and 6 and the open valves 3 and 4 from the carburetor, vapor of liquid fuel (gasoline) or gas mixed with air is admitted. Next, the valves 3 and 4 are closed and the fuel mixture is ignited with an electric spark through the candle 7. The fuel burns out almost instantly, and the gaseous combustion products formed inside the cylinder 1 with high temperature and high pressure through the nozzle openings in the diaphragm 11 rush to the blades of the gas turbine 12 and lead its movement, as a result of which the rotation of the engine shaft 8 begins. Instead of a single gas turbine, a cascade of two or three turbines can be used. For this, after the first turbine, a similar second diaphragm with holes and a second gas turbine, etc. are installed.

 From a gas turbine, the combustion products of the fuel exit into the environment through the open end of the cylinder 13.

 After combustion of the first portion of fuel, valves 3 and 4 reopen and a new portion of the mixture of fuel and air is fed, and so the engine duty cycle is repeated an unlimited number of times. The operation of valves 3 and 4 and the device for igniting fuel with an electric spark is carried out in the same way as in carburetor piston internal combustion engines.

 For a more uniform rotation of the shaft of the engine 8, a flywheel 14 can be used, but the flywheel is not necessary, since its role is played by a gas turbine 12.

 Starting the proposed engine, as well as a piston carburetor, can be carried out using a starter that provides initial rotation of the engine shaft.However, if a special device is provided for autonomously starting the first portion of fuel and air through valves 3 and 4, then a traditional starter is not required.

 Since the combustion of fuel in the cylinder of the proposed engine occurs periodically, as in an internal combustion engine, the maximum allowable temperature of the gases entering the blades of the gas turbine can be much higher than in the prototype gas turbine engine. This leads to a significant increase in efficiency, which will become close to the efficiency of economical piston internal combustion engines. Since this does not require a system for preheating the air entering the combustion chamber with fuel combustion products, the design of the gas turbine engine will be greatly simplified and its weight reduced.

 Compared to the widely used internal combustion engine, the advantage of the proposed gas turbine engine is its simplicity of design and compactness. Therefore, the new engine will be widely used where piston carburetor or gas internal combustion engines are currently used. In particular, this engine can be used on cars, light aircraft and small-sized power plants.

Claims (1)

 A gas-turbine engine containing a combustion chamber with a device for supplying fuel to it, a turbine with a nozzle assembly mounted on the engine shaft, characterized in that the combustion chamber is made in the form of a cylinder, the engine is equipped with a source of electric spark formation, and a device for fuel supply and an electric spark generating source, and the nozzle assembly is located on the engine shaft and is made in the form of a diaphragm with nozzle openings.

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