RU2263805C2 - Gas-turbine engine - Google Patents

Abstract

FIELD: mechanical engineering; internal combustion engines.

SUBSTANCE: gas-turbine internal combustion engine with combustion of explosive mixture getting through nozzle arranged around turbine blades in engine housing in constant volume, contains, according to invention, a turbine installed on shaft in combustion chamber, engine housing with nozzles and deflectors. Turbine is made in form of blades installed at angle and connected by ring over outer tips. Vent ports are located in central part of engine. Combustion chamber accommodates ring with blades. Said blades are made in form of pyramids lying by sides on ring surface with tips pointed in direction of rotation of turbine, and with flat bases-working surfaces installed square to and across outer surface of ring.

EFFECT: improved explosion safety of engine.

6 dwg

Description

The field of technology.

The invention relates to mechanical engineering. Its use is possible as an engine on all types of transport and in industry.

The level of technology.

Known gas turbine installation with the combustion of fuel in a constant volume (patent RU 2147341 C1, 7 F 02 C 5/12, 2000), where the gases from the combustion chamber to the turbines are fed through nozzles. In nozzles, gases gain speed and expand. The gas temperature at the end of the expansion drops, which creates the necessary conditions for the operation of the turbine.

The disadvantage of this engine is the practical impossibility of its application, because the fuel burned in the combustion chamber mainly creates only temperature, but not enough pressure to operate the turbine, and even compressors.

A gas turbine internal combustion engine is known with constant volume combustion of the explosive mixture, comprising a turbine installed in the engine housing on the shaft, the blades of which are located in the combustion chamber, where, through nozzles located around the blades and having continuously operating ignition, an explosive mixture is fed with synchronous shut-off, with the direction of the pressure obtained on the turbine blades and reflectors (patent FR 1538421, IPC F 02 B 53/00, 1968).

The disadvantages of this engine are the rounded shape of the blades in the form of recesses in the turbine housing, which dramatically reduces the efficiency of gas pressure in the direction of rotation of the turbine, because gases press equally in all directions, and the impossibility of arranging more blades due to their shape in such an all-metal turbine.

The closest to the proposed invention is essentially a gas turbine internal combustion engine with constant volume combustion of the explosive mixture flowing through nozzles located around the turbine blades in the engine housing, comprising a turbine mounted on a shaft in the combustion chamber, an engine housing with nozzles and reflectors, this turbine is made in the form of blades mounted at an angle and connected at the outer ends by a ring, ventilation windows are located in the central part of the engine, while in the chamber for combustion, a ring with blades is located, and the turbine shaft and bearings are installed outside the combustion chamber (patent FR 867003, NKL. Cr. 5-CL. 8, 1940

The disadvantages of this engine are the shape of the turbine blades, which in fact can only use part of the pressure efficiency of gases that press in all directions with the same force, and the reverse side of the blades is designed so that about half of the gas pressure efficiency will inevitably press the blades in the direction opposite to the rotation of the turbine , even if there are reflectors in the combustion chamber, and the combustion chamber, with such a device of the blades, as such, no. It is formed only by the spaces between the blades, which essentially serve as several separate combustion chambers in the absence of sufficient space between the blades and the inner surface of the combustion chambers. In addition, when the mixture is ignited when it enters the nozzle, the entire explosive mixture burns in the nozzles, forming a jet stream of gases that press only on some of the blades, and not all at once, if the mixture exploded in the entire combustion chamber if it was present. The specified device of the blades reduces the efficiency of the engine, in addition, it has a huge counter gas resistance during rotation of the turbine. The explosion safety of the engine from accumulation of unburned gases is also not ensured.

SUMMARY OF THE INVENTION

The objective of the invention is to increase the efficiency of gas pressure on the turbine blades, reduce the resistance of the turbine blades to counter gases during rotation of the turbine, simultaneously explode the explosive mixture in the entire combustion chamber, maximize the gas pressure on the working surfaces of the turbine blades, continuously operating ignition with late switching on and ensure the engine explosion safety.

The problem is solved due to the fact that in a gas turbine internal combustion engine with combustion in a constant volume of explosive mixture flowing through nozzles located around the turbine blades in the engine casing containing a turbine mounted on a shaft in the combustion chamber, the engine casing with nozzles and reflectors, the turbine is made in the form of blades mounted at an angle and connected at the outer ends by a ring, ventilation windows are located in the central part of the engine, and a combustion chamber is located a ring with the blades, the blade according to the invention are in the form of pyramids lying side faces on the surface of the ring vertices a turbine rotational direction and flat bottoms - work surfaces mounted perpendicular to and across the outer surface of the ring.

The manufacture of blades in this form provides free rotation of the turbine with a sufficient gap between its blades and the inner surface of the combustion chamber without significant impact on efficiency, and the resulting combustion chamber due to the free space between the blades due to their shape and the space between the surface of the blades and the inner surface of the chamber combustion allows you to ensure the explosion of the entire explosive mixture in the entire combustion chamber simultaneously with the simultaneous pressure of gases on all the blades at once, which will significantly increase Efficiency. Continuous late ignition is triggered at the end of the mixture injection into the nozzles when the explosive mixture has already entered the combustion chamber, but it is valid until the mixture enters the nozzles to ignite the remaining gases. Such ignition and prevention of engine explosion from the accumulation of gases is called late.

The streamlined shape of the blades from the non-working side provides minimal resistance to their gases during rotation of the turbine. Pyramids can be with three faces.

The novelty and significant differences of the invention are in the manufacture of turbine blades in the form of pyramids, reducing the resistance of the blades during rotation of the turbine, the maximum gas pressure on all blades at the same time, the explosion of fuel in the entire combustion chamber at the same time, ignition of fuel at the end of the injection, afterburning of fuel.

A gas turbine internal combustion engine with combustion in a constant volume of explosive mixture consists of a housing 1, a combustion chamber 2, nozzles 3, reflectors 4, a shaft 5, a turbine 6, turbine blades 7, turbine blades 8, ventilation windows of the housing 9, cooling system 10, gas pipelines 11, distribution capacity 12, cylinders with compressed air and gas 13, throttles 14, continuously operating ignition 15, synchronous shutoffs 16, turbine rings 17, turbine hubs 18.

The gas turbine engine operates as follows.

From the cylinders 13 through the chokes 14, compressed air and gas enter the distribution tank 12, where they form an explosive mixture. This mixture through gas pipelines 11 enters the nozzles 3 and the combustion chamber 2. At the end of the explosive mixture, a continuously operating ignition 15 is triggered. As a result of the explosion of the mixture, gas pressure occurs on all turbine blades simultaneously. Cutters 16 provide a uniform, metered flow of the mixture. When the gas pressure on the blades 7, the turbine 6 rotates the shaft 5, at the same time draws the exhaust gases and cools the engine with blades 8 through the windows 9. Reflectors 4 direct the gas pressure to the working surfaces of the blades. The cooling system 10 prevents overheating of the engine. Shaft 5 with thrust bearings is located in the cooling zone, and in the combustion chamber there is only a ring 17 with blades 7. The engine housing 1 consists of two longitudinal halves, fastened with 3 ÷ 5 bolts.

The optimal explosive mixture is air-hydrogen.

The manufacture of the engine is possible at any enterprise with a foundry of metal. The engine is easy to manufacture, reliable in operation, the efficiency is higher than piston engines, the power is higher than piston engines due to the simultaneous gas pressure on all turbine blades and due to the larger shaft rotation lever: for piston engines it bent with a rotation lever of about 50 mm, for a turbine - 500 mm and more plus the absence of friction losses of the pistons.

Figure 1 - schematic illustration of the engine from the side;

figure 2 is a partial transverse section of the engine;

figure 3 - cylinders with gases, throttles, gas pipelines;

figure 4 is a view of a turbine, blades from the side;

figure 5 is a top view of the blades on the turbine ring;

6 is a cross-sectional view of a turbine.

Claims (1)

A gas turbine internal combustion engine with constant volume combustion of the explosive mixture flowing through nozzles located around the turbine blades in the engine housing, comprising a turbine mounted on a shaft in the combustion chamber, an engine housing with nozzles and reflectors, the turbine being made in the form of blades mounted at an angle and connected at the outer ends by a ring, ventilation windows are located in the central part of the engine, a ring with blades is located in the combustion chamber, characterized in that the blade Ki are in the form of pyramids lying side faces on the surface of the ring vertices a turbine rotational direction and flat bottoms - worktops installed perpendicularly and transversely to the outer surface of the ring.

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