RU2572258C2 - Process for increasing gas turbine engine efficiency and gas turbine engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: claimed gas turbine engine comprises the air channel including the air intake and at least one compressor stage, combustion chamber, gas turbine, at least one shaft engaging the compressor and gas turbine, jet nozzle and fuel feed system. Said gas turbine engine includes the air activator arrange outside the engine and its inlet is communicated with the compressor outlet while activator outlet is communicated with the combustion chamber.

EFFECT: enhanced power output.

19 dwg

Description

The invention relates to engine building, specifically to aircraft engines for civilian, military, subsonic and supersonic and hypersonic aircraft.

Known hydrogen gas turbine engine according to the patent of the Russian Federation for the invention No. 2029118, IPC F02C 3/04, publ. 05/20/1995, with an auxiliary circuit operating on hydrogen, an additional air path was introduced into the auxiliary circuit, connecting the outlet from the free compressor with the auxiliary chamber. Hydrogen in the engine circuit acts as a refrigerant. To cool the turbine of the main circuit, high-pressure air is used, which, after cooling the turbine, is supplied to the intermediate overheating combustion chamber, where liquefied air enters the gaseous state at the same time.

The disadvantage is the low specific characteristics of the engine due to the low degree of air compression in the compressor.

Known hydrogen gas turbine engine according to the patent of the Russian Federation for the invention No. 2320889, IPC F02K 3/04, publ. 03/27/2008, which contains a fan, a high-pressure high-speed compressor, a multiplier, a steam-water heater (steam generator), an afterburner, a turboexpander with a heat and mass transfer apparatus. The engine also has a three-stage active-jet turbine, in which the third stage is radial-axial, the flow part of which passes into the critical supersonic section of the Laval nozzle, surrounded by a steam accumulator. The high-pressure high-speed compressor is combined with a pressure increase of 60. The engine is designed for thrust of at least 150 tons with an air flow through the first circuit of 600 kg / s, through the second circuit - 1200 kg / s, the gas temperature in front of the turbine is 2000 K. The fan has the outer diameter of the blades of the first row is 4000 mm. Inside the housing of the Laval nozzle, atomic hydrogen injectors are installed to burn the unburned oxidizer. The disks of a high-pressure high-speed compressor are made combined - centrifugal pumps are added to the axial steps. The Laval nozzle is provided with a central body, through the openings of which a steam-air mixture is created, creating an external elastic “shell-pillow”, which allows changing the area of the critical section of the Laval nozzle through passage.

Disadvantages:

- low level of traction at maximum mode, relatively low specific parameters, for example specific fuel consumption, insufficient compression ratio of the compressor;

- the high cost of hydrogen fuel (the cost of hydrogen is more than 100 times the cost of hydrocarbon fuel - aviation kerosene);

- large volumes of fuel tanks of hydrogen fuel due to the low density of hydrogen (the density of hydrogen is about 10 times lower than the density of hydrocarbon fuels);

 - low specific parameters are explained by the fact that it is impossible to create a compressor with a compression ratio of more than 30 ... 40, due to the fact that the air temperature at its outlet exceeds 800 ° C. In addition, the energy potential of a gas turbine is not enough to drive a more powerful compressor due to gas temperature limitations at the turbine inlet range 1700 ... 1800K, primarily due to a decrease in the resource of the gas turbine blades with increasing temperature. The working blades of a gas turbine are on a large diameter, rotate at huge peripheral speeds, therefore, they are subject to significant centrifugal loads. The strength properties of materials with increasing temperature deteriorate;

- a significant decrease in traction or complete inoperability of the engine at very high altitudes due to lack of air.

A well-known gas turbine engine (Kulagin II. Fundamentals of the theory of aviation gas turbine engines, Moscow, Military Publishing House of the Ministry of Defense of the USSR, 1967, pp. 42 ... 44, Fig. 19), prototype.

This engine contains an air path, which in turn contains an air intake and at least one compressor stage, a combustion chamber, a gas turbine, at least one shaft connecting the compressor and the gas turbine, a jet nozzle and a fuel supply system.

Disadvantages: relatively low specific characteristics of the engine as specific thrust, efficiency of units due to incomplete combustion of fuel.

In almost all engines, up to 5% of the fuel does not burn. Theoretically, it is possible to increase the completeness of fuel combustion in the combustion chamber by another 2 ... 3%, but this will lead to an increase in the dimensions of the combustion chamber and an increase in engine weight.

Objectives of the invention: increasing the energy capabilities of a gas turbine engine and improving its specific characteristics.

Achieved technical results: increasing the compression ratio of the compressor, increasing the traction force of the engine and improving its specific characteristics.

The solution of these problems was achieved in a gas turbine engine containing an air path, which, in turn, contains an air intake and at least one compressor stage, a combustion chamber, a gas turbine, at least one shaft connecting the compressor and the gas turbine, a jet nozzle and fuel supply system

that an air activator is used, which is installed outside the engine, and its input is connected to the outlet of the compressor, and the output of the air activator is connected to the combustion chamber.

The invention is illustrated in FIG. 1 ... 19, where:

- in FIG. 1 shows a diagram of a gas turbine engine with an air activator installed in the air intake,

- in FIG. 2 shows a diagram of a gas turbine engine with an air activator installed behind the compressor,

- in FIG. 3 shows a diagram of a gas turbine engine with an air activator installed between the compressor stages,

- Figs 4 and 5 show a diagram of a radial installation of electrodes,

- in FIG. 6 and 7 show a diagram of the parallel installation of electrodes,

- in FIG. 8 and 9 show a diagram of a cantilever radial installation of electrodes,

- in FIG. 10 and 11 show a diagram of a console parallel installation of electrodes.

- in FIG. 12 shows the design of the section of two electrodes,

- in FIG. 13 shows a section aa, the first option,

- in FIG. 14 shows a section aa, the second option,

- in FIG. 15 shows a section aa, the third option,

- in FIG. 16 shows a diagram of a gas turbine engine with an air activator mounted outside the engine,

- in FIG. 17 shows the design of the remote ionizer,

- in FIG. 18 shows the combustion chamber,

- in FIG. 19 shows a second embodiment of a combustion chamber.

The proposed gas turbine engine (Fig. 1 ... 19) contains an air path 1, which in turn contains an air intake 2, a compressor 3, a combustion chamber 4, a turbine 5 and a jet nozzle 6. The jet nozzle 6 is preferably supersonic.

The compressor 3 contains several stages 7, each of which contains a guide apparatus 8 and an impeller 9. The turbine 5 contains at least one stage 10. Each stage 10 comprises a nozzle apparatus 11 and an impeller 12. The combustion chamber 4 contains a heat pipe 13, an atomizer a plate 14 with nozzles 15 for supplying fuel. The construction of the combustion chamber 4 is described in more detail below with reference to FIG. 5. The shafts 16 and 17 connect the impellers 9 of the compressor 3 and the impellers 12 of the turbine 5 and are mounted on supports 18.

A feature of the proposed gas turbine engine is the presence of an air activator 19. In this case, installation in the air path 1 (Fig. 1 ... 3) or outside the engine (Fig. 18 and 19) is possible. In addition, an electric generator 22 is connected to the shaft 16 through a reducer 20 by a selection shaft 21, which is connected by electrical connections 23 to a high voltage source 24, which is connected by high voltage wires 25 to an air activator 19, more precisely, to its electrodes 26 and 27. The high voltage source 24 is designed 20 ... 30 kV.

Depending on the voltage between the electrodes 26 and 27 and the distance between them, ions or ozone or a mixture of them will form in the air.

Ozone

, «пахну») - простое вещество состава О₃, одно из аллотропических видоизменений элемента кислорода. В отличие от наиболее распространенной в атмосфере Земли молекулярной формы, кислорода О₃, молекула озона состоит из трех атомов. Чистый озон при обыкновенных условиях представляет из себя резко пахнущий взрывчатый газ, в толстом слое синего цвета, обладает сильнейшими окислительными свойствами.Ozone (O ₃ ) (from Greek

, “I smell”) - a simple substance of composition O ₃ , one of the allotropic modifications of the oxygen element. Unlike the most common molecular form in the Earth’s atmosphere, oxygen O ₃ , the ozone molecule consists of three atoms. Under ordinary conditions, pure ozone is a sharp-smelling explosive gas, in a thick layer of blue, has the strongest oxidizing properties.

Discovery story

The history of the discovery of ozone is rather vague, and in general a number of scientific encyclopedias provide various authors of the discovery of ozone. Currently, the scientific community has accepted that ozone was first found at the beginning of 1785 by Van Marum, according to the characteristic odor and oxidative properties found in air, after prolonged transmission of electric sparks in the latter. Van Marum concluded that ozone is the so-called “electrical matter”.

In 1840, Schonbein compared the properties of gaseous oxygen when electric sparks passed through it, and after it was electrolytically isolated, and explained the change in the physical and chemical properties of the altered oxygen by the fact that when it is processed by electric sparks, it goes into a different molecular state.

Later, Marignac and de la Reeve confirmed that ozone is an allotropic modification of oxygen. Later, the well-known inventor Nikola Tesla patented (September 22, 1896) the first ozonizer in history, and in 1857 Werner von Siemens built the first industrial ozonizer using the “perfect magnetic induction tube” he created. In 1901, Siemens built the first hydroelectric station with a powerful ozonizer in Wiesband.

Physical properties

- Boiling point: -111.9 ° C

- Critical temperature: -12.1 ° C

- Decomposition start temperature:

- Heat of formation (liquid) (kcal / mol): +30.4

- Heat of formation (gas) (kcal / mol):

- Heat of fusion (kcal / mol): 0.5

- Heat of vaporization: (kcal / mol): 3,626

- Critical pressure, 54.6 atm:

- Density:

- Density is critical:

Ozone is well soluble in water (under normal conditions, 0.45 volume / 1 volume of water) and at the same time its aqueous solution acquires a thin bluish color. Ozone is much better dissolved in various chlorine and fluoro derivatives of hydrocarbons (freons), for example, under normal conditions, 3 volumes of ozone / 1 volume are dissolved in carbon tetrachloride and the solution has a beautiful and saturated blue color.

Chemical properties

The formation of ozone passes through a reversible reaction:

3O ₂ +68 kcal (285 kJ) ← → 2O ₃ .

Ozone is a very reactive chemical substance, the chemical activity of which is extremely high. This property is due to the fact that the triatomic ozone molecule is capable of light decomposition and additional energy release (ozone is endothermic). The released oxygen atom has an extremely high activity, enhanced by additional energy. So, for example, at room temperature, ozone interacts with almost all chemical elements and their chemical compounds. Under the action of gaseous ozone, all metals except Au, Pt, Ir are converted to oxides or covered with a thin oxide film, sulfides, selenides, tellurides are oxidized to sulfates, selenates, tellurides, ammonia is oxidized to nitrous and nitric acids, etc. Rubber is extremely rapidly destroyed by ozone (embrittlement and crumbles into powder), and many combustible organic substances (alcohols, ketones, hydrocarbons, etc.) ignite or explode in contact with ozone. After some surface oxidation, Cu, Ni, Sn, as well as carbon-free alloys of iron with 25% chromium are quite resistant to ozone. Bacteria, fungi and viruses, when interacting with ozone, are completely destroyed, which is widely used to disinfect a wide variety of environments. In the presence of small amounts of HNO _3, ozone is stabilized, and in sealed containers of glass, some plastics or pure metals, ozone practically does not decompose at low temperatures (-78 ° C).

In more detail, the design of the activator is shown in FIG. 4 ... 11. The activator 19 contains, in addition to the electrodes 26 and 27, an internal dielectric casing 28 and an external dielectric casing 29 mounted inside the motor casing 30. In this case, the electrodes 26 and 27 can be installed radially (Fig. 4 and 5) or in parallel (Fig. 6 and 7). The electrodes 26 and 27 can be made radial and cantilever (Fig. 8 and 9) or parallel and cantilever (Fig. 10 and 11).

The electrodes 26 and 27 can be made in the form of parallel plates with sharp edges 31 (Fig. 12), or in the form of rhombs (Fig. 13), or in the form of streamlined profiles (Fig. 14). The electrodes 26 and 27 form a section that is mounted on the tides on the housing 20 using the cover 32 of an insulating material (Fig. 15). The sharp edges 31 contribute to the activation of the electric discharge process.

The jet engine (Fig. 1) contains a fuel supply system. The fuel supply system includes a tank 33 for storing fuel, a low pressure fuel line 34 connected to the outlet of the tank 33. A pump 35, a high pressure fuel line 36, a flow regulator 37, and a shutoff valve 38 are connected to the low pressure fuel line 34.

The second version of the gas turbine engine (Fig. 16) with a remote activator further comprises an air sampling pipe 39 connected to the outlet of the compressor 3, connected to an air activator 19, the outlet of which is connected by a pipe 40 to the combustion chamber 4.

The design of the remote activator 19 is shown in FIG. 17. The air activator 19 comprises a cylindrical body 41 of dielectric material, to which the inlet and outlet pipes 42 and 43 are connected. In the chamber 44, the electrodes 26 and 27 are mounted on the holders 45 and 46.

The combustion chamber 4 for the second version of the gas turbine engine with an external air activator 19 (Fig. 18) contains a flame tube 13, nozzle pita 14 and nozzles 15. Two collectors 47 and 48 are installed on the nozzle plate 14. Nozzles 15 are connected to the collector 47, and to the collector 48 — nozzles of ionized air or ozone 49. An inner casing 50 is installed under the flame tube 13, forming an inner channel 51 with the flame tube 13. An external channel 53 is formed between the housing 52 of the combustion chamber 4 and the flame tube 13. Holes 54 are made in the flame tube 13.

A variant is possible (Fig. 19), when air with an admixture of ions and ozone is supplied in front of the nozzle plate 14.

Possible execution of the jet nozzle 6 supersonic. This is suitable for supersonic aircraft.

ENGINE OPERATION

When the gas turbine engine (Fig 1 ... 19) carry out its launch by supplying electricity to the starter from an external energy source (in Fig. 1 ... 19 the starter is not shown).

Then turn on the pump 21 (Fig. 1), and the fuel from the tank 33 through the low pressure pipe 34 is supplied to the pump 35 and then through the high pressure pipe 36 is supplied to the nozzles 15 of the combustion chamber 4.

At the same time, air from the atmosphere enters the air duct 1 and passes through an air activator 19, in which ions and / or ozone are formed depending on the voltage at the output of the high voltage source 24. Ions and / or ozone generated due to discharges between the electrodes 26 and 27 of high voltage supplied by high voltage wires 25.

In the presence of an external air activator 19, part of the air consumed by the engine passes through it (Figs. 18 and 19).

A mixture of air with ionized air (and / or ozone) and fuel enters the combustion chamber 4. It is taken into account that ionized air and ozone have higher oxidizing properties, the fuel burns out more fully, and during combustion a higher temperature of the combustion products is formed. This increases its energy potential on the turbine 5 and the jet nozzle 6. Given that the temperature of the combustion products at the inlet of the turbine always has a design limit, it is possible to reduce fuel consumption to maintain a given temperature. This will save 3 ... 5% of fuel.

The application of the invention allowed:

1. To increase the efficiency of a gas turbine engine due to a more complete combustion of hydrocarbon fuel.

2. Reduce the amount of carbon - C and carbon oxides - CO in the exhaust.

3. Ensure engine performance at very high altitudes through the use of ionized air or ozone.

4. At maximum (afterburner) modes when flying at hypersonic speeds, increase the compression ratio of the compressors of the gas turbine engine through the use of complete combustion of fuel.

5. Ensure that aircraft equipped with these engines achieve hypersonic speeds M = 3 ... 6.

6. Reduce the cost of flying an aircraft by using cheaper hydrocarbon fuels.

Claims (1)

A gas turbine engine comprising an air path, comprising in turn an air intake and at least one compressor stage, a combustion chamber, a gas turbine, at least one shaft connecting the compressor and the gas turbine, a jet nozzle and a fuel supply system, characterized in that it contains an air activator, which is installed outside the engine, and its input is connected to the outlet of the compressor, and the output of the air activator is connected to the combustion chamber.

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