RU190146U1 - TWO-HEATING DOUBLE-CIRCUIT NOZZLE OF GAS TURBINE ENGINE - Google Patents

Abstract

Dual-fuel dual-circuit nozzles of a gas turbine engine includes a housing with fittings and channels for supplying gaseous and liquid fuels, an air supply channel, a gaseous and liquid fuel atomizer, a conical swirler, and spray nozzles. The channel for supplying air is located along the channels for supplying gaseous and liquid fuels, connected to the inlet air inlet and outlet air nozzle, and is also equipped with an air filter. The nozzle includes a means of blowing and protection against the formation of carbon on the end surface of the dispenser. The invention is aimed at improving the efficiency of the nozzle, by improving the mixing of fuel with air and protection against the formation of carbon during operation in the dual-fuel mode. 2 з.п f-ly, 3 ill.

Description

The technical field to which the utility model belongs.

The utility model relates to devices with direct injection of a liquid hydrocarbon fuel in a drop state or gaseous hydrocarbon fuel into the combustion chamber of a gas turbine engine and preparation of an air-fuel mixture for combustion in the combustion zone using air, namely, dual-fuel dual-circuit nozzles of a gas turbine engine containing a housing with fittings and gaseous and liquid fuel supply channels, air supply channel, gaseous and liquid fuel atomizer, conical swirl, spray nozzles.

Abbreviations used in the description

GTD - gas turbine engine

GTU - gas turbine unit

GTP - gas turbine drive

The level of technology.

An urgent task is the creation of combustion chambers of ground-based gas-turbine installations (GTU) of low power, which can launch and operate on both gaseous and liquid fuels, ensuring the possibility of switching between fuels without the need to stop the CCD. The need to solve this problem is caused by the need to ensure a continuous process of energy supply, including in the event of interruptions in the supply of gaseous fuel.

Known burner for burning liquid and gaseous fuels [RF patent №2039320, F23D 17/00, publ. 09.07.1995], comprising a housing, a liquid fuel nozzle, an internal gas supply pipe with outlets. The air feed shell has a conical perforated partition at the outlet with an opening angle of at least equal to the opening angle of the torch of the liquid-fuel nozzle. The outer channel is formed by the shell and the housing and communicates with the gas collector through the holes. An annular corner stabilizer is installed in the outer shell of the front part of the channel, forming a cavity with the shell. The partition has openings, and the shell - the window for the exit of the air entering the shell. The shell together with the stabilizer has the possibility of axial movement relative to the body. The known device cannot be used in the GTR due to its large size, low efficiency of work as part of the GTR. The disadvantage is, as indicated in the patent itself, the insufficient stability of the torch when working on fuel oil, therefore it is designed to work on gas.

Known gas-liquid nozzle of a gas turbine engine PA patent of the Russian Federation for Useful model No. 151160, F23D 11/38, publ. 03/20/2015 Lul. No. 8, comprising a housing with a liquid fuel atomizer disposed therein, a hollow nozzle including an inlet and an outlet part installed outside the case and provided with openings for gaseous fuel, the inlet part of the nozzle being associated with the case, the outlet part of the nozzle is made in the form of a truncated cone. Provides a supply of liquid and gaseous fuel in different areas of the swirler of the flame tube, which eliminates the ingress of liquid fuel in the gas fuel nozzle openings

The disadvantages of the nozzle include the absence of a central air channel, which provides the best mixing of liquid fuel with air and, accordingly, improves the combustion efficiency.

Known burner [RF patent №2197685, F23D 17/00, 27.01.2003], designed for burning fuel, mainly in the combustion chambers of the gas turbine. The burner contains an air swirler with blades and, communicating with the fuel supply channel, a gas distributing nozzle with gas distributing holes located between the air swirler blades. Gas distribution nozzles have an additional row of gas distribution holes located in front of the air-swirler blades. In addition, the burner can be additionally equipped with a nozzle of liquid fuel installed on the axis of the burner.

The disadvantages of this device are the low efficiency of the nozzle on the liquid fuel due to fuel injection into the combustion zone without prior preparation, and a small spray angle, as well as the presence of a bulky blade air swirl.

Known fuel nozzle of the combustion chamber of a gas turbine engine [patent RU 182454 U1, F23R 3/14 (2006.01), 08.17.2018], intended for use in the fuel injectors of the combustion chambers of a gas turbine engine. The nozzle includes a housing, sprays and a casing enclosing the casing with the formation of an end gap communicated with an air source, the casing and the casing form a connection, an annular groove is made in the casing, and an insert is installed on the casing; longitudinal grooves, which communicate the cavity of the annular groove with the annular channel under the casing, from the air inlet side into the cavity of the casing groove under the insert, the connection of the casing and the body is made with a gap, and side air outlet connection is made with an interference fit, profiled inserts racks consist of the straight portion and set at an angle to the axis of the nozzle portion.

The disadvantages of this device are the absence of an air filter in the nozzle, which does not provide an adequate level of protection against the ingress of contaminants into the air-fuel mixture, and the presence of a single air outlet that does not provide a sufficient level of protection against carbon formation on the end surface of the atomizer.

The well-known dual-fuel nozzle [RF Patent No. 2578785 C1, F23D 17/00, F23R 3/36, 10/27/2014] intended for injecting liquid fuel or gaseous hydrocarbon into the combustion chamber of a gas turbine engine. The nozzle axis is concentric with the fuel supply channels, the central air supply channel is made, and the liquid fuel supply channel is additionally equipped with a nozzle, which is connected to the central air supply channel and is made with the possibility of centrifugal spin of the fuel. In the body of the casing there are oblique grooves, which create a turbulence zone in the nozzle cavity of the casing. Gas distribution holes are made with the ability to supply gaseous fuel in the zone of turbulence, as well as in the combustion zone, bypassing the zone of turbulence and a nozzle hole.

This nozzle for most of the essential features adopted for the prototype of the claimed utility model.

The disadvantages of this device are:

 - low quality spray of liquid fuel and does not provide the required level of protection against carbonization when using liquid fuels of high viscosity (fuel oil) and gaseous fuels with a high content of heavy impurities (associated petroleum gas, sulfuric gas, biogas, etc.); by performing the air supply channel in the form of a sleeve welded into the nozzle body, since this limits the volume of air supply;

- the inability to supply air through unused fuel channels, including for the implementation of blowing channels when switching between the types of fuel used, which adversely affects the quality of the spray of liquid fuel and the smoothness of the transition process;

- the impossibility of use in ground (tank) GTE: the nozzle is intended for use in aircraft GTE, and therefore its dimensions are too large to be used in ground (tank) GTE of significantly smaller size;

- the impossibility of cleaning the air-fuel mixture.

Disclosure of the utility model.

Based on this original observation, this utility model is mainly intended to offer a dual-fuel dual-circuit nozzle of a gas turbine engine, comprising a housing with fittings and gaseous and liquid fuel channels, an air supply channel, a gaseous and liquid fuel atomizer, a conical swirler, and spray nozzles allowing at least smooth out the above disadvantage, namely to provide the possibility of improving the efficiency of the nozzle, by improving the mixing of the top willow with air and protection against the formation of soot when working in dual-fuel mode, including high-viscosity liquid fuels, such as fuel oil, and gaseous fuels with a high content of heavy impurities, such as associated petroleum gas, sulfuric gas, biogas, etc. ., which is the stated technical problem of the present utility model.

An additional technical result is the compact design, which allows the use of this nozzle in ground (tank) gas turbine engines with a minimum number of modifications and without increasing the size of the gas turbine engine.

To achieve this goal, the air supply channel is located along the gaseous and liquid fuel supply channels, is connected to the air inlet fitting and to the air outlet nozzle, and is also equipped with an air filter, while the nozzle includes a means of blowing and protection against carbonization. the end surface of the spray.

Due to such advantageous characteristics, it becomes possible to increase the air supply to improve the quality of the air-fuel mixture being created and to ensure the protection of the fuel injectors against the formation of carbon on the end surface of the atomizer.

The supply of additional air volume allows for the required composition of the air-fuel mixture during GTE operation on high-viscosity liquid fuels (fuel oil) and gaseous fuels with a high content of heavy impurities (associated petroleum gas, sulfuric gas, biogas, etc.).

In the transition between the types of fuel, air from the GTE compressor is additionally supplied through the fuel channels, carrying out a complete cleaning of the fuel injectors and the combustion chamber, which ensures a smooth transition process without stopping the engine and significant power fluctuations.

Additionally, air can be supplied through unused fuel channels with insufficient air supply volumes from the main air channel to ensure the optimum composition of the air-fuel mixture and to protect against carbon formation. This fact is especially important when working with gas turbine engines on gaseous fuels with a high content of heavy impurities (associated petroleum gas, sulfuric gas, biogas, etc.).

There is a possible embodiment of the utility model in which the means of blowing and protection against the formation of soot on the end surface of the atomizer is formed by an air gap located between the swirler nozzles and the atomizer, twelve inlet openings angled to the nozzle body and twelve outlet openings located on the end side spray bottle.

Due to this advantageous characteristic of essentially integrating the air channel into the nozzle casing, it becomes possible to reduce the nozzle dimensions, which provides an additional technical result — the possibility of using this nozzle in small-size ground-based (tank) GTEs with a minimum number of modifications; combustion.

There is an embodiment of the utility model in which the air filter is made in the form of a filter cartridge containing filter material wrapped with a metal mesh that provides protection and retention of the cartridge flirting material.

Thanks to this advantageous characteristic, the possibility of additional purification of compressed air coming from the gas turbine engine compressor appears, thus avoiding the entry of contaminating elements into the air-fuel mixture, ensuring its high quality.

There is a possible variant of the utility model, in which the conical swirler is fixed in the nozzle by means of a movable support of the spring, preloaded by a spring.

Thanks to this advantageous characteristic, it is possible to change the position of the swirler in the nozzle. With increasing pressure in the chamber of liquid fuel, the volume of the cone chamber of the swirler decreases, thus achieving the required level of intensity of turbulence and the quality of the spray of the air-fuel mixture when the GTE power is set.

The set of essential features of the proposed utility model is unknown in the prior art for devices of similar purpose, which allows to conclude that the criterion "novelty" for the utility model.

Brief description of the drawings.

Other distinctive features and advantages of the utility model clearly follow from the description below for illustration and not being restrictive, with reference to the accompanying drawings, which depict:

- figure 1 schematically depicts a vertical section of a dual-fuel dual-circuit nozzle of a gas turbine engine, according to the utility model,

- figure 2 schematically depicts the movement of air in the dual-fuel dual-circuit nozzle of a gas turbine engine, according to the utility model,

- figure 3 schematically depicts a top view of the dual-fuel twin-circuit nozzle of a gas turbine engine, according to the utility model,

In the figures indicated:

1 - nozzle body

2 - Fittings for the supply of liquid and gaseous fuels (2 units)

3 - Gaseous fuel channel

4 - Liquid fuel channel

5 - Core filter sleeve

6 - Gas fuel atomizer chamber

7 - Camera fuel oil dispenser

8 - Sleeve

9 - O-ring

10 - Pressure ring

11 - Spray Nozzles

12 - Conical Swirl

13 - Spring support

14 - spring

15 - Air duct

16 - Air filter

17 - Air nozzle

18 - Holes for air supply from the air combustion chamber

19 - The annular gap

20 - Blowing air holes

21 - Outlet for the injection of gaseous fuel

22 - Taper swirl chamber

23 - Air passage channels

24 - Outlet for injection of liquid fuel

25 - Air supply.

The dual-fuel dual-circuit nozzle of a gas turbine engine consists of body 1 - with fittings for supplying liquid and gaseous fuels 2 -, channels of gaseous 3 - and liquid 4 - fuels, filter rod 5 -, chambers of a gaseous dispenser 6 - and liquid 7 - fuels. The entire package of parts is fixed by a sleeve 8 - with a sealing 9 - and push 10 - rings. Spray nozzle elements are the nozzle 11 - and a conical swirl 12 -. Swirl 12 - is fixed in the nozzle using spring support 13 -, preloaded spring 14 -. Filter 5 - is a precisely inserted into the hole in the housing 1 - a rod, on the cylindrical part of which a fine thread and a few slot are cut. The filtering element is a fine thread.

The sprayer is made in the form of a nozzle welded to the body of the proposed nozzle and provided with a number of gas distribution holes located at an angle of 45º to the sprayer.

In the case of the proposed nozzle additionally placed a means of supplying compressed air, including a fitting for supplying air, an air channel 15, an air filter 16 -, an air nozzle 17 - and a means of blowing and protection against the formation of scale.

Air is fed into the nozzle body through the air nozzle and through channel 15 - enters the air filter 16 -, then, passing the swirling grooves formed by the nozzle 17 -, mixed with fuel ejected from the swirler 12 - and the sprayed fuel-air mixture is ejected through the nozzle outlet eleven - . In order to eliminate soot on the end surface of the sprayer, air is supplied to the blowing tool and protected from the formation of soot by twelve holes 18 - with a diameter of 2 mm and along the annular gap 19 - with a width of 1 mm. The output of the blasting air is carried out through twelve holes 20 - with a diameter of 0.8 mm. The number and size of the holes are chosen in such a way as to ensure a high value of the coefficient of combustion efficiency and a uniform temperature field of gas in front of the turbine.

The dual-fuel dual-circuit nozzle of the gas turbine engine is installed in the combustion chamber of the GTE in the amount of 18 pieces and are fixed with flanges using two bolts.

Implementation of the utility model.

When working on gaseous fuel, fuel is supplied through fitting 2 - and through channel 3 - to the atomizer chamber 6 - organized parallel to the nozzle axis, where it is mixed with air coming from the swirler 12 -, and the resulting fuel-air mixture is injected into the combustion chamber of the CCD through openings 21 -. Part of the air additionally enters through twelve oblique holes 18 - in the body of the spray gun and, passing through the annular gap 19 -, blows the resulting carbon through the holes 20 -. When gaseous fuel with a high content of heavy impurities is used as fuel (associated petroleum gas, sulfuric gas, biogas, etc.), additional air is supplied to the swirler 12 through the liquid fuel supply channel 4 -, which allows for the effective deflation of the deposited heavy impurities.

When the GTE is operating on liquid fuel, fuel goes through nozzle 2 through channel 4 to chamber 7 in the nozzle body. Passing through the filter 5 - the fuel goes to the swirler 12 -, then through the holes in the collar of the swirler 12 - the fuel goes to two swirling grooves located at an angle of 45 ° to the axis of the swirler and through them - to the cone swirl chamber 22 -. Air is fed into the nozzle body through the nozzle and through channel 15 - enters the air filter 16 -, then, through channels 23 - passes into the swirling grooves formed by the nozzles 17 -, mixed with fuel. The sprayed air-fuel mixture is ejected through the outlet 24 -. During the operation of gas turbine engines on high-viscosity liquid fuels (fuel oil), an additional amount of air is supplied through the gaseous fuel supply channel 3 -, which allows to ensure the required composition and completeness of combustion of the fuel-air mixture.

When the pressure in the liquid fuel chamber 7 - increases, as a result of an increase in the volume of liquid fuel supply, the swirler 12 is displaced to the depth of the nozzles 11 -, which leads to a decrease in the swirl chamber volume 22 - and an increase in the vortex intensity, which allows to ensure the quality of air-fuel mixture increasing the working capacity of the CCD.

The air filter 16 is made in the form of a filter sleeve with a metal grid wound on it, which protects and holds the flirting material of the sleeve, and is intended for additional purification of compressed air coming from the high-pressure compressor of the gas-turbine engine. It is possible to use various types of filter materials depending on the GTE operating conditions and the degree of dust content of the supplied air, taking into account the provision of a cleaning class not lower than F7 according to GOST R EN 779–2014 (polyester, polypropylene, etc.). Additional filtration of compressed air avoids contaminants from entering elements in the air-fuel mixture, ensuring its high quality.

In the transition between the types of fuel, air from the GTE compressor is additionally supplied through the fuel channels, carrying out a complete cleaning of the fuel injectors and the combustion chamber, which ensures a smooth transition process without stopping the engine and significant power fluctuations.

Industrial Applicability.

The proposed dual-fuel nozzle dual-fuel can be carried out by a specialist in practice and in the implementation ensures the implementation of the stated purpose. The ability to be practiced by a specialist in practice follows from the fact that for each attribute included in the formula of a utility model based on the description, a material equivalent is known, which allows to conclude that the criterion "industrial applicability" for the utility model and the criterion "completeness of disclosure" for the utility model .

Due to the fact that the air supply channel is located along the gaseous and liquid fuel supply channels, it is connected to the air inlet fitting and the air outlet nozzle, and is also equipped with an air filter, while the nozzle includes a means of blowing and protection against carbonization on the end surface of the atomizer, and the claimed technical result is achieved - improving the efficiency of the nozzle, by improving the mixing of fuel with air and protecting against the formation of soot when operating in dual-fuel mode, in including high viscosity liquid fuels, such as fuel oil, and gaseous fuels with a high content of heavy impurities, such as associated petroleum gas, sulfuric gas, biogas, etc.

Additionally, the technical result achieved is that the proposed utility model has small dimensions, which allows it to be used as part of small-size ground (tank) GTEs with a minimum number of modifications, while the dimensions of the GTE, in general, and the combustion chamber, in particular, remain unchanged. Dual-fuel twin-fuel injectors improve the performance and versatility of the gas turbine engine.

In addition, in the proposed nozzle swirl has a conical shape. This reduces the size of the turbulence chamber, which significantly reduces friction losses and ensures good quality spray pattern.

Claims (3)

1. Dual-fuel dual-circuit nozzle of a gas turbine engine, comprising a housing with fittings and gaseous and liquid fuel supply channels, an air supply channel, a gaseous and liquid fuel atomizer, a conical swirler, spray nozzles, characterized in that the air supply channel is located along the gaseous and liquid supply channels fuel, is connected to the air inlet and air outlet nozzle, and is also equipped with an air filter, while the nozzle includes a means of blowing and protection s from the formation of soot on the end surface of the sprayer. 2. Dual-fuel dual circuit nozzle according to claim 1, characterized in that the means of blowing and protection against the formation of soot on the end surface of the atomizer is formed by an air gap located between the swirl nozzles and the atomizer, twelve inlet openings angled to the nozzle body and twelve outlet openings located on the front side of the sprayer. 3. Dual-fuel dual circuit nozzle according to claim 1, characterized in that the air filter is made in the form of a filter cartridge filled with filter material held by a metal mesh.

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