RU2493494C1 - Gas turbine engine combustion chamber - Google Patents

Abstract

FIELD: power engineering.

SUBSTANCE: gas turbine engine (GTE) combustion chamber comprising a body, a flame tube, which has outer and inner walls, and a board of circular shape with nozzle modules installed on it and the main fuel header connected with the board, the cavity of which is connected by fuel channels with nozzle modules, inner and outer bodies. The number of nozzle modules is made as multiple to four. Nozzle modules are installed in two rows: inner and outer. Additionally there are two fuel headers: inner and outer, The cavity of the outer header is connected by fuel channels with each nozzle module via one in the outer row of nozzle modules. The cavity of the inner header is connected with each nozzle module via one in the inner row. The main fuel header is connected with remaining nozzle modules of both rows. Between the board and the outer and inner walls of the flame tube there are accordingly installed outer and inner facilities for supply and swirling of cooling air with the possibility to supply air at sharp angle to the axis of the flame tube, which connects the middle of the board and the middle of the output section of the flame tube.

EFFECT: increased completeness of fuel combustion and reduced emission of hazardous substances at all modes, and provision of even temperature field at the outlet of combustion chamber along circumference at all modes.

6 cl, 10 dwg

Description

The invention relates to gas turbine engines - gas turbine engines, including aircraft and stationary gas turbine engines gas turbine engines and can find application in aircraft construction, shipbuilding, gas pumping stations and for peak power plants as a drive for an electric generator designed to generate electricity.

Known combustion chamber of a gas turbine engine according to the patent of the Russian Federation for invention No. 2375597, IPC F02C 7/22, publ. 12/10/2009. The fuel manifold of the combustion chamber of a gas turbine engine contains an annular pipe for supplying fuel to the nozzles installed inside the chamber body, a supply pipe and an inlet fitting located outside the chamber, mounted in an outer sleeve attached to the chamber body with axial movement, provided with an internal a sleeve made in the form of at least one link, including two fixed rings and a movable ring installed between them with the possibility of transverse movement. The fixed rings are connected to the outer sleeve, and the movable ring is installed with the possibility of contacting with the inlet fitting. The device allows you to compensate for thermal stresses that occur in the outer sleeve and the fitting due to various thermal expansion of the housing of the combustion chamber and the fuel manifold in the axial and transverse directions. Reducing the diameter of the surface to the diameter of the fitting allows you to reduce air leakage.

Disadvantages: large unevenness of the temperature field at the outlet of the combustion chamber, due to the small number of nozzles.

Known combustion chamber according to the patent of the Russian Federation for the invention No. 2099640, IPC F23R 3/60, publ. 12/20/2000

This combustion chamber is designed for gas turbine installations (GTE). A perforated hood is mounted on the flame tube in the annular space between the body and the pipe, on which supporting devices and second-circuit burners are fixed. The presence of temperature compensators and the implementation of the outer shell of the flame tube from two sections minimize temperature stresses.

The disadvantages are the same.

Known combustion chamber according to the patent of the Russian Federation for invention No. 215888, IPC F23R 3/26, publ. November 10, 2000

The front device of the combustion chamber for a high-temperature gas turbine engine with the supply of fuel to the fuel manifolds through fixed flow dividers contains a front device made in the form of a series of profiled plates. Profiled plates are installed at the entrance to the primary channels with the possibility of moving relative to each other in the circumferential direction when changing the areas of the passage sections of the primary channels. Each of the profiled plates consists of a fixed and a moving part, telescopically connected to each other. The fixed parts of the telescopic plates are rigidly fixed to the fixed flow dividers. The reciprocal movable parts of the plates are mounted on the movable flow dividers. Fuel collectors at one end with internal ball joints are fixed to fixed flow dividers, and at the other end are pivotally attached to rotary rods, the second ends of which are pivotally attached to movable flow dividers. This embodiment of the front device extends the range of sustainable combustion.

The disadvantages of this combustion chamber are: emission of harmful substances especially in the “low gas” mode, incomplete combustion of fuel, circumferential and radial unevenness of the temperature field at the outlet of their combustion chamber.

Known combustion chamber from the book Startsev N.I. Design and engineering of the gas turbine combustion chamber Samara State Aerospace University, 2007, prototype.

This combustion chamber contains a housing, a flame tube having a ring-shaped stove with nozzle modules mounted on it in two rows and a main fuel manifold mounted on the stove, the cavity of which is connected by the fuel channels to the nozzle modules, the outer and inner flame tube housings ..

The disadvantages of this combustion chamber are: emission of harmful substances especially in the “low gas” mode, incomplete combustion of fuel, circumferential and radial unevenness of the temperature field at the outlet of their combustion chamber. All these disadvantages are due to the fact that all fuel consumption in all modes passes through all the nozzles of the combustion chamber. In addition, the combustion chamber must operate stably in a wide range of modes from “small gas” to “maximum mode”, i.e. in the range of a tenfold change in fuel consumption. If at the maximum mode "the pressure drop across the nozzles (nozzle modules" will be sufficient for high-quality fuel atomization, then in the "low gas" mode the pressure drop across the nozzles will decrease by 100 times, because it changes in proportion to the square of the fuel consumption., And it turns out insufficient for high-quality atomization of fuel.

For example, if the pressure drop across the nozzles at the “maximum mode” is 10 kgf / cm ² , then at the “low gas” mode only 0.1 kgf / cm ² . This leads to incomplete combustion of the fuel, emission of harmful substances and an uneven temperature field at the outlet of the combustion chamber. The latter will lead to burnout of the nozzle and working blades of the turbine.

Objectives of the invention: increasing the completeness of fuel combustion in all modes, reducing emissions of harmful substances and ensuring a uniform temperature field at the outlet of the combustion chamber around the circumference in all modes.

The solution of these problems was achieved in a gas turbine combustion chamber containing a housing, a flame tube having an outer and inner wall and a ring-shaped plate with nozzle modules mounted on it and a main fuel manifold connected to the stove, the cavity of which is connected by fuel channels to the nozzle modules, external and inner casings, so that according to the invention the number of nozzle modules is a multiple of four, nozzle modules are installed in two rows: external and internal, two fuel modules are additionally made the manifold is external and internal, while the cavity of the external manifold is connected by fuel channels to each injector module through one external row of nozzle modules, the cavity of the internal manifold is connected to each injector module through one inner row, and the main fuel manifold is connected to the remaining nozzle modules of both rows, between the stove and the outer and inner walls of the flame tube, respectively, external and internal means for supplying and swirling cooling air with the possibility of air supply at an acute angle to the axis of the flame tube connecting the middle of the stove and the middle of the output section of the flame tube. The collectors can be made in the form of a single unit. The nozzle modules in rows can be staggered on the stove. Means for supplying and swirling air may be configured to swirl air in opposite directions.

Between the nozzle modules, additional air supply channels can be provided.

The invention is illustrated in figure 1 ... 10, where:

figure 1 shows a diagram of a combustion chamber of a gas turbine engine,

figure 2 shows a plate with nozzle modules,

figure 3 shows a diagram of a combustion chamber with collectors made in the form of a single node,

figure 4 shows a plate with collectors made in the form of a single unit,

figure 5 shows a plate with nozzle modules installed in a checkerboard pattern,

Fig.6 shows a diagram of the fuel supply from the manifolds to the injector modules,

Fig.7 shows a plate with means for supplying and swirling air,

in Fig.8 shows the means of supply and swirl of air,

figure 9 shows a diagram of the fuel supply to the nozzle modules and the design of the nozzle modules.

figure 10 shows a diagram of the change in differential pressure on the nozzle modules.

The gas turbine combustion chamber (Fig. 1 ... 10) contains a housing 1 and a flame tube 2 with a stove 3. and a main manifold 4 with a cavity 5. The flame tube 2 has an outer wall 6 and an inner wall 7, on which openings 8 are made for cooling of the flame tube 2 .. Nozzle modules 9 are installed on neither the stove 3, fuel channels 10 ... 12 are made in the stove 3 for supplying fuel to the nozzle modules 9. The number of nozzle modules 9 is a multiple of four.

The nozzle modules 9 are installed in two concentric rows, the outer 13 and the inner 14. The number of nozzle modules 9 in both rows is the same and even. When this nozzle modules 9 can be installed in a checkerboard pattern (figure 3). A feature of the combustion chamber of a gas turbine engine is the implementation of two additional fuel collectors: external 17 with a cavity 18 and internal 19 with a cavity 20 (Figs. 1 and 2)

In addition, the difference between the combustion chamber of the gas turbine engine is the fuel supply circuit from the collectors 4, 17 and 19 to the injector modules 9 (Figs. 6 and 9), which ensures the uniformity of the temperature field at the outlet of the combustion chamber.

The external collector 17 is connected by channels 10 to each nozzle module 9 of the outer row 13 of the nozzle modules 9 through one, the internal collector 19 is connected by channels 11 to each nozzle module 9 of the inner row 14 through one, and the main collector 4 is connected by channels 12 to the other nozzle modules 9 of both rows 13 and 14. The nozzle modules 9 in rows 13 and 14 can be installed in a checkerboard pattern (figure 5), which is preferable, because will accommodate a larger number of nozzles.

Between the stove 3 and the walls 6 and 7 of the flame tube can be installed device for supplying and swirling air 21 and 22 (figure 2 and 6). Devices for supplying and swirling air 21 and 22 contain guide vanes 23. (Fig. 8). The spin direction of the cooling air may be opposite (Fig. 8). In this case, the means for supplying and swirling air are made at an acute angle a to the axis of the flame tube connecting the middle of the stove and the middle of the output section of the flame tube (Fig. 1).

Air swirling not only improves the cooling of walls 6 and 7 of the flame tube 2, but also mixes the combustion products, reducing the circumferential unevenness of the temperature field at the outlet of the combustion chamber, while this direction of air flow (at an acute angle to the axis of the flame tube) significantly improves mixing of the products combustion and as a result increases the completeness of combustion, reduces the emission of harmful substances and ensures a uniform temperature field at the outlet of the combustion chamber. The nozzle modules 9 contain a housing 24, fuel anal 25 and air channel 26 (figure 2). Non-through holes 27 are made in the plate 3 for installing the nozzle modules and through channels 28 for the passage of air into the nozzle modules 9 (Fig. 9).

To ensure the operation of the combustion chamber, it has three pipelines 29..31 with flow controllers 32 ... 34 connected to the collectors 4, 17 and 19, respectively (Fig. 1)

The collectors 4, 17 and 19 can be made in the form of a single unit (Figs. 3 and 4), which includes, in addition to the collectors, a fairing 35 with a cavity 36. The cavity 36 communicates with the cavity 5 of the main collector 4 to increase the volume of the main collector 4. Fairing 35 reduces the loss of air pressure at the inlet to the combustion chamber. The walls of the collectors 4, 17 and 19 are common, which reduces the metal consumption of the collectors. The connection of all parts of a single unit is made by welding seams 37. Depressurization between cavities 5, 18 and 20 will not lead to catastrophic consequences. Between the nozzle modules 9 can be made additional air supply channels 38 (Fig.7).

The gas turbine engine combustion chamber operates as follows.

When starting a gas turbine engine, fuel is supplied through a pipeline 28 through a flow regulator 31 only to the cavity 18 of the external manifold 17. In the low-gas mode ”fuel is also supplied only through the external collector 17 and then through channels 10 to the odd nozzle modules 9 of the outer row 13 .. fuel consumption of more than 20% ... 25% of the maximum fuel consumption is additionally supplied through a pipe 26 through a flow regulator 32 to the cavity 20 of the internal collector 19 and then through channels 11 to the odd nozzle modules 9 of the outer row 13. At a fuel consumption of 40% to 50 % of the maximum additional fuel through the pipeline 27 through the flow regulator 30 is fed into the cavity 5 of the main manifold 4 and then through channels 12 to the remaining (even) nozzle modules 9 of both rows. As a result, the pressure drop across the nozzle modules 9 in all modes is almost constant and amounts to a significant value of pos. 40 of figure 10, compared to pos. 39, which helps to increase the completeness of combustion and reduce the emission of harmful substances. In addition, in all modes, the temperature field at the output of their combustion chamber is more uniform.

The application of the invention allowed:

1. To provide effective smooth regulation of fuel consumption in a gas turbine engine while maintaining an almost constant pressure drop in all modes, especially in the "low gas" mode.

2. To provide an increase in the completeness of combustion in all modes.

3. Provide low emissions of harmful substances.

4. Ensure a uniform temperature field at the outlet of the combustion chamber.

Claims (6)

1. GTE combustion chamber comprising a housing, a heat pipe having external and internal walls, and an annular plate with nozzle modules mounted on it, and a main fuel manifold connected to the stove, the cavity of which is connected by fuel channels to the nozzle modules, external and internal buildings, characterized in that the number of nozzle modules is a multiple of four, the nozzle modules are installed in two rows: external and internal, additionally made two fuel manifolds, external and internal, while The cavity of the external manifold is connected by fuel channels to each nozzle module through one outer row of the nozzle modules, the cavity of the inner manifold is connected to each nozzle module through one inner row, and the main fuel manifold is connected to the remaining nozzle modules of both rows, between the stove and the outer and inner external and internal means for supplying and swirling cooling air with the possibility of supplying air at an acute angle to si flame tube connecting the middle plate and the middle section of the output of the flame tube. 2. GTE combustion chamber according to claim 1, characterized in that the collectors are made in the form of a single unit. 3. The combustion chamber of a gas turbine engine according to claim 1 or 2, characterized in that the nozzle modules in rows are mounted on a stove in a checkerboard pattern. 4. The combustion chamber according to claim 1 or 2, characterized in that the means for supplying and swirling air are configured to swirl air in opposite directions. 5. The combustion chamber according to claim 3, characterized in that the means for supplying and swirling air are configured to swirl air in opposite directions. 6. The combustion chamber according to claim 1 or 2, characterized in that between the nozzle modules there are additional air supply channels.

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