RU2493492C1 - Gas turbine engine combustion chamber and nozzle module - Google Patents

Abstract

FIELD: power engineering.SUBSTANCE: gas turbine engine (GTE) combustion chamber comprises 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, inner and outer jackets installed with a gap relative to the 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, comprising blades installed at the angle to the axis of the combustion chamber. On the walls of the flame tube along the circumference there are "pockets" installed, which are made in the form of hollow streamlined profiles directed towards the axis of the flame tube. Holes are made in the outer and inner jackets in the rear part along the flow.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, the axis of the nozzle module.8 cl, 13 dwg

Description

The group of inventions relates to gas turbine engines, including aircraft and stationary gas turbine engines of gas turbine engines, and can be used in aircraft, 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 non-uniformity 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 the fuel, circumferential and radial unevenness of the temperature field at the outlet of the combustion chamber.

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

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 fuel channels to the nozzle modules, an external and internal flame tube housings.

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

The nozzle module comprises a housing, a central body, a truncated cone-shaped chamber, a central fuel channel and several output channels inclined to the axis of the nozzle module and air swirls made between the housing and the central body in the form of obliquely mounted vanes.

The disadvantages are the same, they are due to the axial location of the nozzle channel.

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 the inner housings, the outer and inner housings installed with a gap relative to the outer and inner housings, in that according to the invention the number of nozzle modules is a multiple of four, the core modules are installed in two rows: external and internal, two additional fuel collectors are external and internal, while the cavity of the external manifold is connected by fuel channels to each nozzle module through one external row of the nozzle modules, the cavity of the internal manifold is connected to each nozzle module through one internal row, and the main fuel manifold is connected to the remaining nozzle modules of both rows, while between the stove and the outer and inner walls of the flame tube is installed respectively, external and internal means for supplying and swirling cooling air with the possibility of supplying air at an acute angle to the axis of the flame tube, containing blades mounted at an angle to the axis of the combustion chamber, and on the walls of the flame tube around the circumference there are "pockets" made in the form of hollow streamlined profiles directed towards the axis of the flame tube. "Pockets" can be installed at an angle to the longitudinal axis of the combustion chamber. Collectors can be made as a single unit. The nozzle modules in rows can be staggered on the stove. "Pockets" and blades on each wall of the flame tube can be installed at the same angle to the axis of the combustion chamber. Means for supplying and swirling air may be configured to swirl air in opposite directions. Means for supplying and swirling air can be configured to swirl air in opposite directions

The solution of these problems was achieved in a nozzle module containing a housing, a central body, a truncated cone-shaped chamber, a central fuel channel and several output channels inclined to the axis of the nozzle module and air swirls made between the housing and the central body in the form of obliquely mounted vanes, that according to the invention, the central fuel channel is non-through and several output channels are drawn into it, made at an angle to the axis of the nozzle module.

The invention is illustrated in figure 1 ... 15, 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 node,

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 an external means of supplying and swirling air and external "pockets",

figure 9 shows the internal means of supplying and swirling air and internal "pockets",

figure 10 shows a diagram of the fuel supply to the nozzle modules and the design of the nozzle modules,

figure 11 shows the design of the nozzle module,

12 shows a section aa,

Fig.13 shows a plate,

on Fig shows a view of B,

on Fig shows a diagram of changes in pressure drop on the nozzle modules.

The combustion chamber of the gas turbine engine (Fig. 1 ... 15) 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 provided for cooling the flame tube 2. The flame tube 2 is closed on both sides with gaps by the outer and inner shells 9 and 10. In the rear part (downstream) of these shells, openings 11 and 12 are made for transferring cooling air into the gaps between the walls 8, 9 and the shells 10 and 11 and further into the flame tube 2.

The nozzle modules 13 are installed on the plate 3, placed in two concentric rows 14 and 15. The fuel channels 16 ... 18 are made in the plate 3 for supplying fuel to the nozzle modules 13. The number of nozzle modules 13 is a multiple of four and an even number in each row. In addition, in the plate 3, through holes 19 are made for installing the nozzle modules 13. At the same time, the nozzle modules 13 can be installed in a checkerboard pattern (Fig. 3). A feature of the combustion chamber of a gas turbine engine is the implementation of two additional fuel collectors: an external 20 with a cavity 21 and an internal 22 with a cavity 23 (FIGS. 1 and 2).

In addition, the difference between the combustion chamber of a gas turbine engine is the fuel supply circuit from the collectors 4, 20 and 22 to the nozzle modules 13 (Figs. 6 and 9), which ensures the uniformity of the temperature field at the outlet of the combustion chamber.

The external manifold 20 is connected by channels 16 to each nozzle module 13 of the outer row 14 of the nozzle modules 14 through one, the internal collector 22 is connected by channels 17 to each nozzle module 13 of the inner row 15 through one, and the cavity 5 of the main manifold 4 is connected by channels 16 to the other nozzle modules 13 of both rows 14 and 15. The nozzle modules 13 in rows 14 and 15 can be installed in a checkerboard pattern (figure 5), which is preferable, because will accommodate a greater number of nozzle modules 13.

Between the stove 3 and the walls 6 and 7 of the flame tube can be installed device for supplying and swirling air 24 and 25 (figure 2 and 6 and 10). Devices for supplying and swirling air 24 and 25 contain guide vanes 26 mounted at an angle α to the axis of the combustion chamber O1O1 (Fig. 8). Indices 1 and 2 relate to the external and internal means of supplying and swirling air, respectively. The direction of air swirl may be opposite for external and internal means (Fig.8 and 9). At the same time, the means for supplying and swirling air 24 and 25 are made at an acute angle β to the axis of the O2O2 flame tube connecting the middle of the stove 3 and the middle of the exit section of the AA flame tube (Fig. 1).

On the outer wall 6 of the flame tube 2 installed external "pockets" 27 for supplying air to the axis of the flame tube O ₂ O ₂ . On the inner wall 7, there are internal “pockets” 28 having the form of hollow streamlined profiles directed towards the axis of the O2O2 flame tube. "Pockets" 27 and 28 should be installed at an angle γ to the axis O1 O1 of the combustion chamber and at an acute angle φ to the axis O ₂ O _{2 of the} flame tube 2.

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 combustion products, since it is actually directed to the "center" of the combustion chamber (the hottest zone), and as a result, increases the completeness of combustion, reduces the emission of harmful substances and ensures a uniform field of temperature p at the exit of the combustion chamber. The nozzle modules 17 contain a housing 29, a cylindrical shape, a central body 30 made inside the housing, a ledge for fastening 31 made on one end of the housing 8, a mixing chamber 32 on the other end and a through fuel channel 33 made in the central body 29 and the ledge for fastening. The non-through fuel channel 33 communicates with the output channels 34, made at an angle to the axis of the nozzle modules 13. The Central body 30 and the housing 29 are connected by vanes 35 mounted obliquely, between which the air channels 36 are made (Fig. 11). In the plate 3 against the air channels 36 air channels 37 (from 3 to 6) are made, separated by jumpers 38 streamlined shape (11).

To ensure the operation of the combustion chamber, it has three pipelines 39 ... 41 with flow regulators 42 ... 44 connected to the collectors 4, 20 and 22, respectively (figure 1)

The collectors 4, 20 and 22 can be made in the form of a single unit (Fig. 3 and 4), which includes, in addition to the collectors, a fairing 45 with a cavity 46 (Fig. 4). The cavity 46 communicates with the cavity 5 of the main manifold 4 to increase the volume of the main manifold 4. The cowl 43 reduces the loss of air pressure at the inlet to the combustion chamber. The walls of the collectors 4, 20 and 22 are common, which reduces the metal consumption of the collectors. The connection of all parts of a single unit is made by welding seams 47. Depressurization between cavities 5, 21 and 23 will not lead to catastrophic consequences.

On Fig shows a diagram 48 of the change in the differential pressure of the fuel on the nozzle modules 13 of the prototype and diagram 49 for the proposed technical solution.

The gas turbine engine combustion chamber and nozzle modules are operated as follows.

When starting a gas turbine engine, fuel is supplied through a pipeline 40 through a flow regulator 43 only to the cavity 21 of the external manifold 20. In the “low gas” mode, fuel is also supplied only through the external collector 20 and then through the channels 16 to the odd nozzle modules 13 of the outer row 14. When increasing fuel consumption of more than 20% ... 25% of the maximum fuel consumption is additionally supplied through a pipe 41 through a flow regulator 44 to the cavity 23 of the inner manifold 22 and then through channels 17 to the odd nozzle modules 13 of the inner row 15. At a fuel consumption of 40 % to 50% of the maximum additional fuel through pipeline 39 through the flow regulator 42 is fed into the cavity 5 of the main manifold 4 and then through channels 18 to the remaining (even) nozzle modules 13 of both rows. The use of "pockets" 27 and 28 will allow you to throw relatively cold air into the Central region of the flame tube 2, thereby ensuring radial uniformity of the temperature field at the outlet of the combustion chamber. The installation of "pockets" 27 and 28 at an angle to the axis O ₁ O _{1 of} the combustion chamber will allow to swirl the flow of exhaust gases at the entrance to the turbine, thereby eliminating the harmful effect of the circular unevenness of the temperature field at the exit of the combustion chamber.

As a result of the use of three fuel manifolds 4, 20 and 22, the pressure drop across the nozzle modules 13 in all modes is almost constant and is a significant value of pos. 49 of Fig. 13, compared to pos. 48, which helps to increase the completeness of combustion and reduce emissions of harmful substances . In addition, in all modes, the temperature field at the outlet of the combustion chamber is more uniform.

The design of the nozzle module provides better mixing of fuel with air.

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 ensure an increase in the completeness of combustion in all modes due to the design features of the combustion chamber and nozzle modules.

3. To ensure low emissions of harmful substances due to high-quality mixing of the fuel-air mixture and due to mixing of the combustion products including air supplied to the combustion zone by means for supplying and swirling air.

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

5. To reduce the radial non-uniformity of the temperature field at the outlet of the combustion chamber on the reliability of the nozzle and rotor blades and to eliminate the harmful effect of circumferential unevenness.

Claims (8)

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 the housings, the outer and inner shells installed with a gap relative to the outer and inner housings, characterized in that the number of nozzle modules is a multiple of four, the nozzle modules are installed in two rows: outside external and internal, two fuel collectors are additionally made, the external manifold cavity being connected by fuel channels to each injector module through one external row of nozzle modules, the internal manifold cavity is connected to each injector module through one internal row, and the main fuel manifold is connected with the rest of the nozzle modules of both rows, while between the stove and the outer and inner walls of the flame tube, respectively, external and internal cf means for supplying and swirling cooling air with the possibility of supplying air at an acute angle to the axis of the flame tube, containing blades installed at an angle to the axis of the combustion chamber, and on the walls of the flame tube circumferentially mounted “pockets” made in the form of hollow streamlined profiles directed to the side the axis of the flame tube, and holes are made in the outer and inner casings in the backstream part. 2. GTE combustion chamber according to claim 1 or 2, characterized in that the "pockets" are installed at an angle to the longitudinal axis of the combustion chamber. 3. The combustion chamber of a gas turbine engine according to claim 1, characterized in that the collectors are made in the form of a single unit. 4. The GTE combustion chamber according to claim 1 or 2, characterized in that the nozzle modules in rows are mounted on a stove in a checkerboard pattern. 5. The combustion chamber according to claim 1 or 2, characterized in that the "pockets" and blades on each wall of the flame tube are installed at the same angle to the axis of the combustion chamber. 6. 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. 7. 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. 8. An injector module comprising a housing, a central body, a truncated cone-shaped chamber, a central fuel channel, air swirls made between the housing and the central body in the form of obliquely mounted vanes, characterized in that the central fuel channel is made through and several output channels made at an angle to the axis of the nozzle module.

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