RU2511992C2 - Injector unit of gas-turbine engine combustion chamber - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: injector unit of gas-turbine engine combustion chamber includes a plate of annular shape with injector modules installed on it in several rows, and a primary fuel collector connected to the plate, collector cavity being connected to fuel channels with injector modules. Injector modules are installed with register ledges inserted into the blind holes made in the plate and provided with mixing chambers of frustum-of-a-cone shape. All the injector modules have central fuel channel. Tangential air swirlers are made between the housing and the central body in the form of inclined blades. The central fuel channel is made blind with inserted tangential holes. Injector modules in rows are installed on the plate in staggered order.

EFFECT: improving fuel combustion completion at all the modes, reducing harmful emissions and providing uniform temperature field at combustion chamber outlet.

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Description

The invention relates to gas turbine engines, including aircraft and stationary gas turbine engines of 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.

The disadvantage is the 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 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 fuel supply to the fuel collectors 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 ability to move 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.

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 and nozzle module from the book Startsev N.I. Design and engineering of the gas turbine engine combustion chamber. Samara State Aerospace University, 2007, prototype 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 the fuel channels to the nozzle modules, the outer and inner flame tube bodies.

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) is sufficient for high-quality atomization of fuel, 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.

The objectives of the invention are to increase the completeness of fuel combustion in all modes, reduce the emission of harmful substances and ensure 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 the nozzle block of the gas turbine combustion chamber, containing a ring-shaped plate with nozzle modules mounted on it in several rows and a main fuel manifold connected to the stove, the cavity of which is connected by fuel channels to the nozzle modules, in that the nozzle modules are installed according to the invention installation ledges into non-through openings made in the plate and having mixing chambers in the form of a truncated cone, while all nozzle modules have central fuel th channel air swirlers provided between the housing and the central body in the form of slanted blades, and the central fuel passage formed therein and a non-through tangential openings withdrawn. The nozzle modules in rows can be staggered on the stove.

The solution of these problems was achieved in the nozzle module containing a mixing chamber in the form of a truncated cone, a central body, a central fuel channel, air swirls made between the body and the central body in the form of obliquely mounted blades, and a central fuel channel made through and through tangential holes, the fact that according to the invention the height of the Central body is selected from the ratio:

h = (0.1 ... 0.5) H,

where h is the protrusion of the Central body inside the mixing chamber,

H is the height of the mixing chamber.

The invention is illustrated in figure 1 ... 5, where:

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

figure 2 shows the nozzle module,

figure 3 shows a section A-A,

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.

The nozzle block of the gas turbine combustion chamber (Figs. 1 ... 5) contains a plate 1 with a collector 2 having a cavity 3. On the plate 1 there are nozzle modules 4 placed in several concentric rows 5. In the plate 1, through holes 6 are made, which end with cylindrical chambers 7, and fuel channels 8 for supplying fuel to the injector modules 4.

The nozzle modules 4 in rows 5 can be installed in a checkerboard pattern (figure 5), which is preferable, because will accommodate a larger number of nozzle modules 4. The nozzle modules 4 contain a cylindrical body 9, a central body 10 made inside the body 9, a mounting ledge 11 made on one end of the body 9, a mixing chamber 12 on the other end and a through fuel channel 13 made in the Central body 9 and the ledge for mounting 11. The mixing chamber 12 is made in the form of a truncated cone. The non-through fuel channel 13 communicates with the tangential openings 14. The central body 10 and the housing 9 are connected obliquely by blades 15, between which air channels 16 are made (FIG. 2). In the plate 1 against the air channels 16 are made air channels 17 (from 3 to 6), separated by jumpers 18 streamlined shape (figure 1).

Optimum sizes of nozzle modules:

h = (0.1 ... 0.5) H,

where h is the protrusion of the Central body inside the mixing chamber,

H is the height of the mixing chamber.

To ensure the operation of the combustion chamber, it has a pipe 19 (figure 1).

The collector 2 can be made with a fairing 20, which is connected to it by welding 21.

During the operation of the combustion chamber, fuel is supplied through a pipe 19 to the cavity 3 of the manifold 2, then through the fuel channels 8 to the cylindrical chambers 7 and then through the tangential openings 14 to the non-through fuel channels 13. Air is supplied through the air channels 17 to the air channels 16 and is mixed with fuel in the mixing chamber 12. High-quality air-fuel mixture burns in the combustion chamber.

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 (1)

An injector block of a gas turbine combustion chamber containing an annular plate with nozzle modules mounted on it in several rows and a main fuel manifold connected to the stove, the cavity of which is connected by fuel channels to the nozzle modules, characterized in that the nozzle modules are installed with mounting tabs in through holes, made in the stove and having mixing chambers in the shape of a truncated cone, while all nozzle modules have a central fuel channel, air swirls made between between the casing and the central body in the form of obliquely mounted blades, and the central fuel channel is not through and tangential openings are brought into it, while the nozzle modules in rows are staggered on the stove.

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