RU2612231C1 - Gte combustion chamber and nozzle unit - Google Patents

Abstract

FIELD: power industry.

SUBSTANCE: gas turbine engine combustion chamber comprises an outer housing, a flame tube and an annular shape plate with nozzle units mounted on it and a fuel manifold connected to the plate and mounted in air space in front of the nozzle plate, which chamber is connected with the pipe line on one side, and with nozzle units containing jet fuel nozzle and air supply and spin channels on the other side by fuel channels. Wherein central electrodes are mounted inside the fuel nozzles, electrically connected to eachother and with a high-voltage insulated wire connected to the high-voltage unit output. Also a nozzle unit is presented.

EFFECT: invention allows to increase fuel combustion completeness and reduce harmful substances emissions for all modes, ensures uniform temperature field at combustion chamber outlet in a circle for all modes.

3 cl, 8 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 fuel, circumferential and radial unevenness of the temperature field at the outlet of their combustion chamber.

Famous gas turbine engine combustion chamber and nozzle module according to the patent of the Russian Federation for the invention No. 2493493, IPC F23R 3/28, publ. 09/20/2013, the prototype.

This combustion chamber contains an outer casing, a flame tube, a nozzle plate and nozzles, an annular manifold mounted in the front cavity on the nozzle plate to which the fuel line is connected.

The disadvantage is incomplete combustion of fuel. About 5% of the fuel does not burn and is released into the atmosphere in the form of C, CO NO, etc. This increases fuel consumption and degrades the ecology of the atmosphere.

Objectives of the invention: increasing the completeness of fuel combustion in the chamber of a gas turbine engine.

Achieved technical results: increased completeness of fuel combustion in the combustion chamber of a gas turbine engine.

The invention is illustrated in FIG. 1 ... 8, where:

in FIG. 1 shows a diagram of a combustion chamber of a gas turbine engine,

in FIG. 2 shows a plate with nozzle modules,

in FIG. 3 shows a diagram of the fuel supply to the modules,

in FIG. 4 shows the design of the nozzle module,

in FIG. 5 shows a section aa,

in FIG. 6 shows the nozzle plate,

in FIG. 7 shows a view of B on the stove,

in FIG. Figure 8 shows the free radical lifetimes.

The combustion chamber of the gas turbine engine (Fig. 1 ... 8) contains an outer casing 1, a flame tube 2, a stove 3 and a collector 4 with a cavity 5. The collector 4 is installed in the air cavity 6 and the fuel pipe 7 is connected to it.

On the plate 3 mounted nozzle modules 8, placed in two concentric rows. In the plate 3, fuel channels 9 are made for supplying fuel through the annular cavities 10 to the nozzle modules 8. In addition, in the plate 3 there are through holes 11 (Figs. 1, 3, and 6) for installing the nozzle modules 8. In this case, the nozzle modules 8 can be staggered.

The circuit for supplying and swirling air to the nozzle modules 8 (Figs. 1, 6, and 7) includes air channels 12 formed by inclined ribs 13.

The nozzle module 8 comprises a housing 14, a central body 15, a jet fuel nozzle 16, a radial hole 17 extending into it and communicating with the annular cavity 10. Concentricly to the jet fuel nozzle 16 are air swirl channels 18 formed by inclined vanes 19 (Fig. 4 and 5). Inside the jet fuel nozzle 16, a central electrode 20 is installed, which is isolated from the housing 14 by an insulator 21. All central electrodes 20 of all modules 8 are electrically connected and connected by a high-voltage insulated wire 22, which in turn is connected to a high voltage unit 23, the other output of which is grounding wire 24 is connected to the outer housing 1 of the combustion chamber. The outer housing 1 of the combustion chamber must be electrically connected to the nozzle plate 3.

During the operation of the gas turbine engine, which includes the combustion chamber, a potential is supplied from the high voltage block 23 to all central electrodes 20 of the nozzle modules 8, while a powerful electric field arises between the central body 15 and the central electrode 20, which activates the fuel, i.e. the radicals H, CH, CH2 and CH3 are formed, having a very short lifetime (of the order of 30 nanosacks, see Fig. 8).

However, given that activated fuel burns out almost immediately, free radicals have time to fulfill their role as a catalyst for the intensification of the combustion process.

The design of the proposed nozzle module 8 provides better combustion of fuel.

The application of the invention allowed:

1. Ensure complete combustion of fuel in all modes, especially in the "small gas" mode.

2. To ensure the reduction of harmful substances due to the design features of the combustion chamber and nozzle modules.

Claims (3)

1. GTE combustion chamber comprising an outer casing, a heat pipe and a ring-shaped stove with nozzle modules mounted on it and a fuel manifold connected to the stove and installed in the cavity in front of the nozzle stove, the cavity of which is connected on one side to the fuel line and to the other channels with nozzle modules containing a jet fuel nozzle and air supply and swirl channels, characterized in that central electrodes are connected inside the fuel nozzles and are connected electrically between oboj and insulated high voltage conductor, connected to the output of the high-voltage unit, wherein the second high-voltage output unit is connected to the outer casing of the combustion chamber, is electrically connected with the nozzle plate. 2. GTE combustion chamber according to claim 1, characterized in that the nozzle modules are installed in two concentric rows. 3. An injector module comprising a housing, a central body, a jet fuel nozzle and air supply and swirl channels made between the housing and the central body, characterized in that central electrodes are installed inside the jet fuel nozzles and are electrically connected to each other and to an insulated high-voltage wire, connected in turn with the exit from the high-voltage block, the second output of the high-voltage block connected to the external housing of the combustion chamber, electrically connected to the nozzle plate.

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