Combustion chamber burner device of gas turbine equipment

FIELD: heating.

SUBSTANCE: invention related to energy, particularly to burner devices and can be used in gas turbine equipment. Burner device consists of a case (1), a fuel nozzle (2), a front device (3), a fire tube (4). The burner device belongs to gas-turbine engine combustion chamber. The front device executed with holes for fuel nozzles installation (2). The fire tube (4) with the front device (3) located inside of the combustion chamber cage (5). Fuel nozzles (2) connected to a gas ring collector (6). In combustion chamber fire tube and cage (5) between wall area air nozzles (7) located radically. Air nozzles (7) connected to the common ring air collector (9). The air collector (9) located in the case (1).

EFFECT: invention allows to regulate primary air supply to the combustion chamber section during equipment operation, burning device design simplification, it operation safety stays constant, possibility of device change on the running gas turbine equipment.

1 dwg

 

The invention relates to energy, in particular to the burning device, and can be used for ignition combustion in power plants of various types, as well as to regulate the supply of primary air in the combustion chamber during operation, the organization of pre-mixing of air and fuel, the ignition of air-fuel mixture so as to stabilize the combustion process.

Known to the burner combustion chamber of a gas turbine engine with adjustable airflow containing heating pipe with Windows in the wall, overlapping placed in the location window movable element connected through a system of levers to drive, while the movable element is designed as a flexible tape covering the heating pipe and having at least one incision, in addition, a system of levers connected sections of the tape, and it provides radial movement of the tape (patent RU №2163991 C2,7IPC F23R 3/26, priority from 19.12.1995,, publ. 10.03.2001,).

The closest technical solution, selected as a prototype, is the burner of the combustion chamber of a gas turbine plant comprising a casing within which is located the flame tube from the front of the device, provided with holes of a fuel injector connected to a gas to which lectorem, air manifold, controls bypass air in the form of rotary valves, equipped with devices for their rotation (patent RU №2162988 C2,7IPC F23R 3/42, priority from 22.02.1999,, publ. 10.02.2001 year).

A disadvantage of the known designs of burners of the combustion chamber is that the supply and regulation of air is provided by a movable mechanical components in the form of a system of levers, throttle or rotary valves, requiring the installation of additional mechanical drives in the combustion chamber, which complicates its design. However, because of the potential damage and failure of moving mechanical components of the burner reliability of the combustion chamber is reduced. While replacing mechanical units on the existing gas turbines impossible without disassembly of the combustion chamber, which requires stopping operation of the gas turbine engine. In addition, during operation of the gas turbine installation at various loads, the flow rate of air entering into the combustion chamber, a constant, and the gas flow rate is changed depending on the required capacity of the installation, to obtain the optimum ratio of air to gas in the gas mixture at the outlet of the fuel injectors at partial loads is not possible, which may lead to incomplete burning of fuel and increased the content of the oxide of nitrogen in the combustion products. To reduce the content of nitrogen oxide in combustion products is necessary to ensure selection of the size of the holes in the wall of the flame tube, and hence the corresponding system of levers and rotating flaps to overlap, resulting in the reliability of the combustion chamber.

The technical objective of the invention is to simplify the design of the burner while maintaining reliability, providing the possibility of replacement on the existing gas turbines.

To solve the problem in the combustion device, the combustion chamber of a gas turbine plant comprising heating pipe with front unit located in the casing of the combustion chamber, the front of the device is provided with a hole fuel injector connected to a gas manifold, air manifold, the device is further provided with air nozzles mounted radially in maintenacne space header pipe and casing, with air nozzles are connected to a common air manifold located in the housing of the burner.

The supply of the burner air nozzle, the radial location them in maintenacne space of the flame tube and the casing of the combustion chamber, and the connection of the air injectors with the General one DL is all air reservoir and its location in the body of the burner simplifies the design of the burner, consequently, the combustion chamber as a whole, while the reliability of the device due to the lack of breakdowns and failures of its components. This is achieved by eliminating moving lever mechanical assemblies, dampers, and actuators necessary for their work. In addition, it is possible to regulate the air flow and optimum ratio of air to gas in the gas mixture at the outlet of the fuel injectors at different loads. Regulation is achieved by the redistribution of air supplied to the fuel injectors and through the holes in the flame tube. During operation of the gas turbine air is supplied through air nozzle in maintenacne space header pipe and casing, which creates resistance to the air compressor, passing in the opposite direction to the fuel injectors. In this part of the air flowing to the fuel injector, and gets clipped into the holes of the header pipe that leads to the change in the flow rate of air supplied to the fuel injectors. The possibility of controlling the flow of air during operation of the combustion chamber allows to obtain the optimal values of emissions of nitrogen oxides and carbon oxides in the combustion products, which improves the environmental performance of the gas turbine installation.

Due to the fact that the body of the burner is a load-bearing structure and it fixed all the constituent elements of the burner, it is possible to upgrade the combustion chamber already existing gas turbines at audit or the average repair in the regulation of primary air by his replacement.

The drawing shows a General view of the burner, longitudinal section.

The burner includes a housing 1, the fuel injector 2, the front device 3, the pipe flame 4. The burner is part of the combustion chamber of the gas turbine engine. Case 1 is the supporting structure, on which are fixed all the constituent elements of the burner. The front unit 3 fixed to the body 1 of the burner from the inside and is made in the form of a disk with holes for the installation of the fuel injectors 2. The flame tube 4 with the front unit 3 are located inside the casing 5 of the combustion chamber. The fuel injector 2 is connected with a gas ring reservoir 6, through which it enters the fuel. In maintenacne space header pipe 4 and the casing 5 of the combustion chamber radially installed air nozzle 7. On the flame tube 4 is made of radial holes 8. Air nozzles 7 are connected common to all the ring is the first air manifold 9. Air manifold 9 is located in the body 1 of the burner. Air nozzle 7 serve to distribute the air between the fuel injector 2 and the optimum ratio of air to gas in the gas mixture at the outlet when the flow of air into the combustion zone through the openings 8 of the flame tube 4.

The burner works as follows. During operation of the burner air from the annular air manifold 9 is supplied to the air nozzles 7 and through them comes in maintenacne space header pipe 4 and the casing 5. Coming out of the air nozzles 7 air creates resistance in this space in the form of a protective air curtain air coming from a compressor (not shown) in the opposite direction to the fuel injector 2 in the same space. When this part of the air from the compressor is cut off and falls into the holes in the flame tube 4. Thus, changing the air pressure in the air nozzles 7, changes the flow rate supplied to the fuel injectors 2 air, which achieves the optimum ratio of air to gas in the gas mixture and high-quality burning fuel-air mixture.

Thus, the use of the proposed burner provides the possibility of controlling the feed of air to the fuel nozzles by changing the air pressure in the air injectors, that simplifies the design of the burner, but it ensures reliability of its work and at the same time reduces the content of nitric oxide in the products of combustion and incomplete combustion of fuel at partial loads of the combustion chamber. In addition, it is possible to replace the burner on existing gas turbines, resulting in lower cost of production.

The burner of the combustion chamber of a gas turbine plant comprising heating pipe with front unit located in the casing of the combustion chamber, the front of the device is provided with a hole fuel injector connected to a gas manifold, air manifold, wherein the device is further provided with air nozzles mounted radially in maintenacne space header pipe and casing, with air nozzles are connected to a common air manifold located in the housing of the burner.



 

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