RU217743U1 - Combustion chamber burner - Google Patents

Abstract

The utility model relates to devices for burning gaseous fuel mainly in the combustion chambers (CC) of gas turbine engines (GTE) based on the implementation of the method of combustion of a pre-mixed lean air-fuel mixture (FA). The burner contains a housing (1) with a rod (2) and a ledge-turbulator (3). In the rod (2) there are channels (4) and (5) for supplying fuel to the standby and main, respectively, combustion zones, a swirler (6) with hollow blades (7) with holes for supplying fuel to the main zone, nozzle bushings (8) and nozzles (9) with holes (10). Sleeve (8) and nozzle (9) are installed in the central body (11) of the swirler. The parts are manufactured using the SLS technology from the nickel alloy HN58MBYu-ID. The technical result of the proposed solution is to improve the manufacturability of the burner by simplifying the structural elements made using selective laser sintering.

Description

The utility model relates to devices for burning gaseous fuels mainly in the combustion chambers (CC) of gas turbine engines (GTE) based on the implementation of the method of combustion of a pre-mixed lean air-fuel mixture (FA).

A combustion chamber with remote flame tubes and a low-emission burner device is known (RF patent No. 2744963, IPC F23R 3/14, publ. 03/17/2021), in which a dual-circuit burner contains a burner housing with a swirler and a central body; a swirler with hollow blades and an associated ledge-turbulator located on the outer diameter of the air channel at the inlet in front of the swirler blades; a rod with channels for supplying fuel to the main and duty zones and with holes for supplying fuel from the annular manifold to the main combustion zone; poorly streamlined central body, which is a continuation of the swirler, with holes for supplying air to the duty zone of combustion and holes for supplying fuel to the duty zone from the annular manifold through the central channel. The bluff body used in this burner as a flame stabilizer is a cylinder turning into a truncated cone with a generatrix angle of 5...7° and a ratio of the cone base diameter to the cylinder diameter equal to 1.35...1.45. The composition of the parts that determine the design of the burner is the burner body with a swirler and a central body, manufactured as a single part using additive technology, and the stem and mixing chamber element, manufactured mechanically.

The disadvantage of this burner device is the impossibility of replacing the central body with holes. Temperature erosion of the inner surface of the central body is possible when the combustion products of fuel assemblies flow around it. In this case, almost the entire device will need to be replaced, which significantly reduces the service life of the technical solution. The combination of parts made by selective laser melting (SLF) and mechanically leads to an uneven structure of the device, which can also cause burner failure.

The closest analogue of the proposed technical solution is a low-emission burner (patent RU No. 198755, IPC F23R 3/14, F23D 17/00, publ. 07/28/2020), containing a nozzle, a housing with a nozzle and a fuel supply rod to the main and duty combustion zones; a ledge-turbulator located in front of the air swirler; an air swirler, in the hollow blades of which there are holes for supplying fuel; the central body with channels for supplying fuel and air to the standby zone, the burner structural elements subject to high-temperature erosion - the fuel injector, the nozzles of the central body are removable, and the burner parts are interconnected by interference fits and threaded pairs. In addition, in a low-emission burner, the turbulizer ledge is removable, and the nozzle is attached to the combustion chamber flame tube and is mated with the burner body by means of a telescopic connection.

The main disadvantage is the complexity of manufacturing the device, which requires the production of a high class of accuracy and high-tech equipment for precise fitting of all parts of the burner.

The technical result of the proposed solution is to improve the manufacturability of the burner by simplifying the structural elements made using selective laser sintering.

The technical result is achieved due to the fact that in the burner device of the combustion chamber, containing a housing with a fuel supply rod to the main and standby combustion zones, an air swirler, in the hollow blades of which there are holes for fuel supply, a nozzle sleeve, a nozzle, a ledge-turbulizer located in front of the air swirler, the central body with channels for supplying fuel and air to the duty zone, the first component part is a body with a rod and a ledge-turbulizer, the second part is a swirler with blades and a central body, the third part is a nozzle and the fourth part is a nozzle sleeve installed in the central body of the device, while all components of the device are made by selective laser fusion.

Due to the manufacture of assembly parts of the burner device using selective laser melting, the production manufacturability has been increased (the labor intensity of manufacturing has been reduced due to the reduction in the amount of machining, the reduction in the range of parts in the assembly), organizations - cleaning the internal cavities of the burner, replacing components).

The invention is illustrated by the following drawings:

- in Fig. 1 shows a general view of the burner device of the combustion chamber;

- in Fig. 2 shows a section of the burner device of the combustion chamber.

The burner contains a body (1) with a rod (2) and a ledge-turbulator (3). In the rod (2) there are channels (4) and (5) for supplying fuel to the standby and main, respectively, combustion zones, a swirler (6) with hollow blades (7) with holes for supplying fuel to the main zone, nozzle bushings (8) and nozzles (9) with holes (10). Sleeve (8) and nozzle (9) are installed in the central body (11) of the swirler.

Parts are manufactured using SLS technology from KhN58MBYu-ID nickel alloy with laser radiation power from 148 to 331 W, scanning speed from 480 to 660 mm/s, scanning step from 0.11 to 0.14 mm and layer thickness from 50 to 60 μm . Rational properties of HN58MBYu-ID metal powder and regime parameters of SLS, selected according to the criteria for achieving the required mechanical properties, provide a high density of the material. Metal powder fraction (-50) microns, consisting of at least 70.0% of particles ranging in size from 22 to 50 microns, rounded, has no sharp edges and satellites, is the same in color and quality, dry and free from agglomerated masses.

The development of a technical process for the manufacture of a burner device by the SLS method includes the following five main steps:

1) development of a three-dimensional model of a part;

2) data transformation and transmission;

3) verification and preparation of a three-dimensional model for cultivation;

4) the process of growing in the SLS-installation;

5) post-processing of the synthesized part.

The proposed technical solution works as follows.

During the operation of this device, a method of burning a lean, homogeneous air-fuel mixture of the main zone in the diffusion flame of the standby combustion zone is implemented.

The jets of fuel from the standby zone through the holes (10) of the nozzle (9) are introduced into the swirling flow of the air-fuel mixture of the main combustion zone. The burning of the standby fuel occurs diffusely in reverse currents behind the central body (11). The fuel of the main circuit through a large number of small holes in the hollow blades of the swirler (6) is injected into the air flow entering the burner swirler behind the ledge-turbulator (3). In the channel formed by the outer wall and the central body (11) of the swirler (6), a poor fuel-air mixture of the main zone, homogeneous in composition, is formed. Combustion of the air-fuel mixture in the main zone in the swirling jet is ensured by the supply of heat from the combustion of the pilot flame in the wake behind the central body (11). As a result of the organization of mutually supporting combustion of two zones in the burner, a stable combustion process is ensured in all operating modes of the gas turbine engine.

The following principles form the basis for the development of the SLS technical process:

- technical - the process must fully ensure the fulfillment of all the requirements of the working drawing and technical requirements for the manufacture of the burner;

- economic - the manufacture of the burner device should be carried out with minimal labor and production costs, not exceed the cost of manufacturing by the traditional method;

- organizational - the burner device must be manufactured in conditions of production organization that provide the greatest efficiency.

Claims (1)

The burner device of the combustion chamber, containing a housing with a fuel supply rod to the main and standby combustion zones, an air swirler, in the hollow blades of which there are holes for fuel supply, a nozzle bushing, a nozzle, a ledge-turbulator located in front of the air swirler, a central body with channels for supply of fuel and air to the standby zone, characterized in that the first component is a body with a rod and a ledge-turbulizer, the second part is a swirler with blades and a central body, the third part is a nozzle and the fourth is a nozzle sleeve installed in the central body devices, while all components of the device are made by selective laser fusion.

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