BURNER AND METHOD FOR ITS PRODUCTION

Abstract

A burner having a combustion space and a multiplicity of swirl channels. each having a fuel nozzle for introducing fuel into the respective swirl channel. and The swirl channels extend from an inflow side to an outflow side leading into the fuel space. The swirl channels can each be flowed through by a fuel-air mixture consisting of the fuel and air flowing into the swirl channel. The burner has a centre axis running through the combustion space and the swirl channels, emanating from the outflow side, are helically wound about the centre axis in portions, so that the fuel-air mixture flowing from the inflow side along the flow path to the outflow side flows through the swirl channels in each case is subjected to a swirl and flows into the combustion space in a swirl-subjected manner.

Claims

1.-13. (canceled)

14. A burner comprising: a combustion space; a multiplicity of swirl channels, wherein each swirl channel has at least one fuel nozzle that introduces fuel into each respective swirl channel; wherein the multiplicity of swirl channels each extend from an inflow side, where the fuel from the respective fuel nozzle can be introduced into each respective swirl channel to an outflow side leading into the combustion space; a flow path of each respective swirl channel extending from the inflow side to the outflow side that is flowed through by a fuel-air mixture of the fuel and air flowing into each swirl channel, a centre axis running through the combustion space, wherein the multiplicity of swirl channels, emanating from the outflow side, are helically wound about the centre axis at least in portions, so that the fuel-air mixture flowing from the inflow side along the flow path to the outflow side is subjected to a swirl by the multiplicity of swirl channels and flows into the combustion space in a swirl-subjected manner.

15. The burner according to claim 14, wherein in the portion of the multiplicity of swirl channels running helically about the centre axis, the flow paths and/or centre lines of the multiplicity of swirl channels each comprise a turn angle of at least one of: greater than 0 and smaller than 90; greater than 60 and smaller than 90; and exactly 60

16. The burner according to claim 14, wherein the multiplicity of swirl channels each comprise, on the outflow side, the portion wound helically about the centre axis and on the inflow side a portion running parallel to the centre axis, wherein a respective transition between the helically wound portion and the portion running parallel to the centre axis is smooth.

17. The burner according to claim 14, wherein the multiplicity of swirl channels each have an annular cross-section and are formed as swirl tubes.

18. The burner according to claim 14, wherein each of the fuel nozzles on the inflow side extends into each respective swirl channel.

19. The burner according to claim 14, wherein the multiplicity of swirl channels on the inflow side each comprise a funnel-shaped inflow portion, into which the respective fuel nozzle extends, wherein between an outer surface of the respective fuel nozzle and an inner surface of the respective swirl channel an air passage running in a cross-section annularly about the fuel nozzle is defined in its inflow portion, through which air can flow into the respective swirl channel.

20. The burner according to claim 14, wherein fluid guiding elements for flow optimisation are provided in the multiplicity of swirl channels and/or on the fuel nozzles.

21. The burner according to claim 14, wherein the multiplicity of swirl channels are arranged on at least one annular course that is coaxial to the centre axis.

22. The burner according to claim 14, wherein the multiplicity of swirl channels of the multiplicity of swirl channels lie against one another.

23. The burner according to claim 22, wherein the multiplicity of swirl channels each comprise a wall delimiting the respective swirl channel in a radial direction and the walls of swirl channels lying against one another are formed integrally and/or in one piece.

24. The burner according to claim 14, wherein the fuel nozzles inject the fuel on the inflow side substantially transversely into the respective swirl channel.

25. The burner according to claim 14, wherein the multiplicity of swirl channels are produced from metal by selective laser melting.

26. A method for producing a burner having a combustion space; a multiplicity of swirl channels, wherein each swirl channel has at least one fuel nozzle that introduces fuel into each respective swirl channel; wherein the swirl channels each extend from an inflow side, where fuel from the respective fuel nozzle can be introduced into the swirl channel to an outflow side leading into the combustion space; a flow path of each swirl channel extending from the inflow side to the outflow side that is flowed through by a fuel-air mixture of the fuel and air flowing into the swirl channel; a centre axis running through the combustion space, wherein the swirl channels, emanating from the outflow side, are helically wound about the centre axis at least in portions, so that the fuel-air mixture flowing from the inflow side along the flow path to the outflow side is subjected to a swirl by the swirl channels and flows into the combustion space in a swirl-subjected manner, comprising one of: producing the swirl channels from a metal powder by selective laser melting; and individually producing the swirl channels and arranging the swirl channels about the centre axis; or producing the swirl channels in groups joined integrally and/or in one piece; and arranging the groups of the swirl channels joined to one another about the centre axis; or producing all swirl channels joined integrally and/or in one piece and arranged about the centre axis.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Other advantageous further developments of the invention are marked in the subclaims or are presented in more detail by way of the figures together with the description of the preferred embodiment. It shows:

[0041] FIG. 1 is a variant of a burner;

[0042] FIG. 2 is an extract of a variant of a burner.

DETAILED DESCRIPTION OF THE PRESENTLY PREFERRED EMBODIMENTS

[0043] The figures are exemplarily schematic. Same reference numbers in the figures point out same functionally and/or structural features.

[0044] In FIG. 1, a burner is shown that comprises a swirl generator comprising a multiplicity of swirl channels 2, which here are embodied as swirl tubes, arranged about a centre longitudinal axis X and into which at their inflow side 21 a fuel nozzle 3 each extends, through which a fuel G can be injected into the swirl channels 2. Here, the swirl channels 2 on the inflow side each comprise a funnel-shaped inflow portion 27, in which between an inner wall or inner surface of the respective swirl channel 2 and an outer wall or outer surface of the respective fuel nozzle 3 an air passage 28 is formed, through which air L can flow into the respective swirl channel 2 substantially parallel to the fuel G. The fuel G and the air L mix in the swirl channels 2 and flow as fuel-air mixture along the respective flow path 23 from the inflow side 21 to an outflow side 23 of the respective swirl channel 2.

[0045] There, the fuel-air mixture initially flows through a portion 24 (straight portion 24) initially running parallel to the centre axis of the respective swirl channel 2, which by a steady, smooth transition 25 merges into a portion 26 wound helically about the centre axis X, which can also refer to as curved portion 26.

[0046] In the process, the fuel-air mixture is imparted a swirl or rotation when flowing through the curved portion 26 so that each fuel-air mixture flow issuing out of a swirl channel 2 into the outflow side combustion space 1 is subjected to a swirl. Here, the fuel-air mixture flow through a single swirl channel 2 merely forms a part flow of the entire fuel-air mixture flow flowing through the swirl channels 2.

[0047] In the combustion space 1, the fuel-air mixture flowing in with the entire fuel-air mixture flow is combusted, wherein by subjecting the individual part flow to a swirl the entire flow is subjected to a swirl resulting in a low-emission combustion, wherein through the multiplicity of swirl channels 2 running along the centre axis X a high flash-back resistance is achieved at the same time so that a flame during the combustion does not substantially flash back out of the combustion space 1 into the swirl channels 2.

[0048] In FIG. 2, an enlarged extract of the portion 24 of a burner running parallel to the centre axis is shown, which can be the burner according to FIG. 1. At least one part of the swirl channels 2 is additionally shown in half section, so that the section runs through the walls 29 of a part of the swirl channels 2, as a result of which in particular the fuel nozzles 3 in the region of the inflow portions 27 formed as funnel are visible.

[0049] As described before, an air passage 26 each running annularly about the fuel nozzle 3 is formed between the outer surfaces of the fuel nozzles 27 and the inner surfaces of the swirl channels 2 in the region of the inflow portions 27, through which the air L flows into the respective swirl channel 2. There, at least one fluid guiding element 4 each formed in the manner of an aerofoil is provided on the fuel nozzles 3, which extends into the annular air passage 26 and steers the inflowing air L into the associated swirl channel 2 in a flow-optimised manner.

[0050] Thus, while there have shown and described and pointed out fundamental novel features of the invention as applied to a preferred embodiment thereof, it will be understood that various omissions and substitutions and changes in the form and details of the devices illustrated, and in their operation, may be made by those skilled in the art without departing from the spirit of the invention. For example, it is expressly intended that all combinations of those elements and/or method steps which perform substantially the same function in substantially the same way to achieve the same results are within the scope of the invention. Moreover, it should be recognized that structures and/or elements and/or method steps shown and/or described in connection with any disclosed form or embodiment of the invention may be incorporated in any other disclosed or described or suggested form or embodiment as a general matter of design choice. It is the intention, therefore, to be limited only as indicated by the scope of the claims appended hereto.