JPS6330070Y2 - - Google Patents

Description

[Detailed Description of the Invention] Industrial Application Field The present invention relates to a premixed combustor for a gas turbine.

BACKGROUND OF THE INVENTION Some conventional gas turbine combustors have a premixing type structure as shown in FIGS. 1 and 2, and are composed of a pilot section 1 and a main section 2.

Problems that the invention aims to solve In conventional combustors of this type, the premixing passage 3 serves to mix the fuel and compressed air in advance, but the number of premixing nozzles 4 that can be installed in the circumferential direction is limited, and nozzle wakes (areas of reduced flow velocity occurring behind the nozzle) occur, making it difficult to obtain a uniform velocity distribution, which often results in flashbacks.

Means for Solving the Problems The present invention has been developed in view of the shortcomings of these conventional premix combustors. That is, the present invention consists of a pilot part and a main part, surrounds the pilot part to form a premixing passage, the premixing passage is cylindrical with inner and outer circumferential walls, and a plurality of premixing nozzles are provided. The premixing type combustor is characterized in that the cylindrical premixing passage is provided with an opening on the inner wall circumferential surface of the cylindrical premixing passage so that the ejection direction is radial.

Effect According to the present invention, fuel is injected from the inner circumferential wall into the premixing passage through which the compressed air flows in a radial direction intersecting the flow of the compressed air.

Embodiment Next, an embodiment of the present invention will be described in detail with reference to FIG.

In Figure 3, 1 is the pilot part, 2 is the main part,
3 is a premixing passage, and 4 is a premixing nozzle.

The fuel is injected from a premixing nozzle 4 that is opened on the inner wall circumferential surface of the premixing passage 3 so that the ejection direction is radial, and is configured to be mixed with compressed air while passing through the premixing passage 3.

Effects of the invention By doing this, the occurrence of wake in the premix nozzle 4 is eliminated. Further, it becomes possible to arrange a large number of the premix nozzles 4 in the circumferential direction.

In other words, by opening the premixing nozzle on the inner circumferential wall of the premixing passage, the nozzle is no longer exposed to the premixing passage, and no wake occurs in the flow in the premixing passage, and the flow in the premixing passage is uniform. It has a velocity distribution. This can prevent backfire. That is, the flashback is caused by the premixed gas at a low flow rate within the nozzle wake.

Further, by ejecting the fuel radially across the compressed air flowing in the axial direction and by arranging a large number of premixing nozzles, it is possible to mix the fuel with the compressed air more homogeneously.

[Brief explanation of the drawing]

Figure 1 is a sectional view showing the configuration of a conventional premixing type combustor, Figure 2 is a detailed enlarged view of section A in Figure 1, and Figure 3 is a partial sectional view showing the configuration of the combustor according to the present invention. be. 1... Pilot section, 2... Main section, 3...
Pre-mixing path, 4...Pre-mixing nozzle.

Claims (1)

[Scope of utility model registration request] It consists of a pilot part and a main part, and surrounds the pilot part to form a premixing passage, which has a cylindrical shape with inner and outer peripheral walls, and a plurality of premixing nozzles are connected to A premixing type combustor characterized in that a premixing passage is provided with an opening on the inner wall circumferential surface of the premixing passage so as to be radially oriented in the ejection direction.