SU1688051A1 - Combustion chamber front device - Google Patents

Abstract

The invention makes it possible to reduce flow resistance. This is achieved by the fact that when the blades 3 of the outer swirler 1 are installed with a tangential backrest, and the blades 4 of the internal swirler 2 change to the axis of the combustion chamber, the aerodynamic structure of the annular swirling jets of air emerging from the swirler causes the area to form behind the stabilizer. reverse currents, stabilizing combustion. When the blades are tangentially tilted backwards to the camera axis, annular swirling air streams flowing from it are deflected to the periphery and, conversely, when the trough is tangential by the trough, the current lines are deflected to the vortex axis. Therefore, as a result of the installation of the swirl blades of the frontal device with a tangential slope, the annular swirling air stream flowing out of the external swirl deviates towards the periphery, and the jet flowing out of the internal swirler connects to the axis of the combustion chamber, which greatly expands the reverse current zone ring stabilizers. 4 il.

Description

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The invention relates: to gas turbine installations, in particular, to front-end devices of the combustion chamber

The purpose of the invention is to reduce the hydraulic resistance

In Fig. 1, the front device of the combustion chamber is longitudinally cut; in Fig. 2, view A in Fig. 1, Fig. 3 - section B-B in Germany 1, in FIG. 4 - section BB, in FIG. one

The front device of the combustion chamber contains outer and inner annular coaxially mounted air vortex blades 1 and 2, blades 3, 4 each of which are mounted tangentially to the corresponding generator 5, b of the cylindrical surface passing through the root section of the flame 7 placed between the swirlers 1 and 2 of the Blades 3 of the outer zevihrlitel 1 are facing back towards the axis 8 of the combustion chamber, and the blades 4 of the internal swirler 2 - with a trough,

The front device is equipped with fuel dispensers 9

When the combustion chamber is in operation, the air flow, the flow around the combustion stabilizer 7, is divided into two annular jets, which are twisted by annular vanes 1,2

The annular swirling air jets from the swirlers 1, 2 and the fuel from the fuel-injection nozzles 9 are fed into the fire zone of the combustion circuit

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Due to the fact that the blades 3 of the outer swirler 1 are installed with a tangential backward slope, and the internal blades are trough to the axis 8 of the combustion chamber, the streamline (dashed lines in FIG. 1) of annular swirling air jets flowing from the outer and inner / trenches of the swirlers 1, 2, deviate respectively to the periphery and to the axis 8 of the combustion chamber. This leads to an increase in the volume of the reverse current zone behind the annular combustion stabilizer 7, thereby reducing the degree of blockage. In the zone of reverse currents (stabilization zone), a very high intensity of turbulent pulsations is observed, which contributes to the good mixing of fuel with air and the rapid flow of combustion.

Claims (1)

Invention Formula A frontal combustion chamber device containing outer and inner annular coaxially mounted vaned air impellers, the blades of each of which are mounted tangentially to the generatrix of the cylindrical surface passing through the root section of the blades, and an annular flame stabilizer placed between the eddies, characterized in that in order to reduce the hydraulic resistance, the blades of the outer swirler are turned back to the axis of the combustion chamber, and the internal blades Vb fig.Z AT 6 figl