JP2894084B2 - Swirling annular combustor - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustor, and more particularly to a gas turbine combustor mounted on an automobile.

[0002]

2. Description of the Related Art Conventionally, an internal combustion engine, which is a so-called Otto cycle, is mainly used as an engine for a vehicle. However, application of a gas turbine having a large output per unit weight to a vehicle has been studied. FIG. 5 is a cross-sectional view of a gas turbine mounted on a vehicle that is currently generally proposed. Combustion air is compressed by a compressor 51 and taken into a casing 50.

[0003] The combustor 53 is formed by spiraling a cylinder whose diameter becomes smaller as it goes earlier, with the smaller diameter as the center, and the combustion gas turns around the turbine 58. A fuel injection nozzle 55 is provided on the bottom surface of the larger diameter of the combustor 53, and fuel is injected into the combustor 53. Compressed air is sucked from holes provided around the combustor 53 and mixed with fuel inside the combustor 53 to become combustion gas after combustion to drive the turbine 58.

[0004] The turbine 58 and the compressor 51 are directly connected to one shaft, and about 2/3 of the power generated by the turbine is used for driving the compressor, and the remaining about 1/3 is taken out as power for driving the automobile. However, in such a combustor, there is a limit to an increase in the amount of heat to obtain a larger output, that is, to increase the combustion under a high load.

In order to achieve high-load combustion, it is necessary not only to promote the mixing of fuel and air but also to increase the combustion speed. To achieve these, a jet swirling combustor has been proposed (innovation). Achievement Report on Aircraft Technology Development No. 0106, "Study of Jet-Swirl-Type Annular High-Load Combustor," Published by Japan Aerospace Industry Innovation Center for Innovative Aircraft Technology.

FIG. 6 is a cross-sectional view of a jet swirl combustor 60 proposed in the above-mentioned report, in which a bottom surface 61 is formed in a hemispherical shape. Injected from 65. FIG. 7 is a schematic view of a part of the jet swirl type combustor. As shown in FIG. 7, the combustion gas swirls along the bottom surface of the hemisphere and spirals through the combustor formed in an annular shape. Aperture 6 after propagation
7 to drive the turbine.

[0007] Since the flame turns along the hemispherical bottom surface, centrifugal force not only increases the moving speed of the flame, but also promotes the mixing of fuel and air by injecting fuel into the jet.

[0008]

However, since the combustion air is supplied from the air suction holes 63 formed in the outer periphery of the combustor, the air flow and the fuel jet collide with each other in the combustor, and the fuel flow is reduced. A part of the fuel is discharged from the opening 67 without being burned, causing the following problem. (1) Exhaust gas properties deteriorate.

(2) Fuel efficiency is deteriorated. The present invention has been made in view of the above problems, and an object of the present invention is to provide a jet swirl combustor that can burn fuel more completely without collision between a fuel jet and an intake air flow. And

[0010]

According to the present invention, there is provided a swirl type annular combustor in which a combustion chamber having a circular cross section is formed in an annular shape according to the present invention, a mixture supply passage for supplying a combustion mixture to the annular combustor, An exhaust passage that is drawn out in the same direction and parallel to the air supply passage, and an air hole that blows air so as to contact a swirling circle of a flame that penetrates the wall of the annular combustor and swirls along the inner surface of the annular combustor. Provide.

[0011]

In the swirl type annular combustor according to the present invention,
Since the fuel and the combustion air are mixed in advance in the mixture supply passage, the degree of mixture of the mixture supplied to the combustion chamber is improved. Further, the combustion is performed while swirling along the inner wall of the combustion chamber having a circular cross section, and the secondary air is sucked in so as to promote the swirling of the flame, so that the combustion speed is improved,
High load combustion is realized.

[0012]

FIG. 1 is a sectional view of a gas turbine using a swirling annular combustor according to the present invention.
The air compressed by the compressor 11 installed at the front of the casing is supplied to the combustion chamber 13 by the mixture supply path 12 having a nozzle, and is also supplied to the inside of the casing 10 through the bleed hole 14.

In this embodiment, the mixture supply path 12
Are concentrically configured. A fuel injection nozzle 15 is provided in the air-fuel mixture supply path 12 and injects fuel into the air-fuel mixture supply path 12. The collision plate 1 is located below the fuel injection nozzle 15.
6 is provided to change the flow of the fuel injected from above perpendicularly to the axis of the mixture supply passage 12 by 90 °.

The air-fuel mixture supplied to the combustion chamber 13 swirls and burns along the inner wall of the combustion chamber 13 having a circular cross section, and the exhaust gas passage 17 drawn in the same direction as the air-fuel mixture supply passage 12 in the same direction. And drives the turbine 18. In this embodiment, the exhaust path 17 is formed in a concentric shape having a smaller diameter than the mixture supply path 12.

An air suction hole 131 is formed around the combustion chamber 13, and the compressed air supplied to the inside of the casing 10 is sucked into the combustion chamber 13. FIG. 2 shows the mixture supply path 1
FIG. 2 is an enlarged sectional view of a combustion chamber 13 and an exhaust passage 17.
FIG. 3 is a partial top view of the swirling annular combustor according to the present invention, and FIG. 4 is a part of a cross-sectional view taken along line AA.

The impingement plate 16 is curved with a curvature R which is larger than the curvature r of the annular air-fuel mixture supply passage 12, and is configured to spread the fuel in a fan shape to promote mixing with the air. FIG. 8 is a partial perspective view of the air-fuel mixture supply passage 12. The fuel injected from the fuel injection nozzle 15 collides with the collision plate 16 and is spread in a fan shape, and combustion is performed in a sheet shape.

An orifice 121 is provided at an inner connection portion between the air-fuel mixture supply passage 12 and the combustion chamber 13 so that the fuel which has not been sufficiently finely divided is supplied to the combustion chamber 13 along the inner wall of the combustion chamber 13. The flow direction is changed so as to enter, and the combustion flame is prevented from flowing back into the air-fuel mixture supply passage 12. Further, the air intake hole 131 is opened in the combustion chamber 13.
Is provided so as to promote the swirling of the combustion gas swirling along the inner wall of the combustion chamber 13, that is, so that the sucked air flows in the tangential direction of the virtual swirl circle of the combustion gas.

As a result, the central portion of the swirling combustion gas is maintained at a high temperature and has a flame holding effect.

[0019]

According to the swirling annular combustor according to the present invention, the following effects can be obtained. (1) Since the fuel jet and the air jet do not collide in the combustor, the unburned fuel is prevented from being mixed with the exhaust gas and is prevented from deteriorating in the properties of the exhaust gas and the fuel consumption. It becomes possible.

(2) Even if the gas turbine itself is downsized,
The combustion length can be maintained long, and the discharge of unburned components can be prevented. According to this embodiment, the following effects can be further obtained. (3) Since the fuel injected from the fuel injection nozzle once collides with the collision plate, it becomes possible to atomize the fuel, not only to promote the mixing with air, but also to improve the combustion speed to improve the exhaust gas properties. It can be improved.

(4) Since the combustion is performed in a sheet form, the temperature of the flame becomes uniform and the NOx can be reduced.

[Brief description of the drawings]

FIG. 1 is a sectional view of a gas turbine to which a swirling annular combustor according to the present invention is applied.

FIG. 2 is a sectional view of a swirling annular combustor according to the present invention.

FIG. 3 is a top view of a swirling annular combustor according to the present invention.

FIG. 4 is a sectional view of the swirl type annular combustor according to the present invention,
It is A sectional drawing.

FIG. 5 is a sectional view of a conventionally used gas turbine.

FIG. 6 is a cross-sectional view of the previously proposed swirling annular combustor.

FIG. 7 is a schematic view of a previously proposed swirl type annular combustor.

FIG. 8 is a partial perspective view of a mixed gas supply path of the swirling annular combustor according to the present invention.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 11 ... Casing 12 ... Compressor 13 ... Air-fuel mixture supply path 14 ... Bleed hole 15 ... Fuel injection nozzle 16 ... Impact plate 17 ... Exhaust path 18 ... Air suction hole 19 ... Orifice

Claims (1)

(57) [Claims] 1. A swirling annular combustor in which a combustion chamber having a circular cross section is formed in an annular shape, a mixture supply path for supplying a mixture for combustion to the annular combustor, and in the same direction as the mixture supply path. An exhaust passage that is drawn out in parallel, and an air hole that penetrates a wall of the annular combustor and ejects air so as to contact a virtual swirl circle of a flame swirling along the inner surface of the annular combustor. A swirl type annular combustor characterized by the above.