JPS6330068Y2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a gas turbine combustor.

A gas turbine with a conventional annular combustor is
As shown in Fig. a, the case 3 includes a combustor chamber 4, a combustor outer cylinder 5, stationary blades 6, moving blades 7, and a combustor inner cylinder 8.

An annular combustor is formed in a space surrounded by a combustor outer cylinder 5 and a combustor inner cylinder 8, and a fuel nozzle 9 is arranged on the combustor inlet side and a stator vane 6 on the outlet side.

On the fuel nozzle 9 side of the fuel device, the outer cylinder 5 and the inner cylinder 8 have air holes 11 and 12 in their walls, respectively, but on the stationary blade 6 side, the outer cylinder 5 and the inner cylinder 8 have air holes 11 and 12, respectively, as shown in FIG. Air holes 11 are provided only in the wall.

The stationary blades 6 serve to discharge combustion gas to the rotor blades 7, and in order to further send air from the outer cylinder 5 to the inner cylinder 8, they are hollow as shown in FIG. 1c and have air holes 1.
It has 3. Most of the combustion air supplied from the air source 1 is transferred from the combustor chamber 4 to the combustor outer cylinder 5.
The air is fed into the combustor through air holes 11 provided in the combustor. The remaining air passes through air holes 13 formed in the stationary blades 6 and flows into the combustor through air holes 12 formed in the combustor inner cylinder 8. On the other hand, the fuel, which is pumped under pressure by the fuel pump 2 and atomized in the radial direction of the combustor by the nozzle 9, mixes with the above-mentioned combustion air in the primary combustion zone 10 and burns as combustible gas. The combustion gas passes through the combustor formed by the combustor outer cylinder 5 and the combustor inner cylinder 8, passes through the stationary blades 6 and the rotor blades 7, and is released into the atmosphere.

Figure 2 shows the air flow in the primary combustion zone. As shown in this figure, since the air holes 11 and 12 of the combustor outer cylinder 5 and the combustor inner cylinder 8 are spaced at regular intervals, the combustion air ejected from the air holes forms a large circulating flow. It becomes difficult to do so. For this reason, the disadvantage of conventional combustors is that they are difficult to hold flame and have a narrow combustion range.

The present invention aims to improve the short combustion range of conventional combustors and improve the combustor performance.

In order to achieve this objective, in the present invention, the air holes in the inner cylinder on the combustor inlet side are separated into a part near the combustion nozzle and a part where the combustion gas flow changes from the radial direction of the combustor to the axial direction (the part far from the nozzle). It is set up as follows.

An embodiment of the present invention will be described below with reference to FIG.

The annular combustor according to the present invention also has a primary combustion zone 10 extending in the radial direction and a secondary combustion zone connected thereto and extending in the axial direction, as in the prior art. Fuel is atomized and injected in the radial direction of the combustor from a fuel nozzle 9 provided in the shaft of the primary combustion zone 10,
Air holes 11 and 14a of the outer cylinder 5 and inner cylinder 8,
14b to become combustion gas, and later the combustion gas flow changes from the combustor radial direction to the axial direction and enters the secondary combustion zone, and then from the stator blade 6 to the rotor blade 7.
is discharged to.

What is different from the conventional one is the air hole 14 in the inner cylinder 8.
a and 14b are respectively provided in a part near the fuel nozzle 9 and in a part where the combustion gas flow changes from the radial direction of the combustor to the axial direction, that is, in a part far from the nozzle 9. Air flows in from air holes 11 distributed at regular intervals as in the conventional case. Therefore, the air ejected from the inner cylinder 8 to the combustor flows through the air holes 14a near the nozzle.
and the air hole 14b located far from the nozzle, and the air flow from the air hole 14a is the same as before, but the air flow from the air hole 14b is different from the air flow flowing in from the outer cylinder 5. This creates a resistance flow, which acts to form a circulating flow x in the vicinity of the center between the air holes 14a and 14b, that is, in the primary combustion zone 10 inside the combustor.

In this way, since a strong circulating flow is generated in the primary combustion zone of the combustor, flame stabilization becomes easy and the combustion range can be expanded.

[Brief description of the drawings]

Fig. 1a is a cross-sectional view of the annular combustor portion of a conventional gas turbine, Fig. 1b is a cross-sectional view taken along line B-B in Fig. 1a, and Fig. 1c is a cross-sectional view taken along line C-C in Fig. 1a. , FIG. 2 is a sectional view of the combustor near the fuel nozzle, and FIG. 3 is a sectional view of the annular combustor portion according to the present invention. 1...Air source, 2...Fuel pump, 3...Case, 4...Combustor chamber, 5...Combustor outer cylinder, 6...
Stationary blade, 7... Moving blade, 8... Combustor inner cylinder, 9... Fuel nozzle, 10... Primary combustion zone, 11, 12, 1
3... Air hole, 14a, 14b... Air hole.

Claims (1)

[Scope of utility model registration request] In an annular combustor formed by a combustor outer cylinder and a combustor inner cylinder and having a primary combustion zone extending in the radial direction and a secondary combustion zone connected to this and extending in the axial direction, on the inlet side of the primary combustion zone The combustor outer cylinder is provided with air holes distributed at regular intervals, and the air holes of the combustor inner cylinder on the inlet side of the primary combustion zone are connected to a portion near the combustion nozzle, so that the combustion gas flow is directed to the combustor radius. The air hole is provided at a portion where the direction changes from the axial direction to the axial direction, so that the air flow from the air hole provided in the latter portion becomes a resistance flow against the air flow flowing from the combustor outer cylinder, and a circulating flow is formed near the center. A combustor characterized by: