JPS6166019A - Gas turbine combustor - Google Patents

Abstract

PURPOSE:To make it possible to provide a certain allowance for the combustion range of the combustor by connecting a combustion compartment to an exhaust compartment via a bypass pipe provided with a control valve for adjusting the amount of air within the combustion compartment, and exhausting bypass air into the exhaust compartment. CONSTITUTION:The amount of air within a combustion compartment 108 which has been exhausted out of a compressor 101 is controlled from the outside by means of a bypass pipe 112 provided with a control valve 113. Thus, the amount of air which is optimum for continuing to ignite or burn two burners 104 and 106 is secured. As a result, it is possible to reduce the unignition phenomena and load variations to be burdened on the gas turbine at the time of changing a single movement over to a combined operation.

Description

DETAILED DESCRIPTION OF THE INVENTION Field of Industrial Application The present invention is applicable to gas turbines, when igniting a sub-combustor and a main combustor, or when switching from an independent operation of only the sub-combustor to a combined operation of both combustors. It is used in the technical field of adjusting the amount of air in the turbine combustion chamber in order to reduce the occurrence of non-ignition phenomena and gas turbine load fluctuations during switching.

2. Description of the Related Art A conventional gas turbine combustor will be described with reference to FIG.

As shown in FIG. 2, in a two-stage combustion gas turbine combustor having a sub-combustion chamber 104 of a diffusion combustion type and a main combustion chamber 106 of a premix combustion type, compressed air is passed from a compressor 101 through a diffuser 109. or is supplied to the combustion chamber 108,
The air is distributed to the sub-combustor 104 or the main combustor 106 at an appropriate ratio, and is combusted in each combustion chamber. The combustion gas passes through the transition piece 107, is supplied to the turbine 110, and rotates the turbine.

In such conventional gas turbines, the amount of air supplied to the combustor is uniquely determined by the amount of air at the outlet of the compressor.

Therefore, when igniting the auxiliary combustor 104 and the main combustor 106, it is necessary to adjust the amount of fuel supplied to each combustor to create the optimum fuel-air ratio for ignition, and then perform ignition. Therefore, the operating range for normally igniting and burning the main combustor 106 is narrow, and even if the main combustor 106 is ignited normally, load fluctuations on the gas turbine will occur when the main combustor 106 is ignited. .

Problems to be Solved by the Present Invention The present invention is to enable operation of a gas turbine combustor with a wide range of ignition and combustion.

Means for Solving the Problems The present invention takes the following measures in order to solve the above-mentioned problems. That is, a bypass pipe equipped with a control valve for adjusting the amount of air in the combustion casing of the gas turbine is provided to connect the combustion casing and the exhaust casing, and the bypass air is discharged into the exhaust casing. do.

According to the means described above, the combustion range of the combustor can be widened by guiding the bypass air to the outside of the combustion chamber and controlling the amount of air with a control valve provided in the bypass pipe. becomes possible.

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

In FIG. 1, the same reference numerals as those in FIG. 2 described above indicate the same parts.

The air compressed by the compressor 101 is sent to the TIF user 20.
9 and is supplied to the combustion chamber 108, and becomes the air necessary for combustion within the two combustors, the auxiliary combustor 104 and the main combustor 106. Of course, some of that air is also used to cool the combustor metal.

A new bypass pipe 112 is installed in the combustion chamber casing 103.
is provided to connect the combustion chamber 108 and the exhaust chamber 115. This bypass pipe 112 is provided with a control valve 113 for controlling the amount of air in the combustion chamber 108. In the figure, 102 is a compressor casing, 105 is a premix nozzle, 111 is a turbine, and a casing, and arrows indicate air flow.

A bypass pipe 112 is provided with a valve 113 that controls the amount of air discharged from the compressor 101 into the combustion chamber 108.
The two combustors 104,
It is possible to secure the optimum amount of air to sustain the ignition or combustion of 106.

Effects of the Invention According to the configuration described above, the amount of bypass air is increased or decreased when igniting the sub-combustor 104 and the main combustor 106, or when switching from the independent operation of the sub-combustor 104 to the combined operation of both combustors. This makes it possible to prevent non-ignition phenomena,
It is possible to reduce gas turbine load fluctuations when switching from independent operation to combined operation.

[Brief explanation of drawings]

FIG. 1 is a sectional view showing the configuration of a gas turbine combustor according to the present invention, and FIG. 2 is a sectional view of a conventional example. 101...Compressor, 102...Compressor casing,
103... Combustion chamber casing, 104... Secondary combustor, 105... Premix nozzle, 106... Main combustor, 10
7... Transition piece, 108... Combustion casing, 109... Diffuser, 110... Turbine, 111... Turbine casing, 112... Bypass pipe, 113 φ/ Control valve, 115... Exhaust casing. (2 others) Figure 1 No.? Cause

Claims (1)

[Claims] A bypass pipe equipped with a control valve for adjusting the amount of air in the combustion casing of the gas turbine is provided to connect the combustion casing and the exhaust casing, and the bypass air is discharged into the exhaust casing. Gas turbine combustor.