JPS5925038A - Parallel gas turbine - Google Patents

Abstract

PURPOSE:To combine a fuel injector, an ignitor, an ignition detector, and a speed governor by sharing a single combustor with independent gas turbines, and further to eliminate control of the governor for uniformly distributing load on the independent gas turbines. CONSTITUTION:Air to be independently sucked and compressed by compressors 2a and 2b is collected to a combustor 3, where fuel is combusted to be a combustion gas of high temperatures. The combustion gas heated by the combustor 3 is divided to be fed into turbines 1a and 1b, where a heat energy of the combustion gas is converted to a shaft power which is in turn absorbed by the compressors 2a and 2b or the like, and then is transmitted through a reduction gear 4 to an output shaft. With this arrangement, shift of an ignition timing for the independent gas turbines 1a and 1b may be eliminated because of a single combustor 3, and simultaneously the independent gas turbines 1a and 1b are permitted to run at the same gas temperature even under a maximum load condition.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a parallel gas turbine of an open cycle gas turbine and a closed cycle gas turbine.

An example of two conventional parallel gas turbines is shown in FIG.

In the figure, 1a and 1b are turbines, 2a and 2b are compressors, 3a and 3b are combustors, 4 is a reduction gear that connects two sets of gas turbines 1a and 1b using gears, etc., and 5 is a load absorption device. .

That is, as shown in the figure, in the conventional parallel gas turbine, -
One combustor for each set of gas turbines; in the case of two sets of parallel gas turbines, a total of two combustors were provided. For this reason, it had the following five drawbacks.

A, combustor C fuel injection device, ignition device, ignition detection device,
Two sets of speed governors are required.

If the load sharing of each gas turbine does not match during maximum load operation, one gas turbine will become overloaded and the gas temperature will exceed the allowable temperature, so the governor will ensure that each gas turbine is distributed equally. It was necessary to control the load so that it would be distributed appropriately.

C. During startup, if the ignition timing of each gas turbine did not match, there was a risk of an overrun if the fuel accumulated inside the gas turbine with the ignition delay t ignited and burned all at once.

2. As in the previous section, if there is an ignition delay in one of the gas turbines, the rotation of the gas turbine will increase quickly,
The starter remains under high load for a long time, shortening its lifespan.

Note that these drawbacks also apply when three or more sets of gas turbines are connected in parallel.

The present invention is proposed in an attempt to eliminate the above-mentioned drawbacks of the conventional example, and it avoids the duplication of the fuel control device and combustion device that existed in the conventional parallel gas turbine, and also avoids the duplication of the fuel control device and combustion device that are present in the conventional parallel gas turbine. With the aim of equalizing load sharing during malfunctions and peak loads, conventional gas turbines installed - number of combustors for one set of gas turbines, whereas one set of individual gas turbines was installed. The combustor can be shared, and along with this, the fuel injection system,
The ignition device, ignition detection device, and speed control device can also be used in one unit.
Furthermore, there is no need to control the speed governor to equalize the load sharing among the individual gas turbines.

Hereinafter, two preferred embodiments of the present invention will be described.
This will be explained in detail with reference to FIG. 2, which shows the configuration of a parallel gas turbine in the case of a set of gas turbines.

In FIG. 2, la and 1b indicate gas turbines 2a and 2b as compressors, 3 as a combustor, 4 as a speed reduction device, and 5 as a load absorption device.

The gas turbine 1a and the compressor 2a are coaxial,
Further, the gas turbine 1b and the compressor 2b are also coaxially connected. The combustor 3 includes two sets of compressors 2a,
2b, only - pieces are installed, and the combustor outlet side is further divided into two and connected to the turbines 1a and 1b. Arrows in the figure indicate the flow of air and combustion gas. The speed reduction device 4 connects two rotating shafts using gears or the like, and reduces the speed to match the load absorbing device 5.

Next, the operation of the present invention will be described.

The air individually sucked and compressed by the compressors 2a and 2b is collected together in the combustor 3, and high-temperature combustion gas is generated by combustion of fuel.

Combustion gas heated in the combustor 3 is divided into two parts, converted into axial force by the turbines 1a and 1bK, absorbed by a compressor, etc., and then passed through the reduction gear 4 to become axial power. In the present invention, since there is only one combustor 3 (3), there is no difference in ignition timing between the individual gas turbines (in addition, the individual gas turbines are operated at the same gas temperature even during maximum load operation). becomes possible.

According to the present invention, the parallel gas turbine has the following effects. .

a. Since there is only one combustor, the fuel injection device, ignition device, ignition detection device, and speed regulating device can be made into one, which greatly simplifies the fuel system.

b. During maximum load operation, the combustion gas acting on the turbine comes out of one combustor, so each turbine can easily operate at the same gas temperature. In addition, in conventional parallel gas turbines, the speed governor was controlled to equalize the load sharing among the individual gas turbines, and the temperature of the gas acting on the turbine was maintained at the same time, but in the present invention, the load sharing is The speed governor's load roll is completely eliminated (no longer required).

C0 Conventional gas turbines have a delay in ignition (4) The fuel accumulated inside the turbine ignites and burns all at once, so there is a risk of overline, but with the present invention, the ignition timing is shifted. It is true that there is no
Such risks are eliminated.

d. During startup, the starter is not in a high load state due to the difference in ignition timing of each gas turbine, which has a significant effect on improving starter life.

[Brief explanation of the drawing]

Figure 1 is a circuit diagram showing the configuration of a conventional parallel gas turbine.
FIG. 2 is a circuit diagram showing the configuration of the parallel gas turbine of the present invention. la, lb# gas turbine, 2a, 2b...compressor, 3...combustor, 4...reduction device, 5...load absorption device.

Claims (1)

[Claims] In a parallel gas turbine configuration, one combustor is shared by two sets of compressors and gas turbines connected to each other, and the outlet side of the combustor is branched and connected to each of the gas turbines, and a fuel injection device is installed. , a parallel gas turbine characterized by having a single auxiliary device such as an ignition device, an ignition detection device, and a speed governor.