JPH0439395Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Technical Field of the Invention] The present invention relates to a fuel supply device for gas turbine equipment, and in particular, to a gas turbine that can obtain good combustion conditions for multiple types of fuel. Regarding fuel supply devices for equipment.

[Technical background of the invention and its problems]

Liquid fuels such as light oil and kerosene have traditionally been used as fuel for gas turbines, but in recent years, liquefied natural gas (hereinafter referred to as LNG) and liquefied propane gas (hereinafter referred to as
It's called LPG. ) and other gaseous fuels are often used. Recently, many types of gas turbine equipment are designed to use multiple types of gaseous fuels to ensure stable plant operation.

FIG. 4 shows a gas turbine power generation facility equipped with a device for supplying two types of gaseous fuels, LNG and LPG. According to this equipment, LPG fuel or LNG fuel fed through an LPG fuel supply pipe 1 or an LNG fuel supply pipe 2 is injected into a combustor 4 by a fuel injection nozzle 3 and combusted together with compressed air from a compressor 5G. be done. The gas turbine 6 is driven by this combustion gas, and the generator 7 is operated. In this case, the amount adjustment for each fuel is
This is done by operating stop valves 8 and 9 and flow control valves 11 and 12 provided in each fuel supply pipe 1 and 2, respectively.

However, in such conventional gas turbine equipment, the fuel injection nozzle 3 is commonly used for different types of fuel, so it is difficult to always achieve a good injection effect for the different characteristics of each fuel. Therefore, it was impossible to maintain optimal combustion conditions at all times. As a result, local abnormally high temperature areas occur in the combustion gas, and it is difficult to reduce NOx.
The drawback was poor fuel efficiency.

It is also generally known to have a plurality of fuel systems each individually connected to a combustor via a combustion injection nozzle.

When the calories of the fuels differ, it is more efficient to use individual nozzles according to the calories of each fuel than to use a single nozzle, but in this case,
There was a problem in which the fuel gas and high-temperature air inside the combustor flowed back into the fuel pipe connecting the combustion injection nozzle and fuel control valve of the fuel system that was not in use, creating a risk of explosion.

In particular, when the fuel injection nozzle and the fuel control valve are connected by a long pipe, the fuel pipe is filled with a mixture of a large amount of fuel gas and high-temperature air.

In addition, the fuel system that is not in use is isolated by a fuel control valve, but this fuel control valve is not necessarily a completely sealed valve, so the high temperature air and fuel gas can flow back through this valve. There was also a risk that the fuel could flow into the fuel system when it was not in use.

[Purpose of invention]

Therefore, the present invention eliminates the drawbacks of such conventional fuel supply devices for gas turbine equipment, allows multiple types of gaseous fuel to be combusted well at all times, and also allows combustion to be carried out to the fuel pipes of the fuel system to which fuel is not being supplied. The purpose of the present invention is to provide a device that reliably prevents the backflow of high-temperature gas inside a container.

[Summary of the idea]

In order to achieve the above object, the fuel supply device for gas turbine equipment according to the present invention is a fuel supply device for gas turbine equipment that appropriately supplies a plurality of types of gaseous fuel to a fuel chamber for operation. A plurality of fuel supply pipes each independently connected to a combustor through the most suitable fuel injection nozzle and sequentially provided with a fuel stop valve and a flow control valve in the middle;
A plurality of air purge pipes disposed between the discharge side of the compressor and the downstream side of the flow rate control valve of each of the fuel supply pipes for extracting a part of the compressed air of the compressor and guiding it into each of the fuel supply pipes. air supply pipes, and air purge stop valves that are interposed in the middle of each air supply pipe and open when fuel is not being supplied from the fuel supply pipes communicating with the air supply pipes.

This allows multiple fuels to be supplied to the combustor separately in good condition, and also allows the compressed air in the compressor to pass through the open air purge stop valve and air supply pipe into the fuel pipes that are not supplying fuel. This makes it possible to reliably prevent high-temperature gas in the combustor from flowing back into this piping.

[Example of idea]

Embodiments of the present invention will be described in detail below with reference to the drawings.

In FIG. 1, the same components as the conventional gas turbine power generation equipment shown in FIG. 4 are represented by the same symbols.
The combustor 4 has an LPG fuel supply pipe 21 and an LNG
The fuel supply pipe 22 is connected to the fuel injection nozzles 23 and 24.
are connected via. These fuel injection nozzles 23 and 24 are the ones most suitable for each type of fuel used, so that fuel injection can always be performed satisfactorily. In addition, both the fuel supply pipes 2
1 and 22, stop valves 25 and 22 suitable for each fuel supply are provided.
26 and flow control valves 27 and 28 are provided, respectively, so that a predetermined amount of fuel can be supplied very efficiently.

Further, air supply pipes 30 and 31 for air purge are connected to the outlet side portion of the compressor 5, and each air supply pipe 30 and 31 is connected to the LPG fuel supply pipe 21.
and LNG fuel supply pipe 22, respectively. Each air supply pipe 30, 31 has a flow control valve 27, 28 provided in each fuel supply pipe 21, 22.
The fuel supply pipes 21 and 22 are connected to downstream portions of the fuel supply pipes 21 and 22, respectively, and are adapted to feed a portion of the compressed air within the compressor into the respective fuel supply pipes 21 and 22. Further, an air purge stop valve 32, an air purge stop valve 32,
33 are provided respectively.

In gas turbine equipment having such a configuration, when LPG fuel is used, the stop valve 25 of the LPG fuel supply pipe 21 is opened, the flow control valve 27 is opened to a predetermined opening degree, and the LNG fuel supply pipe 22 is opened. stop valve 26 and flow control valve 28
Keep it fully closed. As a result, only LPG fuel is introduced into the combustor 4, and operation is performed by burning the LPG fuel. In this case, LPG fuel is
Since the fuel is injected into the combustor 4 through the fuel injection nozzle 23 suitable for LPG fuel, extremely good combustion conditions can be obtained.

At this time, the air purge stop valve 33 of the air supply pipe 31 is opened (the air purge stop valve 32 of the air supply pipe 30 is fully closed), and a portion of the compressed air is released.
The LNG is introduced into the fuel supply pipe 22 as air for air purge. This air purge can prevent the LPG fuel from flowing back into the LNG fuel supply pipe 22 from inside the combustor 4,
The danger of explosion due to accumulation of fuel gas can be avoided.

Next, when operating with LNG fuel,
Open the stop valve 26 and flow control valve 28 of the LNG fuel supply pipe 22, and open the stop valve 25 of the LPG fuel supply pipe 21,
The flow rate control valve 27 is kept fully closed, and the air purge stop valve 32 of the air supply pipe 30 is kept open (the air purge stop valve 33 of the air supply pipe 31 is kept fully closed).

As a result, LNG fuel can be supplied through the fuel injection nozzle 24 suitable for it, and an optimal combustion state can be obtained.
Backflow of LNG fuel to the fuel supply pipe 21 can be prevented.

In the embodiment shown in FIG. 2 (the same components as in FIG. 1 are represented by the same symbols), double air purge stop valves 40, 41 and 42, 43 are installed in the middle of the air supply pipes 30 and 31 for air purge, respectively. and between each stop valve 40, 41 and 42,
Atmospheric discharge pipes 44 and 45 are branched from between 43, respectively. Furthermore, each of the above atmospheric discharge pipes 4
There are also stop valves 46 and 47 for opening to the atmosphere in the middle of 4 and 45.
are provided for each.

In this way, by providing double air purge stop valves in the air supply pipes 30 and 31, it is possible to reliably prevent fuel leakage due to valve leakage or valve malfunction, and in the event that leaked fuel is compressed. It can be released into the atmosphere before reaching Aircraft 5. Therefore, the risk of explosion can be completely prevented. In this case, the two air purge stop valves and the atmosphere release stop valve on the fuel supply side are kept fully closed, while the two air purge stop valves and the atmosphere release valve on the side that does not supply fuel are fully opened.

Furthermore, in the embodiment shown in FIG. 3 (the same components as in FIG. 2 are represented by the same symbols), the fuel supply pipe 21,
22 stop valves 25, 26 and flow control valves 27, 28
Atmospheric discharge pipes 50 and 51 are branched from between the two, and atmospheric release stop valves 52 and 53 are provided in the middle of each of the atmospheric discharge pipes 50 and 51, respectively. Further, each of these atmospheric discharge pipes 50, 51 is connected to atmospheric discharge pipes 44, 45 extending from the air supply pipes 30, 31.
are combined into one book. A blower (not shown) is provided in this single atmospheric discharge pipe to forcibly discharge residual fuel.

In this way, no gas from the fuel system on the side to which fuel is not supplied can be left in the guide, and a gas turbine with extremely high safety can be obtained.

[Effect of idea]

As described above, according to the present invention, each fuel supply pipe and the combustor are connected through the fuel injection nozzle most suitable for each fuel, so that optimal combustion can be performed for each fuel used. Combustion efficiency can be increased. Moreover, by forcibly guiding a portion of the compressed air in the compressor as air purge air to the fuel piping that is not supplying fuel, it is possible to ensure that high-temperature gas in the combustor does not flow back into this piping. It has the effect of being able to prevent it.

[Brief explanation of the drawing]

Fig. 1 is an explanatory diagram of a gas turbine equipment system according to an embodiment of the present invention, Figs. 2 and 3 are explanatory diagrams of a gas turbine equipment system according to another embodiment of the invention, and Fig. 4 is an explanatory diagram of a gas turbine equipment system according to another embodiment of the invention. It is a system explanatory diagram showing turbine equipment. 4... Combustor, 5... Compressor, 6... Gas turbine, 7... Generator, 21, 22... Fuel supply pipe, 23, 24... Fuel injection nozzle, 25, 26
... Stop valve, 27, 28 ... Flow rate control valve, 30,
31...Air supply pipe, 32, 33, 40, 41,
42, 43, 52, 53...Air purge stop valve,
44, 45, 50, 51...Atmospheric discharge pipe.

Claims (1)

[Scope of utility model registration request] In a fuel supply system for gas turbine equipment that supplies multiple types of gaseous fuel to the fuel chamber as appropriate for operation, each fuel is independently connected to the combustor through the fuel injection nozzle most suitable for each fuel. A plurality of fuel supply pipes each having a fuel stop valve and a flow control valve interposed therein in sequence are arranged between the discharge side of the compressor and the downstream side of the flow control valve of each of the fuel supply pipes. A plurality of air supply pipes for air purge extracting a portion of the compressed air and guiding it into each of the fuel supply pipes, and a fuel supply pipe interposed in the middle of each of the air supply pipes and communicating with the air supply pipe. A fuel supply device for gas turbine equipment, comprising an air purge stop valve that opens when fuel is not being supplied.