JPS59122729A - Slightly pressurized fuel gas turbine - Google Patents

Abstract

PURPOSE:To eliminate the need of especially disposing a gas compressor so as to reduce the expenditure for installing an apparatus by owing compression of slightly pressurized fuel gas to the shaft power of a gas turbine and using its revolution and drive power. CONSTITUTION:A gas supply chamber 7 having an air intake port is disposed at the air supply side of a compressor 2 and a slightly pressurized fuel gas pipe 12 is connected thereto via a flow control valve 11. Air is thereby carried from the intake port 6 to the gas supply chamber 7 by the compressor 2 which is driven by a gas turbine 1 and is compressed along with the slightly pressurized fuel gas which is fed from nozzles formed in ejecttion pipes 9 and 10 in the form of mixture gas, which is squeezed to be sent into a combustion chamber 3 and ignited to be burnt therein. The need of independently installing a special gas compressor is therefore eliminated so that the expenditure for installing an apparatus may be reduced extremely.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention is aimed at reducing boil off gas generated during low temperature storage of liquefied fuel gas such as LPG + LNG.
) and other gas turbines that use low-pressure gas as fuel.

1. With the recent demands for pollution prevention and effective use of energy resources, LPG and LNG'! Gas turbines that use fF liquefied fuel gas as fuel have begun to generate electricity. In this case, the stored liquefied fuel gas is normally used by forced vaporization, but a considerable amount of evaporated gas is generated during low-temperature storage of the liquefied fuel gas, and the use of such a low-pressure gas is also desired. 1 Conventionally, when such low-pressure fuel gas is used as fuel for a gas turbine, it is pressurized to about 20 to 30 Ky/tri using a fuel gas compressor connected via piping from a liquefied fuel gas low-temperature storage tank. After that,
This pressurized gas was generally pumped into the combustion chamber of a gas turbine. However, installing such a large fuel gas compressor individually requires manufacturing and installation costs, operating costs, and installation space.
This is accompanied by various economic disadvantages.

The present invention aims to overcome the above-mentioned problems associated with operating a gas turbine using low-pressure fuel gas, and the present invention is designed to compress low-pressure fuel gas by the rotational force of a shaft driven by the gas turbine. This is what I did. According to the present invention, in a gas turbine including a gas turbine, an air compressor, and a combustion chamber provided on the same axis, a low pressure fuel gas is supplied upstream of the air compressor, and the fuel gas is supplied to the air compressor together with the air. A fuel gas compressor that is compressed or driven by the rotation of the shaft is provided on the shaft, and after the low pressure fuel gas is compressed by the fuel gas compressor, it is supplied to the combustion chamber. A method of operating a gas turbine using low pressure fuel gas is provided. More specifically, the present invention provides an air compressor and a gas turbine on the same axis, communicates between the compressor and the gas turbine via a combustion chamber, and provides low-pressure fuel gas in the air supply chamber of the compressor. Provided is a low-pressure fuel gas turbine, characterized in that a jet pipe is provided so that a mixture of air and low-pressure fuel gas is simultaneously compressed through the same compressor and then pumped to a combustion chamber. be done.

In addition, the low pressure gas in the present invention refers to the evaporative gas of liquefied fuel gas such as LPG or LNG and the number Ky/c#! generated from related equipment such as transportation piping. means low pressure gas. The pressure of the evaporated gas is usually 2 (1 (1 to 30
It is 00 dragon.

The invention will now be explained in more detail with reference to the drawings. FIG. 1 is an explanatory diagram showing one embodiment of the gas turbine of the present invention. In the figure, numeral 1 is a gas turbine output, 2 is a compressor, 3 is a combustion chamber, and 4 is a gas turbine output receiving part such as a generator. be. The rotors of the gas turbine 1, the compressor 2, and the generator 4 are mounted on a common rotating shaft 5, and as the tanabine 1 rotates, the compressor 2 and the generator 4 are also rotationally driven together with the rotating shaft 5. .

A gas supply chamber 7 having an air intake is installed on the air supply side of the compressor 2. This gas supply chamber 7 has a low pressure fuel gas pipe 12 connected to a low pressure fuel gas pipe 12 via a flow rate control valve 11. A fuel gas supply pipe 8 is inserted, and annular gas spray pipes 9, 10 are connected to the tip thereof, and the low pressure fuel gas introduced into this ejection pipe is discharged from the ejection pipe 9. It is ejected from a nozzle installed in IO.

Therefore, the air from the compressor 2 driven by the gas turbine 1 is guided through the intake port 6 to the gas supply chamber 7, and is compressed by the compressor 2 together with the low-pressure fuel gas from the jet pipes 9 and 10. , a mixed gas is sent under pressure to the combustion chamber 3, where it is ignited and combusted. The obtained combustion gas is fed into a gas turbine l
There, the gas turbine is rotated and its output is transmitted to the generator 4. Combustion exhaust gas is exhausted from the exhaust port 13. For safety reasons, a flame arrester 1 may be installed on the piping connecting the combustion chamber 3 and the compressor 2, if necessary.
4, etc., to prevent backfire and prevent accidents such as explosions and fires of equipment such as compressors.

The model, material, etc. of the flame arrester should be selected appropriately depending on the conditions.

In the gas turbine described above, after being ejected from the ejection pipes 9 and 10, the low-pressure fuel gas enters the compressor together with air and is compressed, and the amount of ejection thereof is adjusted to an appropriate combustion range by the S-sive 11. Further, the ejection pipes 9 and 10 for the low pressure fuel gas are preferably arranged as close as possible to the front surface of the compressor 2, and although the ejection pipes can take various shapes, Generally, it is annular and is composed of one or more members.

In the present invention, as described above, the low pressure fuel gas is
It is compressed by the rotational force of a shaft driven by a gas turbine, and as shown in Figure 2, as a foreign compression method of compressing air and low-pressure fuel gas at the same time, as shown in Figure 2, It is also possible to provide a compressor on the drive shaft of the gas turbine and perform compression with this gas compressor. That is, according to another aspect of the present invention, an air compressor, a low pressure fuel gas compressor, and a gas turbine are provided coaxially, and the air compressor and the gas turbine are communicated via a combustion chamber. Further, the micro-pressure fuel gas compressor is connected to the combustion chamber, and after the micro-pressure fuel gas is compressed in the micro-pressure fuel gas compressor provided coaxially with the air compressor, the micro-pressure fuel gas is compressed into the combustion chamber. A low pressure fuel gas turbine is provided.

In FIG. 2, the same reference numerals as in FIG. 1 indicate the same members. In this embodiment, the shaft 5 is extended into the supply chamber 7, and a low-pressure fuel gas compressor 21 is connected to the shaft end, and a low-pressure fuel gas supply pipe 8 is connected to the inlet side of the compressor 21. One end of a compressed gas conduit 22 is connected to the outlet side, and the other end of the compressed gas conduit 22 is opened to the combustion chamber 3. Therefore, the low pressure fuel gas compressor 21 is also rotationally driven by the drive of the turbine 1, and the low pressure fuel gas from the supply pipe 8 is compressed and sent under pressure to the combustion chamber 3 through the conduit 22, and from the air compressor 2. is mixed with compressed air and ignites and burns. Although the fuel gas compressor 21 is located in front of the air compressor 2 and inside the supply chamber 7 in FIG.
As described above, according to the present invention, the compression of the low pressure fuel gas is directly applied to the axial force of the gas turbine and the rotational drive thereof is utilized. Unlike conventional methods, there is no need to separately install a special gas compressor, and equipment costs can be greatly reduced. Since it is done directly, it is also more efficient from an energy standpoint.

[Brief explanation of the drawing]

FIG. 1 is an explanatory diagram showing one embodiment of the gas turbine of the present invention, and FIG. 2 is an explanatory diagram showing another embodiment. l... Gas turbine, 2... Compressor, 3... Combustion chamber, 4... Generator, 5... Rotating shaft, 8... Low pressure fuel gas supply pipe, 9, 10. ...Low pressure fuel gas ejection pipe, 2
Single low pressure fuel gas compressor. Agent: Patent attorney Toshiaki Ikeura, 1) 1 SI'72 B:

Claims (3)

[Claims] (1) Install an air compressor and a gas turbine on the same axis,
The air compressor and the gas turbine are connected through a combustion chamber, and a low-pressure fuel gas jet pipe is disposed within the air supply chamber of the air compressor to extract output from the shaft end. A low-pressure fuel gas turbine characterized by: (2) An air compressor, a low-pressure fuel gas compressor, and a gas turbine are installed on the same shaft, and the air compressor and the gas turbine are communicated via a combustion chamber, and the low-pressure fuel gas is compressed. A low-pressure fuel gas turbine characterized in that the engine is connected to a combustion chamber and output is extracted from the shaft end. (3) In a gas turbine consisting of a gas turbine, an air compressor, and a combustion chamber installed on the same axis, low-pressure fuel gas is supplied upstream of the air compressor and compressed together with air by the air compressor. Alternatively, a fuel gas compressor driven by the rotation of the shaft is provided on the 11fl+, and the micro-pressure fuel is compressed by the fuel gas compressor and then supplied to the combustion chamber. How to operate a gas turbine using gas.