Natural gas supply structure for gas turbine

Abstract

The invention discloses a natural gas supply structure for a gas turbine and relates to a natural gas supply structure. The problems that a fuel supply structure of a gas turbine is poor in gas flow accuracy and large in installation and maintenance work difficulty are solved. The first annular pipe, the second annular pipe and the third annular pipe are designed in a two-half split mode and can be disassembled and assembled in a split mode in the assembling and disassembling process, and the manufacturing, assembling, disassembling and maintaining difficulty is lowered; the three annular pipes exist independently, gas can be supplied independently or jointly according to a control program, pressure sensors are installed on gas supply pipelines of the three annular pipes, pressure fluctuation can be monitored at any time and fed back to a control system, fuel pressure can be accurately measured, and the problem that the gas inflow is difficult to accurately control is solved. The invention belongs to the technical field of gas turbine gas supply equipment.

Description

Technical Field

[0001] The present invention relates to a natural gas supply structure, in particular to a natural gas supply structure for a gas turbine, and belongs to the technical field of gas turbine gas supply equipment. Background Art

[0002] The natural gas supply pipes of gas turbines deliver a stable supply of fuel to the nozzles. Currently, pressure losses in pipes and valves make it difficult to precisely control the amount of gas flowing through these pipes. This is particularly true at low flow rates, where gas flow accuracy is poor, impacting overall performance. Gas turbines are typically compact in design and have complex piping. Installation and disassembly of these pipes requires disassembly of numerous peripheral components, making installation and maintenance complex and challenging.

[0003] In summary, how to propose a natural gas supply structure to address the above technical issues has become an urgent problem to be solved by those skilled in the art. Summary of the Invention

[0004] In view of the above-mentioned deficiencies in the prior art, the present invention provides a natural gas supply structure for a gas turbine.

[0005] The technical solution of the present invention is: a natural gas supply structure for a gas turbine, comprising a first annular pipe, a second annular pipe and a third annular pipe arranged coaxially.

[0006] The first annular pipe is installed on the casing of the gas turbine through a fixed support, and the second annular pipe and the third annular pipe are both installed on the gantry through pipe clamps, and the gantry is supported on the foundation of the gas turbine.

[0007] The first annular tube, the second annular tube and the third annular tube each include two semicircular fuel pipes and two pipe joints, and the fuel pipes are butt-jointed via the pipe joints.

[0008] The first annular tube, the second annular tube and the third annular tube are all integrally provided with a fuel inlet pipe.

[0009] The first annular pipe, the second annular pipe and the third annular pipe are all connected to the combustion chamber nozzle of the gas turbine through the air supply pipeline.

[0010] Pressure sensors are installed on the air supply pipelines of the first annular pipe, the second annular pipe and the third annular pipe, and a check valve and a purge air pipe are also installed on the air supply pipeline of the third annular pipe.

[0011] Compared with the prior art, the present invention has the following effects:

[0012] The first annular tube 1, the second annular tube 2 and the third annular tube 3 all adopt a two-half split design, which can be separated and disassembled during installation and disassembly, reducing the difficulty of manufacturing, installation, disassembly and maintenance; and the three annular tubes exist independently, and can supply air independently or jointly according to the control program. A pressure sensor 8 is installed on the air supply pipe 4 of the three annular tubes, which can monitor pressure fluctuations at any time and feed back to the control system, thereby realizing accurate measurement of fuel pressure and solving the problem of difficult accurate control of intake volume. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 is an axonometric drawing of the present invention;

[0014] Figure 2 This is a front view of the first annular tube 1, the second annular tube 2 and the third annular tube 3 of the present invention;

[0015] Figure 3 It is a partial view of the first annular tube 1, the second annular tube 2 and the third annular tube 3 of the present invention;

[0016] Figure 4 It is a partial view of the first annular tube 1 of the present invention;

[0017] Figure 5 yes Figure 4 Cross-sectional view in the direction of A;

[0018] Figure 6 This is a schematic diagram of the joint between the second annular tube 2 and the third annular tube 3 of the present invention;

[0019] Figure 7 This is a schematic diagram of the joint of the first annular tube 1 of the present invention;

[0020] Figure 8 Schematic diagram of the first annular tube 1 and the gas supply pipeline 4 of the present invention;

[0021] Figure 9 is a schematic diagram of the second annular tube 2 and the gas supply pipeline 4 of the present invention;

[0022] Figure 10 It is a schematic diagram of the third annular tube 3 and the air supply pipeline 4 of the present invention.

[0023] In the figure: 1. first annular tube; 2. second annular tube; 3. third annular tube; 4. air supply pipe; 5. fixed support; 6. pipe clamp; 7. check valve; 8. pressure sensor; 10. purge air pipe; 100. pipe joint. DETAILED DESCRIPTION

[0024] In order to make the purpose, features and advantages of the present invention more obvious and easy to understand, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0025] Specific implementation method 1: Combination Figures 1 to 10 The present embodiment is described. A natural gas supply structure for a gas turbine in the present embodiment includes a first annular pipe 1 , a second annular pipe 2 , and a third annular pipe 3 that are coaxially arranged.

[0026] The first annular pipe 1 is installed on the casing of the gas turbine through a fixed support 5, and the second annular pipe 2 and the third annular pipe 3 are both installed on the gantry through pipe clamps 6. The gantry is supported on the foundation of the gas turbine. This arrangement can effectively reduce the layout space of the three annular pipes.

[0027] The first annular tube 1, the second annular tube 2 and the third annular tube 3 each include two semicircular fuel pipes and two pipe joints 100, and the fuel pipes are butt-jointed via the pipe joints 100. This arrangement fully takes into account the limited space and complexity of the pipelines near the combustion engine and the large number of pipelines around each annular tube, so the two fuel pipes are butt-jointed to achieve the purpose of saving space and facilitating installation and maintenance.

[0028] Furthermore, the pipe joint 100 on the first annular pipe 1 is a universal pipe joint, such as a universal straight-through pipe joint disclosed in the utility model patent with publication number CN203010058U in the prior art.

[0029] Furthermore, the fuel pressure in the second annular tube 2 and the third annular tube 3 is relatively high, so the pipe joints 100 on the second annular tube 2 and the third annular tube 3 are both clamp-type pipe joints, such as the clamp-type non-welded pipe joints disclosed in the utility model patent with announcement number CN2444102Y in the prior art.

[0030] A fuel inlet pipe is integrally provided at the four o'clock direction of the first annular tube 1, the second annular tube 2 and the third annular tube 3. Such a configuration facilitates the connection of an external gas pipeline.

[0031] The first annular pipe 1, the second annular pipe 2 and the third annular pipe 3 are all connected to the combustion chamber nozzle of the gas turbine through the air supply pipe 4. With this arrangement, the three annular pipes are independent of each other and can supply air independently or jointly according to the control program; the air supply pipes 4 of the first annular pipe 1, the second annular pipe 2 and the third annular pipe 3 are all installed with pressure sensors 8, and the air supply pipe 4 of the third annular pipe 3 is also installed with a check valve 7 and a purge air pipe 10.

[0032] Specific implementation method 2: Combination Figures 1 to 10 To illustrate this embodiment, in this embodiment, the butting surfaces of the first annular tube 1 , the second annular tube 2 and the third annular tube 3 all have included angles with the center plane of the casing.

[0033] Preferably, the angle between the butt joint surface of the first annular tube 1 and the center plane of the casing is 15°; the angle between the butt joint surfaces of the second annular tube 2 and the third annular tube 3 and the center plane of the casing are both 11°.

[0034] Furthermore, 16 air supply lines 4 are mounted in a circular array on the first annular tube 1, one of which is fitted with a pressure sensor 8. This arrangement allows for constant monitoring of pressure fluctuations and accurate recording of fuel pressure at the nozzle inlet. The axis of each air supply line 4 forms a 30° angle with the axis of the first annular tube 1, creating a radial arrangement of the air supply lines 4, saving installation space and ensuring a rational routing.

[0035] Furthermore, 16 air supply lines 4 are mounted in an annular array on the second annular tube 2, one of which is equipped with a pressure sensor 8. This arrangement allows for constant monitoring of pressure fluctuations and accurate recording of the fuel pressure at the nozzle inlet. The axis of the air supply line 4 is parallel to the axis of the second annular tube 2.

[0036] Furthermore, 16 air supply pipes 4 are installed on the third annular tube 3 in an annular array, and a pressure sensor 8 is installed on one of the air supply pipes 4. With this arrangement, pressure fluctuations can be monitored at any time, and the fuel pressure at the nozzle inlet can be accurately recorded; and a check valve 7 and a purge air pipe 10 are installed on all 16 air supply pipes 4, and the purge air pipe 10 is arranged on the pipeline between the check valve 7 and the combustion chamber nozzle.

[0037] Due to the low pollution emission requirements, the gas turbine in this embodiment needs to increase the fuel supply of the first annular pipe 1 and the second annular pipe 2 and cut off the air supply of the third annular pipe 3 under high load, so that the fuel is in a lean combustion state, achieving efficient combustion and reducing pollutant emissions; because after the external air pipeline stops supplying air to the third annular pipe 3, the pressure at the outlet of the combustion chamber nozzle is high and the pressure inside the third annular pipe 3 is low, a high-temperature gas backflow problem will occur, so a check valve 7 and a purge air pipe 10 are installed on all the air supply pipes 4. After the air supply is stopped, the purge air pipe 10 is connected to the purge gas (such as nitrogen) to purge the fuel, which can thoroughly clean the residual natural gas in the fuel pipeline and fill the interior with nitrogen. The return valve 7 can ensure that the high-temperature gas cannot flow back, thereby ensuring the safety of the entire machine.

[0038] Other components and connection relationships are the same as those in the first embodiment.

[0039] Specific implementation method three: Combination Figures 1 to 10 To illustrate this embodiment, the first annular tube 1, the second annular tube 2, and the third annular tube 3 are all made of stainless steel. Other components and connection relationships are the same as those in the first or second embodiment.

[0040] Specific implementation method four: Combination Figures 1 to 10 To illustrate this embodiment, the air supply pipeline 4 in this embodiment is a metal hose. Preferably, a corrugated tube with a stainless steel braided sheath is selected. With this arrangement, the air supply pipeline 4 can compensate for displacement changes with temperature when the unit is working, and can also absorb the vibration caused by the operation of the unit, avoiding the risk of damage to the pipeline during operation.

[0041] Other components and connection relationships are the same as those in the first, second or third embodiment.

[0042] How it works

[0043] Combine Figures 1 to 10 The working principle of the present invention is described:

[0044] The first annular pipe 1 is installed on the casing of the gas turbine through a fixed support 5, and the second annular pipe 2 and the third annular pipe 3 are both installed on the gantry through pipe clamps 6. The gantry is supported on the foundation of the gas turbine to reduce the layout space of the three annular pipes.

[0045] The first annular tube 1, the second annular tube 2 and the third annular tube 3 each include two semicircular fuel pipes and two pipe joints 100, and the fuel pipes are butt-jointed via the pipe joints 100. This arrangement fully takes into account the limited space and complexity of the pipelines near the combustion engine and the large number of pipelines around each annular tube, so the two fuel pipes are butt-jointed to achieve the purpose of saving space and facilitating installation and maintenance.

[0046] The first annular pipe 1, the second annular pipe 2 and the third annular pipe 3 are all connected to the combustion chamber nozzle of the gas turbine through the air supply pipe 4. With this arrangement, the three annular pipes are independent of each other and can supply air independently or jointly according to the control program.

[0047] Pressure sensors 8 are installed on the air supply lines 4 of the first annular tube 1, the second annular tube 2 and the third annular tube 3. On the other hand, they can monitor pressure fluctuations at any time and accurately record the fuel pressure at the nozzle inlet.

[0048] The present invention has been disclosed as above in terms of preferred embodiments, but this is not intended to limit the present invention. Any simple modifications, equivalent changes, and modifications made to the above implementation cases by any person skilled in the art without departing from the content of the technical solution of the present invention based on the technical essence of the present invention are still within the scope of the technical solution of the present invention.

Claims

1. A natural gas supply structure for a gas turbine, characterized by: It comprises a first annular tube (1), a second annular tube (2) and a third annular tube (3) which are coaxially arranged; The first annular pipe (1) is mounted on a casing of a gas turbine via a fixed support (5), and the second annular pipe (2) and the third annular pipe (3) are both mounted on a gantry via pipe clamps (6), and the gantry is supported on a foundation of the gas turbine; The first annular tube (1), the second annular tube (2) and the third annular tube (3) each comprise two semicircular fuel pipes and two pipe joints (100), and the fuel pipes are butt-jointed via the pipe joints (100); The first annular tube (1), the second annular tube (2) and the third annular tube (3) are all integrally provided with a fuel inlet pipe; The first annular pipe (1), the second annular pipe (2) and the third annular pipe (3) are all connected to the combustion chamber nozzle of the gas turbine through an air supply pipeline (4); Pressure sensors (8) are installed on the air supply pipelines (4) of the first annular tube (1), the second annular tube (2) and the third annular tube (3), and a check valve (7) and a purge air pipe (10) are also installed on the air supply pipeline (4) of the third annular tube (3).

2. The natural gas supply structure for a gas turbine according to claim 1, characterized in that: There is an included angle between the butting surfaces of the first annular tube (1), the second annular tube (2) and the third annular tube (3) and the center plane of the casing.

3. The natural gas supply structure for a gas turbine according to claim 2, characterized in that: Sixteen air supply pipes (4) are installed on the first annular tube (1) in an annular array, and a pressure sensor (8) is installed on one of the air supply pipes (4); an axis of the air supply pipe (4) and an axis of the first annular tube (1) form an angle.

4. A natural gas supply structure for a gas turbine according to claim 3, characterized in that: Sixteen air supply pipelines (4) are installed on the second annular tube (2) in an annular array, and a pressure sensor (8) is installed on one of the air supply pipelines (4); the axis of the air supply pipeline (4) is parallel to the axis of the second annular tube (2).

5. The natural gas supply structure for a gas turbine according to claim 4, characterized in that: Sixteen air supply pipelines (4) are installed on the third annular tube (3) in an annular array, and a pressure sensor (8) is installed on one of the air supply pipelines (4); The 16 air supply pipelines (4) are all equipped with a check valve (7) and a purge air pipe (10), and the purge air pipe (10) is arranged on the pipeline between the check valve (7) and the combustion chamber nozzle.

6. The natural gas supply structure for a gas turbine according to claim 5, characterized in that: The first annular tube (1), the second annular tube (2) and the third annular tube (3) are all made of stainless steel.

7. The natural gas supply structure for a gas turbine according to claim 6, characterized in that: The air supply pipeline (4) is a metal hose.

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