Radial grading low-emission dual-fuel nozzle structure of gas turbine

Abstract

The invention relates to the technical field of gas turbine nozzles, in particular to a radial graded low-emission dual-fuel nozzle structure of a gas turbine, and aims to solve the problems that a conventional diffusion flame nozzle or a simple premixing nozzle is difficult to maintain low-NOx combustion in a high-load state, and the overall performance of the gas turbine is affected. According to the scheme, the nozzle comprises a first-stage natural gas premixing fuel pipe, a second-stage natural gas premixing fuel pipe on-duty natural gas fuel pipe, a fuel oil auxiliary oil way fuel pipe, a fuel oil main oil way fuel pipe, an on-duty natural gas fuel cavity, a first-stage natural gas premixing fuel cavity, a second-stage natural gas premixing fuel cavity and a nozzle end face air cavity which are arranged on the nozzle. The fuel nozzle comprises a first-stage natural gas premixing swirl vane, a second-stage natural gas premixing swirl vane, a fuel nozzle outer end face swirl vane, a fuel nozzle inner swirler fixator, a fuel main oil way injection device, a fuel auxiliary oil way nozzle, an auxiliary atomization air inlet, an auxiliary atomization device, an on-duty natural gas injection device and a fuel nozzle inner swirler. And the goal of low emission is achieved.

Description

Technical Field

[0001] This invention relates to the field of gas turbine nozzle technology, specifically to a radially staged low-emission dual-fuel nozzle structure for a gas turbine. Background Technology

[0002] Gas turbines, as the core power equipment of offshore oil and gas platforms, are widely used in power generation, natural gas compression, and process drive applications. The unique environment of offshore platforms, characterized by compact space, short maintenance windows, stringent safety requirements, and potentially fluctuating fuel supply, places extremely high demands on the reliability, compactness, fuel adaptability, and low-emission performance of gas turbines. A key aspect of dual-fuel gas turbines is the stability of their combustion organization, ensuring high stability whether the gas or fuel operates alone or in combination. Increasingly stringent environmental regulations require offshore platform gas turbines to achieve extremely low nitrogen oxide (NOx) emissions. Conventional diffusion flame nozzles or simple premixed nozzles struggle to maintain low NOx combustion under high load conditions. Since nozzle design directly determines the combustion performance of the combustion chamber, the nozzle design of a dual-fuel gas turbine determines its overall performance.

[0003] In summary, conventional diffusion flame nozzles or simple premixed nozzles are unable to maintain low NOx combustion under high load conditions, which affects the overall performance of the gas turbine. Summary of the Invention

[0004] The purpose of this invention is to address the problem that conventional diffusion flame nozzles or simple premixed nozzles cannot maintain low NOx combustion under high load conditions, thus affecting the overall performance of gas turbines. This invention proposes a radial staged low-emission dual-fuel nozzle structure for gas turbines.

[0005] The objective of this invention is achieved as follows:

[0006] A radially staged low-emission dual-fuel nozzle structure for a gas turbine includes a primary natural gas premixed fuel pipe, a secondary natural gas premixed fuel pipe, a standby natural gas fuel pipe, a fuel oil auxiliary oil circuit fuel pipe, a fuel oil main oil circuit fuel pipe, a standby natural gas fuel chamber, a primary natural gas premixed fuel chamber, a secondary natural gas premixed fuel chamber, a nozzle end face air chamber, a primary natural gas premixed swirl vane, a secondary natural gas premixed swirl vane, a fuel oil nozzle outer end face swirl vane, a fuel oil nozzle inner swirler retainer, a fuel oil main circuit injection device, a fuel oil auxiliary circuit nozzle, an auxiliary atomizing air inlet, an auxiliary atomizing device, a standby natural gas injection device, and a fuel oil nozzle inner swirler.

[0007] The interior of the first-stage natural gas premixed swirl blade is a hollow cavity, and a natural gas injection hole is opened on the first-stage natural gas premixed swirl blade;

[0008] The hollow cavities of the primary natural gas premixed fuel pipe, the primary natural gas premixed fuel chamber, and the primary natural gas premixed swirl blade are connected in sequence. The natural gas entering the primary natural gas premixed fuel pipe is ejected through the natural gas injection hole of the primary natural gas premixed swirl blade.

[0009] The interior of the secondary natural gas premixed swirl blade is a hollow cavity, and the secondary natural gas premixed swirl blade has two natural gas injection holes.

[0010] The hollow cavities of the secondary natural gas premixed fuel pipe, the secondary natural gas premixed fuel chamber, and the secondary natural gas premixed swirl blade are connected in sequence; the natural gas entering the secondary natural gas premixed fuel pipe is ejected through the natural gas injection hole of the secondary natural gas premixed swirl blade.

[0011] The interior of the swirl vane on the outer end face of the fuel nozzle is a hollow cavity, and there are three natural gas injection holes on the swirl vane on the outer end face of the fuel nozzle.

[0012] The natural gas fuel pipe, the standby natural gas fuel chamber, the hollow cavity of the swirl vane on the outer end face of the fuel nozzle, and the standby natural gas injection device are connected in sequence; the natural gas entering the natural gas fuel pipe enters the standby natural gas injection device through the natural gas injection hole of the swirl vane on the outer end face of the fuel nozzle, and is then ejected by the standby natural gas injection device.

[0013] The fuel line in the auxiliary fuel circuit is connected to the swirler inside the fuel injector.

[0014] The fuel line and the fuel injection device of the main fuel line are connected;

[0015] The auxiliary atomizing air inlet and the auxiliary atomizing device are connected.

[0016] Furthermore, a pressure plate is provided on the nozzle, and the primary natural gas premixed fuel chamber is formed by the cavity between the nozzle and the pressure plate. The nozzle and the pressure plate are welded together.

[0017] Furthermore, the nozzle is covered with a pressure plate two, and the secondary natural gas premixed fuel chamber is formed by the cavity between the nozzle and the pressure plate two, with the nozzle and the pressure plate two being welded together.

[0018] Furthermore, the nozzle is covered with a pressure plate three, and the duty natural gas fuel chamber is formed by the cavity between the nozzle and the pressure plate three, and the nozzle and the pressure plate three are welded together.

[0019] Furthermore, the first-stage natural gas premixed swirl blade is welded to the pressure plate.

[0020] Furthermore, the secondary natural gas premixed swirl blade is welded to the pressure plate.

[0021] Furthermore, the fuel main fuel line fuel pipe is welded to the fuel main fuel line injection device.

[0022] Furthermore, the main fuel injection device is welded to the auxiliary atomizing device.

[0023] Furthermore, the swirl vanes on the outer end face of the fuel nozzle are welded to the on-duty natural gas injection device.

[0024] Furthermore, the fuel auxiliary fuel line nozzle has a threaded structure, and the fuel nozzle internal swirler retainer has an external threaded structure. The fuel auxiliary fuel line nozzle and the fuel nozzle internal swirler retainer are connected by threads to press the fuel nozzle internal swirler tightly.

[0025] Beneficial effects:

[0026] 1. The structure of this invention integrates fuel oil and gas pipelines into the same nozzle, enabling fuel oil combustion alone, gas combustion alone, and fuel oil-gas mixed combustion.

[0027] 2. The structure of this invention arranges the main fuel injection holes in the secondary premixed air flow channel to achieve the effect of full premixing of the main diesel fuel circuit with air, thereby achieving the goal of low emissions.

[0028] 3. The nozzle body has a simple structure with no thin walls or dead zones, making it easy to process by machining or 3D printing additive technology, which greatly reduces processing time.

[0029] 4. The structure is highly compact to adapt to space constraints; it has excellent dual-fuel (gas / liquid) adaptability and rapid, smooth switching capability; it adopts an advanced staged combustion strategy to achieve ultra-low NOx emissions over a wide load range; it has high reliability and easy maintenance; and it optimizes the uniformity of gaseous fuel premixing and the atomization quality of liquid fuel. Attached Figure Description

[0030] Figure 1 This is a cross-sectional view of a radially staged low-emission dual-fuel nozzle structure for a gas turbine according to the present invention;

[0031] Figure 2 This is a perspective view of a radially staged low-emission dual-fuel nozzle structure for a gas turbine according to the present invention;

[0032] Figure 3 This is a front view of a radially staged low-emission dual-fuel nozzle structure for a gas turbine according to the present invention;

[0033] Figure 4 This is a schematic diagram of the natural gas inlet and auxiliary atomizing air inlet of a gas turbine radial staged low-emission dual-fuel nozzle structure according to the present invention.

[0034] Figure 5This is a schematic diagram of a partial internal structure of a radially staged low-emission dual-fuel nozzle structure for a gas turbine according to the present invention;

[0035] Figure 6 This is the present invention. Figure 5 A partial schematic diagram;

[0036] Figure 7 This is a schematic diagram of channel 1 of the present invention;

[0037] Figure 8 This is a schematic diagram of the two channels of the present invention;

[0038] Figure 9 This is a schematic diagram of the three channels of the present invention;

[0039] Figure 10 This is a schematic diagram of the four channels of this invention;

[0040] Figure 11 This is a schematic diagram of the 5-channel invention. Detailed Implementation

[0041] Specific Implementation Method 1: A radially staged low-emission dual-fuel nozzle structure for a gas turbine, comprising a primary natural gas premixed fuel pipe 1, a secondary natural gas premixed fuel pipe 2, a standby natural gas fuel pipe 3, a fuel auxiliary oil circuit fuel pipe 4, a fuel main oil circuit fuel pipe 5, a standby natural gas fuel chamber 6, a primary natural gas premixed fuel chamber 7, a secondary natural gas premixed fuel chamber 8, a nozzle end face air chamber 9, a primary natural gas premixed swirl vane 10, a secondary natural gas premixed swirl vane 11, a fuel nozzle outer end face swirl vane 12, a fuel nozzle inner swirler holder 13, a fuel main oil circuit injection device 14, a fuel auxiliary oil circuit nozzle 15, an auxiliary atomizing air inlet 16, an auxiliary atomizing device 17, a standby natural gas injection device 18, and a fuel nozzle inner swirler 19, all mounted on the nozzle.

[0042] The interior of the first-stage natural gas premixed swirl blade 10 is a hollow cavity, and a natural gas injection hole is opened on the first-stage natural gas premixed swirl blade 10;

[0043] The hollow cavities of the primary natural gas premixed fuel pipe 1, the primary natural gas premixed fuel chamber 7, and the primary natural gas premixed swirl blade 10 are connected in sequence. The natural gas entering the primary natural gas premixed fuel pipe 1 is ejected through the natural gas injection hole of the primary natural gas premixed swirl blade 10.

[0044] The interior of the secondary natural gas premixed swirl blade 11 is a hollow cavity, and the secondary natural gas premixed swirl blade 11 has two natural gas injection holes.

[0045] The hollow cavities of the secondary natural gas premixed fuel pipe 2, the secondary natural gas premixed fuel chamber 8, and the secondary natural gas premixed swirl blade 11 are connected in sequence; the natural gas entering the secondary natural gas premixed fuel pipe 2 is ejected through the natural gas injection hole 2 of the secondary natural gas premixed swirl blade 11.

[0046] The interior of the swirl vane 12 on the outer end face of the fuel nozzle is a hollow cavity, and the swirl vane 12 on the outer end face of the fuel nozzle has three natural gas injection holes.

[0047] The natural gas fuel pipe 3, the standby natural gas fuel chamber 6, the hollow cavity of the swirl vane 12 on the outer end face of the fuel nozzle, and the standby natural gas injection device 18 are connected in sequence; the natural gas entering the natural gas fuel pipe 3 enters the standby natural gas injection device 18 through the natural gas injection hole 3 on the outer end face of the swirl vane 12 of the fuel nozzle, and is ejected by the standby natural gas injection device 18.

[0048] The fuel line 4 in the auxiliary fuel line is connected to the swirler 19 inside the fuel nozzle.

[0049] The fuel main line fuel pipe 5 and the fuel main line injection device 14 are connected;

[0050] The auxiliary atomizing air inlet 16 and the auxiliary atomizing device 17 are connected.

[0051] In this implementation:

[0052] 1. The inlet is the primary natural gas premixed fuel pipe. Natural gas enters the primary natural gas premixed fuel chamber through it, and then enters the primary natural gas premixed swirl vane through the channel in the primary natural gas premixed fuel chamber. It is then sprayed out from the small holes on the primary natural gas premixed swirl vane and mixed with air.

[0053] Path 2: The inlet is a secondary natural gas premixed fuel pipe. Natural gas enters the secondary natural gas premixed fuel chamber through the channel, and then enters the secondary natural gas premixed swirl vane from the secondary natural gas premixed fuel chamber. It is then sprayed out from the small holes on the secondary natural gas premixed swirl vane and mixed with air.

[0054] Route 3: The inlet is the duty natural gas fuel pipe. Natural gas enters the duty natural gas fuel chamber through it, and then enters the cavity connected to the swirl vanes on the outer end face of the fuel nozzle through the channel in the duty natural gas fuel chamber. After passing through the swirl vanes on the outer end face of the fuel nozzle, it is sprayed out from the duty natural gas injection device.

[0055] 4th route: The inlet is the fuel auxiliary oil line fuel pipe, which is sprayed out after passing through the duty nozzle cyclone.

[0056] 5th route: The inlet is the fuel pipe of the main fuel line, which is sprayed out through the fuel injection device of the main fuel line.

[0057] Air entering through the auxiliary atomizing air inlet is ejected through the auxiliary atomizing device.

[0058] Specific implementation method 2: A gas turbine radial staged low emission dual fuel nozzle structure, wherein a pressure plate is provided on the nozzle, and the first stage natural gas premixed fuel chamber 7 is formed by the cavity between the nozzle and the pressure plate, and the nozzle and the pressure plate are welded together.

[0059] Other implementation methods are the same as those in Specific Implementation Method 1.

[0060] Specific implementation method 3: A gas turbine radial staged low emission dual fuel nozzle structure, wherein the nozzle is covered with a pressure plate 2, the secondary natural gas premixed fuel chamber 8 is formed by the cavity between the nozzle and the pressure plate 2, and the nozzle and the pressure plate 2 are welded together.

[0061] Other implementation methods are the same as those in Specific Implementation Method 1.

[0062] Specific implementation method four: A gas turbine radial staged low emission dual fuel nozzle structure, wherein the nozzle is covered with a pressure plate three, the duty natural gas fuel chamber 6 is formed by the cavity between the nozzle and the pressure plate three, and the nozzle and the pressure plate three are welded together.

[0063] Other implementation methods are the same as those in Specific Implementation Method 1.

[0064] Specific implementation method 5: A gas turbine radial staged low emission dual fuel nozzle structure, wherein the first stage natural gas premixed swirl blade 10 is welded to the pressure plate.

[0065] Other implementation methods are the same as those in Specific Implementation Method Two.

[0066] Specific implementation method six: A gas turbine radial staged low-emission dual-fuel nozzle structure, wherein the secondary natural gas premixed swirl blade 11 is welded to the pressure plate 2.

[0067] Other implementation methods are the same as those in Specific Implementation Method 3.

[0068] Specific implementation method seven: A gas turbine radial staged low emission dual fuel nozzle structure, wherein the fuel main oil circuit fuel pipe 5 is welded to the fuel main oil circuit injection device 14.

[0069] Other implementation methods are the same as those in Specific Implementation Method Four.

[0070] Specific implementation method eight: A gas turbine radial staged low emission dual fuel nozzle structure, wherein the main fuel injection device 14 is welded to the auxiliary atomizing device 17.

[0071] Other implementation methods are the same as those in Specific Implementation Method 1.

[0072] Specific Implementation Method Nine: A gas turbine radial staged low-emission dual-fuel nozzle structure, wherein the swirl vane 12 on the outer end face of the fuel nozzle is welded to the duty natural gas injection device 18.

[0073] Other implementation methods are the same as those in Specific Implementation Method 1.

[0074] Specific Embodiment 10: A gas turbine radial staged low-emission dual-fuel nozzle structure, wherein the fuel auxiliary oil passage nozzle 15 has an internal thread structure, the fuel nozzle inner swirler retainer 13 has an external thread structure, the fuel auxiliary oil passage nozzle 15 and the fuel nozzle inner swirler retainer 13 are connected by threads to press the fuel nozzle inner swirler 19 tightly.

[0075] Other implementation methods are the same as those in Specific Implementation Method 1.

Claims

1. A radially staged low-emission dual-fuel nozzle structure for a gas turbine, characterized in that: It includes a primary natural gas premixed fuel pipe (1), a secondary natural gas premixed fuel pipe (2), a standby natural gas fuel pipe (3), a fuel auxiliary fuel line fuel pipe (4), a fuel main fuel line fuel pipe (5), a standby natural gas fuel chamber (6), a primary natural gas premixed fuel chamber (7), a secondary natural gas premixed fuel chamber (8), an air chamber on the nozzle end face (9), a primary natural gas premixed swirl vane (10), a secondary natural gas premixed swirl vane (11), a swirl vane on the outer end face of the fuel nozzle (12), a swirl holder inside the fuel nozzle (13), a fuel main fuel line injection device (14), a fuel auxiliary fuel line nozzle (15), an auxiliary atomizing air inlet (16), an auxiliary atomizing device (17), a standby natural gas injection device (18), and a swirl in the fuel nozzle (19). The interior of the first-stage natural gas premixed swirl blade (10) is a hollow cavity, and a natural gas injection hole is opened on the first-stage natural gas premixed swirl blade (10); The hollow cavities of the primary natural gas premixed fuel pipe (1), the primary natural gas premixed fuel chamber (7) and the primary natural gas premixed swirl blade (10) are connected in sequence. The natural gas entering the primary natural gas premixed fuel pipe (1) is ejected through the natural gas injection hole of the primary natural gas premixed swirl blade (10). The interior of the secondary natural gas premixed swirl blade (11) is a hollow cavity, and the secondary natural gas premixed swirl blade (11) has two natural gas injection holes. The hollow cavities of the secondary natural gas premixed fuel pipe (2), the secondary natural gas premixed fuel chamber (8), and the secondary natural gas premixed swirl blade (11) are connected in sequence; Natural gas entering the secondary natural gas premixed fuel pipe (2) is ejected through the natural gas injection hole 2 of the secondary natural gas premixed swirl vane (11); The interior of the swirl vane (12) on the outer end face of the fuel nozzle is a hollow cavity, and the swirl vane (12) on the outer end face of the fuel nozzle has three natural gas injection holes. The natural gas fuel pipe (3), the duty natural gas fuel chamber (6), the hollow cavity of the swirl vane (12) on the outer end face of the fuel nozzle, and the duty natural gas injection device (18) are connected in sequence; the natural gas entering the natural gas fuel pipe (3) enters the duty natural gas injection device (18) through the natural gas injection hole of the swirl vane (12) on the outer end face of the fuel nozzle, and is ejected by the duty natural gas injection device (18); The fuel line (4) of the fuel auxiliary oil circuit is connected to the fuel nozzle internal swirler (19); The fuel line (5) and the fuel injection device (14) of the main fuel line are connected; The auxiliary atomizing air inlet (16) and the auxiliary atomizing device (17) are connected.

2. The radially staged low-emission dual-fuel nozzle for a gas turbine according to claim 1, characterized in that: The nozzle is covered with a pressure plate, and the primary natural gas premixed fuel chamber (7) is formed by the cavity between the nozzle and the pressure plate. The nozzle and the pressure plate are welded together.

3. The radially staged low-emission dual-fuel nozzle for a gas turbine according to claim 1, characterized in that: The nozzle is covered with a pressure plate two, and the secondary natural gas premixed fuel chamber (8) is formed by the cavity between the nozzle and the pressure plate two. The nozzle and the pressure plate two are welded together.

4. The radially staged low-emission dual-fuel nozzle for a gas turbine according to claim 1, characterized in that: The nozzle is covered with a pressure plate three, and the duty natural gas fuel chamber (6) is formed by the cavity between the nozzle and the pressure plate three. The nozzle and the pressure plate three are welded together.

5. A gas turbine radial staged low-emission dual-fuel nozzle according to claim 2, characterized in that: The first-stage natural gas premixed swirl blade (10) is welded to the pressure plate.

6. A gas turbine radial staged low-emission dual-fuel nozzle according to claim 3, characterized in that: The secondary natural gas premixed swirl blade (11) is welded to the pressure plate.

7. A gas turbine radial staged low-emission dual-fuel nozzle according to claim 4, characterized in that: The fuel main fuel line fuel pipe (5) is welded to the fuel main fuel line injection device (14).

8. The radially staged low-emission dual-fuel nozzle for a gas turbine according to claim 1, characterized in that: The main fuel injection device (14) is welded to the auxiliary atomizing device (17).

9. A gas turbine radial staged low-emission dual-fuel nozzle according to claim 1, characterized in that: The swirl vane (12) on the outer end face of the fuel nozzle is welded to the on-duty natural gas injection device (18).

10. A gas turbine radial staged low-emission dual-fuel nozzle according to claim 1, characterized in that: The fuel auxiliary oil passage nozzle (15) has a threaded structure, and the fuel nozzle inner swirler retainer (13) has an external threaded structure. The fuel auxiliary oil passage nozzle (15) and the fuel nozzle inner swirler retainer (13) are connected by threads to press the fuel nozzle inner swirler (19) tightly.

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