Ignition starting device and gas turbine

Abstract

The present application discloses an ignition and starting device and a gas turbine. The ignition and starting device comprises a nozzle body, an ignition nozzle, a swirler, and a bushing. The nozzle body comprises a nozzle seat and a flame rod. The nozzle seat is provided with an oil inlet channel and an oxygen supply channel. One end of the ignition nozzle extends into the flame rod. The swirler comprises a swirler seat and a swirler rod. A fuel swirl channel is formed between the inner wall of the swirler rod and the outer wall of the flame rod. An oil groove is provided on the side of the swirler seat facing the nozzle seat for fuel to flow from the oil inlet channel to the fuel swirl channel. The bushing comprises a bushing seat and a bushing rod. An oxygen swirl channel is formed between the inner wall of the bushing rod and the outer wall of the swirler rod. An oxygen groove is provided on the side of the bushing seat facing the swirler seat for oxygen to flow from the oxygen supply channel to the oxygen swirl channel. This arrangement allows oxygen and fuel to fully contact after being swirled and sprayed, making them more easily ignited by the ignition nozzle. Ignition can be successfully completed at high altitudes where the air is thin. The device has the advantages of short ignition and cross-flame time and low cost.

Description

Technical Field

[0001] The present application relates to the technical field of gas turbines, and in particular to an ignition and starting device and a gas turbine. Background Art

[0002] A gas turbine is an internal combustion power machine that uses a continuously flowing gas as a working fluid to drive a high-speed rotation of its impeller, converting the fuel's energy into useful work. It is a type of rotary impeller heat engine. Gas turbines are used in many applications, such as aviation weaponry. Modern advanced aviation weaponry often requires rapid start-up, requiring the weapon's power unit to rapidly accelerate to high thrust without a slow warm-up period. This requires the power unit to possess rapid start-up capabilities, starting and accelerating to full operation in a short period of time. With the advancement of modern information technology, aircraft are flying at ever-higher altitudes. However, the thin air and low oxygen content at high altitudes make it difficult for gas turbines to ignite. Furthermore, after ignition is generated in existing gas turbine ignition systems, the fire must propagate further until the entire flame tube is ignited, resulting in a relatively long cross-flame time. This difficulty in achieving ignition and the long cross-flame time at high altitudes contribute to the long ignition and starting time of the ignition and starting system.

[0003] Application Contents

[0004] Therefore, the technical problem to be solved by the present application is to overcome the defect of the relatively long ignition and starting time of the ignition and starting device in the prior art, thereby providing an ignition and starting device and a gas turbine equipped with the device.

[0005] To solve the above technical problems, the technical solution of the present application is as follows: an ignition starting device, comprising:

[0006] The nozzle body includes a nozzle seat and a hollow flame spray rod. The nozzle seat is provided with an oil inlet channel and an oxygen supply channel.

[0007] An ignition nozzle is mounted on the nozzle holder and one end of the ignition nozzle extends into the flame rod;

[0008] The swirler comprises a swirler seat connected to the nozzle seat and a swirler rod sleeved on the outer periphery of the flame rod; a fuel swirl channel for swirling fuel is formed between the inner wall of the swirl rod and the outer wall of the flame rod; an oil groove is provided on the side of the swirler seat facing the nozzle seat for fuel to flow from the oil inlet channel to the fuel swirl channel;

[0009] The bushing includes a bushing seat connected to the cyclone seat and a bushing rod sleeved on the outer circumference of the cyclone rod; an oxygen cyclone channel for oxygen cyclone ejection is formed between the inner wall of the bushing rod and the outer wall of the cyclone rod; an oxygen groove for oxygen to flow from the oxygen supplement channel to the oxygen cyclone channel is provided on the side of the bushing seat facing the cyclone seat.

[0010] Preferably, a first swirl groove is provided on the outer wall of the flame spray rod, and the inner wall of the swirl rod is fitted with the outer wall of the flame spray rod having the first swirl groove to form the fuel swirl channel.

[0011] Preferably, the wall thickness of the portion of the flame spray rod where the first swirl groove is provided is thicker than the wall thickness of the portion where the first swirl groove is not provided.

[0012] Preferably, a first annular channel is formed between the inner wall of the swirl rod and the outer wall of a portion of the flame spray rod where the first swirl groove is not provided, and the first annular channel communicates between the oil groove and the fuel swirl channel.

[0013] Preferably, a second swirl groove is provided on the outer wall of the swirl rod, and the inner wall of the bushing rod is fitted with the outer wall of the swirl rod having the second swirl groove to form the oxygen swirl channel.

[0014] Preferably, the wall thickness of the portion of the swirl rod where the second swirl groove is provided is thicker than the wall thickness of the portion where the second swirl groove is not provided.

[0015] Preferably, a second annular channel is formed between the inner wall of the bushing rod and the outer wall of a portion of the swirl rod where the second swirl groove is not provided, and the second annular channel is connected between the oxygen groove and the oxygen swirl channel.

[0016] Preferably, the nozzle seat is provided with a fuel throttling hole communicating with the oil inlet channel and the oil tank.

[0017] Preferably, the nozzle seat is provided with an oxygen throttling hole communicating with the oxygen supply channel and the oxygen tank.

[0018] Preferably, the cyclone seat is provided with an oxygen hole communicating with the oxygen tank and the oxygen throttling hole.

[0019] Preferably, a first sealing member for separating the fuel throttling hole and the oxygen throttling hole is sealed between the nozzle seat and the swirler seat.

[0020] Preferably, the position where the fuel throttle hole communicates with the swirler seat is closer to the center of the flame spray rod than the position where the oxygen throttle hole communicates with the swirler seat, and a second sealing member for isolating the oxygen throttle hole from external air is sealed between the nozzle seat and the swirler seat.

[0021] Preferably, a third sealing member is sealed between the cyclone seat and the bushing seat to separate the oxygen hole from external air.

[0022] Preferably, an air inlet hole for allowing external air to enter the oxygen swirl channel is provided on the outer wall of the bushing rod.

[0023] Preferably, at one end away from the bushing seat, the end of the bushing rod is extended by an end length relative to the ends of the swirl rod and the flame spray rod to form a steady flow cavity inside the extended portion.

[0024] A gas turbine is also provided, comprising the ignition and starting device described in any one of the above items.

[0025] The technical solution of this application has the following advantages:

[0026] 1. In the present invention, an oil inlet channel and an oxygen supply channel are provided on the nozzle body. Oxygen flows into the oxygen groove of the bushing seat through the oxygen supply channel on the nozzle body, and then passes through the oxygen swirl channel between the swirl rod and the bushing rod to rotate and accelerate before being diffused and sprayed outward. Fuel flows into the oil groove of the swirler seat through the oil inlet channel on the nozzle body, and then passes through the fuel swirl channel between the flame spray rod and the swirl rod to rotate and accelerate before being atomized and sprayed outward. The diffused oxygen can fully contact with the atomized fuel, and the mixed oil and gas are more easily ignited by the electric spark emitted by the ignition nozzle, thereby improving the ignition start-up rate and success rate, making it easier for the ignition starting device to successfully complete ignition at high altitudes where the air is thin, and having the advantages of short ignition and cross-flame time and low cost.

[0027] 2. The inner wall of the swirl rod fits with the first swirl groove of the flame spray rod to form a fuel swirl channel. The fuel swirl channel thus formed has a simple structure and a stable working state.

[0028] 3. A steady flow cavity is set up to prevent wind from blowing directly into the combustion chamber and affecting the combustion efficiency, thereby improving the working stability of the combustion chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the following is a brief introduction to the drawings required for use in the specific implementation methods or the description of the prior art. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0030] Figure 1 A longitudinal sectional view of an ignition starting device in an embodiment of the present application;

[0031] Figure 2 A top view of the nozzle body in an embodiment of the present application;

[0032] Figure 3 Schematic diagram of the overall structure of the nozzle body in the embodiment of the present application;

[0033] Figure 4 is a longitudinal sectional view of the nozzle body in the embodiment of the present application;

[0034] Figure 5 A front view of the nozzle body in an embodiment of the present application;

[0035] Figure 6 Schematic diagram of the overall structure of the cyclone in the embodiment of this application

[0036] Figure 7 is a longitudinal sectional view of a cyclone in an embodiment of the present application;

[0037] Figure 8 Schematic diagram of the overall structure of the bushing in the embodiment of this application

[0038] Figure 9 A longitudinal sectional view of a bushing in an embodiment of the present application;

[0039] Figure 10 Schematic diagram of the positional relationship between the flow stabilization cavity and the combustion chamber in an embodiment of the present application.

[0040] Explanation of reference numerals: 1, ignition nozzle; 2, nozzle body; 3, swirler; 4, bushing; 5, flow stabilization chamber; 6, flame tube; 2a, nozzle seat; 2b, nozzle mounting seat; 2c, oil inlet section; 2d, oxygen supply section; 2e, flame rod; 201, first mounting hole; 202, nozzle hole; 203, second mounting hole; 204, oil inlet channel; 205, fuel throttle hole; 206, oxygen supply channel; 207, oxygen throttle hole; 20 8. First sealing groove; 209. Second sealing groove; 210. First swirl groove; 3a. Swirl seat; 3b. Swirl rod; 301. Third mounting hole; 302. Fourth mounting hole; 303. Oxygen hole; 304. Second swirl groove; 305. Oil groove; 4a. Bushing seat; 4b. Bushing rod; 401. Fifth mounting hole; 402. Sixth mounting hole; 403. Third sealing groove; 404. Air inlet hole; 405. Oxygen groove. DETAILED DESCRIPTION

[0041] The following will clearly and completely describe the technical solution of this application in conjunction with the accompanying drawings. Obviously, the embodiments described are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making any creative efforts are within the scope of protection of this application.

[0042] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0043] Example 1

[0044] The ignition and starting device provided in this embodiment includes a nozzle body 2, an ignition nozzle 1, a swirler 3 and a bushing 4. The longitudinal section of the ignition and starting device is shown in FIG. Figure 1 shown.

[0045] The nozzle body 2 comprises a horizontally arranged nozzle holder 2a and a vertically arranged hollow flame rod 2e. An oil inlet section 2c is located at the left end of the nozzle holder 2a, and an oxygen supply section 2d is located at the right end. The oil inlet section 2c includes an oil inlet channel 204, while the oxygen supply section 2d includes an oxygen supply channel 206. The upper surface of the nozzle holder 2a is provided with a first mounting hole 201 and a second mounting hole 203. A nozzle hole 202 is located in the center of the upper surface of the nozzle holder 2a. The lower portion of the ignition nozzle 1 extends into the nozzle hole 202. A nozzle mounting seat 2b is provided on the upper surface of the nozzle holder 2a for securing the ignition nozzle 1. This nozzle mounting seat 2b has a through hole that connects to the second mounting hole 203 via a connector, thereby securing the ignition nozzle 1. The lower end of the ignition nozzle 1 serves as the ignition end.

[0046] The swirler 3 comprises a horizontally arranged swirler seat 3a and a vertically arranged swirler rod 3b. The swirler seat 3a is connected to the nozzle seat 2a, while the swirler rod 3b is mounted externally to the flame rod 2e. A fuel swirl channel, through which the fuel is swirl-ejected, is formed between the inner wall of the swirl rod 3b and the outer wall of the flame rod 2e. An oil groove 305 is provided on the side of the swirler seat 3a facing the nozzle seat 2a (i.e., on the upper end surface of the swirler seat 3a), allowing fuel to flow from the oil inlet channel 204 into the fuel swirl channel. A third mounting hole 301 is provided in the swirler seat 3a, and a fourth mounting hole 302 is provided in the swirler rod 3b.

[0047] The bushing 4 includes a horizontal bushing seat 4a and a vertical bushing rod 4b. The bushing seat 4a is connected to the cyclone seat 3a, and the bushing rod 4b is sleeved on the outside of the cyclone rod 3b. An oxygen swirl channel for ejecting oxygen swirl is formed between the inner wall of the bushing rod 4b and the outer wall of the cyclone rod 3b. An oxygen groove 405 is provided on the side of the bushing seat 4a facing the cyclone seat 3a (i.e., the upper end surface of the bushing seat 4a) for oxygen to flow from the oxygen supply channel 206 to the oxygen swirl channel. The bushing seat 4a is provided with a fifth mounting hole 401, and the bushing rod 4b is provided with a sixth mounting hole 402.

[0048] The first mounting hole 201, the third mounting hole 301, and the fifth mounting hole 401 are arranged opposite to each other, and a connecting member is passed through the first mounting hole 201, the third mounting hole 301, and the fifth mounting hole 401 to achieve fixation. The fourth mounting hole 302 and the sixth mounting hole 402 are arranged opposite to each other, and a connecting member is passed through the fourth mounting hole 302 and the sixth mounting hole 402 to achieve fixation.

[0049] The ignition and starting device provided in this embodiment operates as follows: Fuel enters the oil tank 305 through the oil inlet channel 204 and then enters the fuel swirl channel through the oil tank 305. The fuel is atomized within the fuel swirl channel, and the atomized fuel reacts more easily with oxygen, making ignition easier. Oxygen enters the oxygen tank 405 through the oxygen supply channel 206. After passing through the oxygen swirl channel, the oxygen diffuses, allowing the diffused oxygen to fully contact the fuel, making ignition easier. In this embodiment, by swirl-forming the fuel and oxygen separately, the fuel and oxygen are mixed more thoroughly, and the fuel and oxygen mixture is then ignited by the ignition nozzle 1. This improves the ignition rate and success rate, allowing the ignition and starting device to successfully ignite at high altitudes where the air is thin, while also shortening the ignition and starting time.

[0050] The nozzle body 2, swirler 3, and bushing 4 in this embodiment are all integrated, resulting in a simple structure, low production costs, and strong stability. The tight nesting of the ignition nozzle 1, swirler 3, nozzle body 2, and bushing 4 reduces displacement, collision, and wear during operation, thereby improving operational stability and service life.

[0051] like Figure 3 As shown, the lower outer wall of the flame rod 2e is provided with a spiral first swirl groove 210. The inner wall of the swirl rod 3b is aligned with the outer wall of the portion of the flame rod 2e containing the first swirl groove 210 to form a fuel swirl channel. The wall thickness of the portion of the flame rod 2e containing the first swirl groove 210 is greater than that of the portion not containing the first swirl groove 210. A first annular channel is formed between the inner wall of the swirl rod 3b and the outer wall of the portion of the flame rod 2e not containing the first swirl groove 210. The first annular channel connects the oil groove 305 and the fuel swirl channel. The nozzle holder 2a is provided with a fuel throttle hole 205 connecting the oil inlet channel 204 and the oil groove 305. Fuel passes through the oil inlet channel 204, the fuel throttle hole 205, the oil groove 305, the first annular channel, and the first swirl groove 210 in sequence before mixing with oxygen. This fuel channel configuration offers a simple structure, low production costs, and high operational stability. In an alternative embodiment, a spiral swirl groove may be provided on the inner wall of the swirl rod 3b, and the outer wall of the flame spray rod 2e is fitted with the inner wall of the swirl rod 3b to form a fuel swirl channel.

[0052] like Figure 6As shown, the lower outer wall of the swirl rod 3b is provided with a spiral second swirl groove 304. The inner wall of the bushing rod 4b abuts against the outer wall of the portion of the swirl rod 3b containing the second swirl groove 304 to form an oxygen swirl channel. The wall thickness of the portion of the swirl rod 3b containing the second swirl groove 304 is greater than the wall thickness of the portion not containing the second swirl groove 304. A second annular channel is formed between the inner wall of the bushing rod 4b and the outer wall of the portion of the swirl rod 3b not containing the second swirl groove 304. The second annular channel connects the oxygen groove 405 and the oxygen swirl channel. The nozzle holder 2a is provided with an oxygen throttling hole 207 connecting the oxygen supply channel 206 and the oxygen groove 405. The cyclone holder 3a is provided with an oxygen port 303 connecting the oxygen groove 405 and the oxygen throttling hole 207. Oxygen passes through the oxygen supply channel 206, oxygen throttle hole 207, oxygen hole 303, oxygen groove 405, second annular channel, and second swirl groove 304 before mixing with the fuel. This arrangement of the oxygen channel has a simple structure, low production cost, and strong operational stability. Furthermore, the fuel channel and oxygen channel are provided separately, so they do not flow into or affect each other, further improving operational stability. In an alternative embodiment, a spiral swirl groove can be provided on the inner wall of the bushing rod 4b, with the outer wall of the swirl rod 3b abutting against the inner wall of the bushing rod 4b to form the oxygen swirl channel.

[0053] A first seal is installed between the nozzle seat 2a and the swirler seat 3a to separate the fuel throttle hole 205 from the oxygen throttle hole 207. The first seal comprises an annular first sealing groove 208 and a sealing ring. The location where the fuel throttle hole 205 communicates with the swirler seat 3a is closer to the center of the flame rod 2e than the location where the oxygen throttle hole 207 communicates with the swirler seat 3a. A second seal is installed between the nozzle seat 2a and the swirler seat 3a to separate the oxygen throttle hole 207 from the outside air. The second seal comprises an annular second sealing groove 209 and a sealing ring. A third seal is installed between the swirler seat 3a and the bushing seat 4a to separate the oxygen hole 303 from the outside air. The third seal comprises an annular third sealing groove 403 and a sealing ring. The arrangement of the first, second, and first seals ensures that the fuel and oxygen channels remain airtight, preventing them from interflowing and preventing outside air from entering the fuel and oxygen channels and affecting fuel and oxygen intake. The provision of three seals helps to maintain the independence of each channel and improves the working stability of each channel.

[0054] An air inlet 404 is provided on the outer wall of the bushing rod 4b for allowing external air to enter the oxygen swirl channel. The air inlet 404 can also complete the air intake, which helps to increase the oxygen content in the ignition starting device and helps to improve the ignition rate and success rate.

[0055] At one end, away from the bushing seat 4a, the end of the bushing rod 4b extends a certain length relative to the ends of the swirl rod 3b and the flame rod 2e, forming a steady-flow chamber 5 within the extended portion. The fuel channel and the oxygen channel ultimately merge into the steady-flow chamber 5, and the ignition end of the ignition nozzle 1 communicates with the steady-flow chamber 5.

[0056] Example 2

[0057] This embodiment also provides a gas turbine, which includes a gas turbine body and an ignition and starting device as described in the above embodiment 1. The gas turbine body includes a combustion chamber, which includes a flame tube 6. The ignition and starting device has a flow stabilization chamber 5 inserted into the flame tube 6. After the fuel and oxygen are ignited in the flow stabilization chamber 5, the flame tube 6 is immediately ignited, thereby achieving rapid ignition and starting. In addition, at high altitudes, the wind is strong, and if the wind blows into the flame tube 6, it will affect the combustion stability in the flame tube 6. At this time, the flow stabilization chamber 5 acts to block the wind. When the wind passes through the flow stabilization chamber 5 and then enters the flame tube 6, the wind has been weakened by the flow stabilization chamber 5, thereby reducing the wind's impact on the stability of the combustion in the flame tube 6, thereby improving the working stability of the gas turbine at high altitudes.

[0058] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications arising therefrom remain within the scope of protection of this application.

Claims

1. An ignition starting device, characterized in that: include: The nozzle body (2) comprises a nozzle seat (2a) and a hollow flame spray rod (2e); the nozzle seat (2a) is provided with an oil inlet channel (204) and an oxygen supply channel (206); An ignition nozzle (1) is mounted on the nozzle seat (2a) and one end of the ignition nozzle extends into the flame spray rod (2e); The swirler (3) comprises a swirler seat (3a) connected to the nozzle seat (2a) and a swirler rod (3b) sleeved on the outer periphery of the flame spray rod (2e); a fuel swirl channel for swirl spraying of fuel is formed between the inner wall of the swirl rod (3b) and the outer wall of the flame spray rod (2e); an oil groove (305) for fuel to flow from the oil inlet channel (204) to the fuel swirl channel is provided on the side of the swirler seat (3a) facing the nozzle seat (2a); The bushing (4) comprises a bushing seat (4a) connected to the cyclone seat (3a) and a bushing rod (4b) sleeved on the outer periphery of the cyclone rod (3b); an oxygen cyclone channel for oxygen cyclone ejection is formed between the inner wall of the bushing rod (4b) and the outer wall of the cyclone rod (3b); an oxygen groove (405) for oxygen to flow from the oxygen supplement channel (206) to the oxygen cyclone channel is provided on the side of the bushing seat (4a) facing the cyclone seat (3a); A first swirl groove (210) is provided on the outer wall of the flame spray rod (2e), and the inner wall of the swirl rod (3b) is fitted with the outer wall of the flame spray rod (2e) having the first swirl groove (210) to form the fuel swirl channel; A first annular channel is formed between the inner wall of the swirl rod (3b) and the outer wall of the portion of the flame spray rod (2e) not provided with the first swirl groove (210), and the first annular channel communicates between the oil groove (305) and the fuel swirl channel.

2. The ignition starting device according to claim 1, characterized in that: The wall thickness of the portion of the flame spray rod (2e) provided with the first swirl groove (210) is greater than the wall thickness of the portion not provided with the first swirl groove (210).

3. The ignition starting device according to claim 1, characterized in that: A second swirl groove (304) is provided on the outer wall of the swirl rod (3b), and the inner wall of the bushing rod (4b) is fitted with the outer wall of the swirl rod (3b) having the second swirl groove (304) to form the oxygen swirl channel.

4. The ignition starting device according to claim 3, characterized in that: The tube wall thickness of the portion of the swirl rod (3b) provided with the second swirl groove (304) is greater than the tube wall thickness of the portion not provided with the second swirl groove (304).

5. The ignition starting device according to claim 4, characterized in that: A second annular channel is formed between the inner wall of the bushing rod (4b) and the outer wall of the portion of the swirl rod (3b) not provided with the second swirl groove (304), and the second annular channel is connected between the oxygen groove (405) and the oxygen swirl channel.

6. The ignition starting device according to claim 1, characterized in that: The nozzle seat (2a) is provided with a fuel throttling hole (205) communicating with the oil inlet channel (204) and the oil groove (305).

7. The ignition starting device according to claim 6, characterized in that: The nozzle seat (2a) is provided with an oxygen throttling hole (207) communicating with the oxygen supply channel (206) and the oxygen tank (405).

8. The ignition starting device according to claim 7, characterized in that: The cyclone seat (3a) is provided with an oxygen hole (303) communicating with the oxygen groove (405) and the oxygen throttling hole (207).

9. The ignition starting device according to claim 8, characterized in that: A first sealing member for separating the fuel throttling hole (205) and the oxygen throttling hole (207) is sealed between the nozzle seat (2a) and the swirler seat (3a).

10. The ignition starting device according to claim 9, characterized in that: The position where the fuel throttle hole (205) communicates with the swirler seat (3a) is closer to the center of the flame spray rod (2e) than the position where the oxygen throttle hole (207) communicates with the swirler seat (3a). A second sealing member for isolating the oxygen throttle hole (207) from external air is provided between the nozzle seat (2a) and the swirler seat (3a).

11. The ignition starting device according to claim 10, characterized in that: A third sealing member is provided between the cyclone seat (3a) and the bushing seat (4a) for isolating the oxygen hole (303) from external air.

12. The ignition starting device according to claim 11, characterized in that: An air inlet hole (404) for external air to enter the oxygen swirl channel is provided on the outer wall of the bushing rod (4b).

13. The ignition starting device according to claim 12, characterized in that: At one end away from the bushing seat (4a), the end of the bushing rod (4b) extends a certain length relative to the ends of the swirl rod (3b) and the flame-spraying rod (2e) to form a steady flow cavity (5) inside the extended portion.

14. A gas turbine, characterized in that: The invention comprises the ignition and starting device according to any one of claims 1 to 13.

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