Gas turbine combustion device and combustion method thereof

Abstract

The present invention discloses a gas turbine combustion device and a combustion method thereof, and relates to the technical field of gas turbines. It comprises an installation unit, including an installation shell, a flame tube arranged in the installation shell, an air intake cavity arranged in the installation shell, and an air intake support plate; a mixing unit, including a main fuel supply pipe arranged on the installation shell, a duty fuel supply pipe arranged on the installation shell, a mixing section arranged on the duty fuel supply pipe, and an injection section arranged on the main fuel supply cavity. The present invention achieves sufficient and uniform mixing of air and fuel by providing a mixing section and an injection section, and air enters the air intake cavity from the tail, is rectified by the air intake support plate, and then flows into the flame tube, is evenly mixed with the fuel in the mixing section and the injection section, and is ignited by the igniter, effectively avoiding the backfire phenomenon caused by uneven mixing of air and fuel.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine combustion device and a combustion method thereof. Background Art

[0002] Most of the heavy-duty gas turbines currently in service use natural gas as fuel, which releases a large amount of carbon dioxide during combustion, which is not conducive to carbon emission reduction. Therefore, researchers at home and abroad are trying to find a clean fuel to replace traditional hydrocarbon fuels. They have mastered the technology of natural gas blended hydrogen combustion and are committed to the development of all-hydrogen gas turbines.

[0003] As a clean and efficient energy source, hydrogen holds significant significance in energy technology reform and energy development strategies. In recent years, it has experienced rapid development due to its clean, environmentally friendly, and sustainable advantages. Hydrogen combustion produces only water as a combustion product, and using pure hydrogen as a gas turbine fuel can significantly reduce carbon emissions. However, hydrogen has a high combustion velocity and low ignition energy, making flashback common in traditional gas turbines. Furthermore, premixed hydrogen combustion increases pressure fluctuations, leading to unstable combustion.

[0004] Based on this, the present invention provides a gas turbine combustion device and a combustion method thereof, which can stably burn hydrogen and is also suitable for conventional gaseous fuels such as natural gas. Summary of the Invention

[0005] The present invention is proposed in view of the above-mentioned problems existing in the existing gas turbine combustion device and combustion method thereof.

[0006] Therefore, the object of the present invention is to provide a gas turbine combustion device, which aims to solve the technical problems of flashback and high nitrogen oxide emissions in conventional gas turbine combustion devices when using pure hydrogen as fuel.

[0007] In order to solve the above technical problems, the present invention provides the following technical solutions: comprising:

[0008] The mounting unit includes a mounting shell, a flame tube disposed in the mounting shell, an air intake cavity disposed between the mounting shell and the flame tube, and an air intake support plate disposed in the air intake cavity;

[0009] a mixing unit comprising a main fuel supply pipe provided on the mounting shell, a service fuel supply pipe provided on the mounting shell, a main fuel supply chamber provided on one end of the main fuel supply pipe close to the air inlet chamber, a mixing portion provided on a side of the service fuel supply pipe close to the flame tube, and an injection portion provided on the main fuel supply chamber;

[0010] Wherein, the end of the duty fuel supply pipe close to the flame tube is a closed end.

[0011] As a preferred embodiment of the gas turbine combustion device of the present invention, the mixing section includes a mixing assembly arranged on the side of the service fuel supply pipe close to the flame tube, and an air intake assembly arranged on the mixing assembly.

[0012] As a preferred embodiment of the gas turbine combustion device of the present invention, the mixing assembly includes a service fuel jet hole arranged on the side of the service fuel supply pipe close to the flame tube, and a swirler arranged in the gap between the service fuel jet holes.

[0013] As a preferred embodiment of the gas turbine combustion device of the present invention, the air intake assembly includes an air hood arranged on the side of the swirler away from the duty fuel supply pipe, and a funnel-shaped cover shell arranged on the end of the air hood away from the duty fuel supply pipe.

[0014] As a preferred solution of the gas turbine combustion device of the present invention, the injection portion includes an injection assembly arranged on the main fuel supply chamber, and a spray mixing assembly arranged on the injection assembly.

[0015] As a preferred embodiment of the gas turbine combustion device of the present invention, the injection assembly includes a main fuel delivery pipe provided on the main fuel supply cavity, a main fuel annular pipe provided on a side of the main fuel delivery pipe away from the main fuel supply cavity, and a main fuel jet column provided on the main fuel annular pipe;

[0016] The main fuel annular tube is coaxially arranged with the flame tube, and the diameter of each stage of the main fuel annular tube decreases in sequence along the axial direction of the flame tube.

[0017] As a preferred embodiment of the gas turbine combustion device of the present invention, the spray mixing assembly includes a main fuel micro-mixing column arranged on the main fuel annular tube and perpendicular to the main fuel jet column, and a main fuel micro-mixing hole arranged on the main fuel micro-mixing column.

[0018] Beneficial effects of the present invention:

[0019] By setting up the mixing section and the injection section, sufficient and uniform mixing of air and fuel is achieved. The air enters the intake cavity from the tail and is rectified by the intake support plate before flowing into the flame tube. After being evenly mixed with the fuel in the mixing section and the injection section, it is ignited by the igniter, effectively avoiding the backfire phenomenon caused by uneven mixing of air and fuel.

[0020] Another object of the present invention is to provide a combustion method for a gas turbine combustion device, which aims to solve the technical problem that the existing gas turbine combustion chamber is prone to backfire when burning hydrogen, which often leads to unstable flames.

[0021] In order to solve the above technical problems, the present invention provides the following technical solutions: comprising: air enters the air intake cavity from the rear of the mounting housing via the compressor, and flows back into the flame tube after passing through the air intake support plate;

[0022] The fuel passes through the service fuel supply pipe and the service fuel jet hole into the gap of the swirler, is mixed with the air entering the air hood, and then is transmitted to the flame tube, and is ignited by the igniter to form a service flame.

[0023] As a preferred embodiment of the combustion method of the gas turbine combustion device of the present invention, the fuel passes through the service fuel supply pipe and enters the gap of the swirler from the service fuel jet hole, mixes with the air therein, generates swirl under the action of the swirler, and forms a stable reflux zone.

[0024] As a preferred embodiment of the combustion method of the gas turbine combustion device of the present invention, when the air passes through each group of the main fuel annular pipes, vortices or turbulence with a small resistance coefficient are formed downstream thereof.

[0025] The beneficial effects of the present invention are as follows: by providing an air hood, a funnel-shaped cover, and a swirler, a mixture of fuel and air forms a stable recirculation zone downstream of the swirler, effectively ensuring the stability of the flame; at the same time, the mixture of fuel and air forms a vortex or turbulence with a small resistance coefficient downstream of each group of main fuel annular pipes, further improving the mixing degree of air and fuel, and providing a continuous supply of air and fuel mixture to the flame, thereby improving the stability of flame combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be derived from these drawings without inventive effort. Among them:

[0027] Figure 1 This is a schematic diagram of the internal structure of the gas turbine combustion device of the present invention.

[0028] Figure 2 for Figure 1 Enlarged schematic diagram of point A in the middle.

[0029] Figure 3 It is a schematic diagram of the internal cross-sectional structure of the gas turbine combustion device of the present invention.

[0030] Figure 4 It is a schematic diagram of the internal cross-sectional structure of the gas turbine combustion device of the present invention.

[0031] Figure 5 for Figure 4 Enlarged diagram of point B in the middle. DETAILED DESCRIPTION

[0032] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0033] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0034] Secondly, the term "one embodiment" or "embodiment" herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in various places throughout this specification does not necessarily refer to the same embodiment, nor does it constitute a separate or selective embodiment that is mutually exclusive with other embodiments.

[0035] Furthermore, the present invention is described in detail with reference to schematic diagrams. For ease of illustration, when describing the embodiments of the present invention, cross-sectional views illustrating device structures may be partially enlarged and not to scale. Furthermore, the schematic diagrams are merely illustrative and should not limit the scope of protection of the present invention. Furthermore, in actual production, the three-dimensional dimensions of length, width, and depth should be included.

[0036] Example 1

[0037] Reference Figure 1-3 , which is a first embodiment of the present invention, provides a gas turbine combustion device, which includes:

[0038] The mounting unit 100 includes a mounting housing 101, a flame tube 102 disposed in the mounting housing 101, an air intake cavity 103 disposed between the mounting housing 101 and the flame tube 102, and an air intake support plate 104 disposed in the air intake cavity. After air enters the air intake cavity, it is rectified by the air intake support plate 104, then moves to the top of the flame tube 102 and flows back into the flame tube 102, so that the air and fuel are fully mixed, thereby improving ignition efficiency.

[0039] The mixing unit 200 includes a main fuel supply pipe 201 provided on the mounting shell 101, a service fuel supply pipe 202 provided on the mounting shell 101, a main fuel supply chamber 203 provided at one end of the main fuel supply pipe 201 close to the air inlet chamber, a mixing section 204 provided on the service fuel supply pipe 202 close to the flame tube 102, and an injection section 205 provided on the main fuel supply chamber 203. Fuel enters the main fuel supply chamber 203 through the main fuel supply pipe 201 and is ejected through the injection section 205. The fuel ejected from the injection section 205 and the mixing section 204 is fully mixed with the air therein, significantly improving the mixing effect. The central axis of the main fuel jet column 205a-3 is parallel to the central axis of the flame tube 102, so that the fuel transmitted from the main fuel jet column 205a-3 is consistent with the overall velocity direction of the gas in the flame tube 102, effectively improving the overall flow velocity of the gas in the flame tube 102, thereby reducing the residence time of the gas, which is conducive to reducing the generation of pollutants and improving the environmental protection effect.

[0040] Among them, the end of the duty fuel supply pipe 202 close to the flame tube 102 is a closed end M, which avoids the fuel passing directly through the flame and causing flame instability, thereby improving the stability of flame combustion.

[0041] During use, air enters the device through the air intake cavity 103, and when passing through the air intake support plate 104, it passes through the small holes opened on the air intake support plate 104, which facilitates air circulation and stabilizes the air flow. It then moves to the top of the flame tube 102 and flows back into the flame tube 102, so that the air and fuel are fully mixed, thereby improving the ignition efficiency. At the same time, the fuel enters the main fuel supply cavity 203 through the main fuel supply pipe 201 and is ejected through the injection part 205. The fuel entering through the duty fuel supply pipe 202 passes through the mixing part 204 again, and is ejected from the injection part 205 and the mixing part 20 The ejected fuel is fully mixed with the air inside the flame tube 102, significantly improving the mixing effect. The central axis of the main fuel jet column 205a-3 is parallel to the central axis of the flame tube 102, so that the fuel transmitted by the main fuel jet column 205a-3 is consistent with the overall velocity direction of the gas in the flame tube 102, effectively improving the overall flow velocity of the gas in the flame tube 102, thereby reducing the residence time of the gas, which is beneficial to reducing the generation of pollutants and improving environmental protection effects. In addition, the short residence time of the gas effectively avoids the generation of thermal nitrogen oxides and can prevent backfire.

[0042] Example 2

[0043] Reference Figure 1-5, which is the second embodiment of the present invention. This embodiment is different from the first embodiment in that: the mixing section 204 includes a mixing assembly 204a arranged on the side of the service fuel supply pipe 202 close to the flame tube 102, and an air intake assembly 204b arranged on the mixing assembly 204a. The fuel reaches the air intake assembly 204b through the mixing assembly 204a and is fully mixed with the air there, which effectively improves the mixing efficiency of the fuel and air and improves the stability of the flame.

[0044] Compared with Example 1, the mixing assembly 204a further includes a service fuel jet hole 204a-1 arranged on the side of the service fuel supply pipe 202 close to the flame tube 102, and a swirler 204a-2 arranged in the gap of the service fuel jet hole 204a-1. The fuel enters through the service fuel supply pipe 202. Since the end of the service fuel supply pipe 202 close to the flame tube 102 is a closed end M, the fuel is then ejected through the service fuel jet hole 204a-1. At this time, the fuel and air form a stable recirculation zone under the action of the swirler 204a-2, so that more fuel and air enter the stable recirculation zone, thereby improving the mixing efficiency of the fuel and air.

[0045] Compared with Example 1, the air intake assembly 204b further includes an air hood 204b-1 arranged on the side of the swirler 204a-2 away from the service fuel supply pipe 202, and a funnel-shaped cover 204b-2 arranged at the end of the air hood 204b-1 away from the service fuel supply pipe 202. The air flows back through the top of the flame tube 102 into the air hood 204b-1, and then enters the funnel-shaped cover 204b-2. Due to the increase in the cross-section of the fluid, a stable reflux zone is generated under the action of the swirler 204a-2 at the same time as the fuel ejected through the service fuel jet hole 204a-1.

[0046] Compared with Example 1, the injection part 205 further includes an injection component 205a arranged on the main fuel supply chamber 203, and a spray mixing component 205b arranged on the injection component 205a. The fuel enters the injection component 205a through the main fuel supply chamber 203, and then enters the spray mixing component 205b for spraying, thereby increasing the degree of mixing with the air with the help of the fuel injection momentum.

[0047] Compared to Example 1, the injection assembly 205a further includes a main fuel delivery pipe 205a-1 disposed on the main fuel supply chamber 203, a main fuel annular pipe 205a-2 disposed on the side of the main fuel delivery pipe 205a-1 away from the main fuel supply chamber 203, and a main fuel jet column 205a-3 disposed on the main fuel annular pipe 205a-2. The fuel in the main fuel supply chamber 203 enters the main fuel annular pipe 205a-2 through the main fuel delivery pipe 205a-1 and is ejected through the main fuel jet column 205a-3.

[0048] The main fuel annular tube 205a-2 is coaxially arranged with the flame tube 102, and the diameter of each stage of the main fuel annular tube 205a-2 decreases successively along the axial direction of the flame tube 102. When the air flows into the main fuel annular tube 205a-2, due to the fast air flow speed and low dynamic viscosity, and the main fuel annular tube 205a-2 is provided with multiple groups, when the air passes through each group of main fuel annular tubes 205a-2, vortices will periodically fall off on the upper and lower sides thereof, forming a regularly arranged vortex array, so that vortices or turbulence with a small resistance coefficient are formed downstream of each group of main fuel annular tubes 205a-2, so that the fuel and air can be mixed quickly and efficiently with the help of high turbulence, further improving the mixing degree of fuel and air.

[0049] Compared with Example 1, the spray mixing assembly 205b further includes a main fuel micro-mixing column 205b-1 arranged on the main fuel annular tube 205a-2 and perpendicular to the main fuel jet column 205a-3, and a main fuel micro-mixing hole 205b-2 arranged on the main fuel micro-mixing column 205b-1. The fuel is sprayed through the main fuel jet column 205a-3 and the main fuel micro-mixing hole 205b-2 on the main fuel micro-mixing column 205b-1 respectively. At this time, due to the small size of the main fuel micro-mixing hole 205b-2, the sprayed fuel can form a micro-premix with the air, effectively preventing backfire. At the same time, its combustion temperature is lower than the diffusion combustion temperature, which significantly reduces the generation of thermal nitrogen oxides. It is particularly suitable for hydrogen combustion. When the fuel is hydrogen, it can significantly reduce carbon emissions and improve environmental protection effects.

[0050] The remaining structures are the same as those of Example 1.

[0051] Example 3

[0052] Reference Figure 1-5 , which is the third embodiment of the present invention, is based on Embodiments 1 and 2 and provides a combustion method for a gas turbine combustion device, comprising:

[0053] Air enters the air intake cavity 103 from the rear of the mounting housing 101 through the compressor, and then flows back into the flame tube 102 after passing through the air intake support plate 104, so that the air and fuel are fully mixed, thereby improving the ignition efficiency;

[0054] The fuel passes through the service fuel supply pipe 202 and enters the gap of the swirler 204a-2 from the service fuel jet hole 204a-1, mixes with the air entering the air cover 204b-1, and then is transmitted to the flame tube 102, where it is ignited by the igniter to form the service flame. At this time, the air and the fuel ejected through the service fuel jet hole 204a-1 simultaneously generate a stable reflux zone under the action of the swirler 204a-2.

[0055] Compared with Example 2, further, the fuel passes through the duty fuel supply pipe 202 and enters the gap of the swirler 204a-2 from the duty fuel injection hole 204a-1, mixes with the air here and generates a vortex under the action of the swirler 204a-2, forming a stable reflux zone, thereby improving the mixing efficiency of the fuel and air.

[0056] Compared to Example 2, further, when the air passes through each set of primary fuel annular tubes 205a-2, a vortex or turbulent flow with a small drag coefficient is formed downstream thereof. Since the air flows at a high speed and has a low dynamic viscosity, its Reynolds number (Re=ρuL / μ) is generally greater than 40.

[0057] Where, ρ is the fluid density, u is the fluid velocity, L is the characteristic length, and μ is the dynamic viscosity of the fluid. The flow field downstream of the main fuel annulus 205a-2 is no longer steady, but vortices are periodically shed on both sides of the annulus, forming a regularly arranged vortex array, namely, the Karman vortex street. When Re is greater than 300, the "vortex street" behind the cylinder gradually loses its regularity and periodicity. When Re is greater than 200,000 to 400,000, the laminar boundary layer upstream of the annulus may be converted into turbulent flow at any time. In turbulent flow, the width of the flow wake is reduced, and the drag coefficient is The sudden decrease causes the air to flow through each group of main fuel annular tubes 205a-2 at intervals, forming vortices or turbulence with a small resistance coefficient downstream of each group of main fuel annular tubes 205a-2. Due to the air flow in the flame tube 102, the vortex shedding, turbulent disturbance and the irregular movement brought about thereby are utilized to enable the fuel in the main fuel micro-mixing column 205b-1 and the main fuel jet column 205a-3 to be mixed with the surrounding air quickly and efficiently with the help of high turbulence after flowing out, and after being mixed evenly, be ignited and burned by the on-duty flame, thereby improving the stability of the flame.

[0058] The remaining structures are the same as those of Example 2.

[0059] It is important to note that the construction and arrangement of the present application shown in a number of different exemplary embodiments are merely illustrative. Although only a few embodiments are described in detail in this disclosure, it should be readily understood by those who refer to this disclosure that many modifications are possible (e.g., the size, scale, structure, shape, and proportion of various elements, as well as parameter values ​​(e.g., temperature, pressure, etc.), mounting arrangements, use of materials, color, changes in orientation, etc.) without departing substantially from the novel teachings and advantages of the subject matter described in this application. For example, an element shown as integrally formed may be composed of multiple parts or elements, the position of the element may be inverted or otherwise changed, and the nature, number, or position of the discrete elements may be altered or changed. Therefore, all such modifications are intended to be included within the scope of the present invention. The order or sequence of any process or method steps may be changed or reordered according to alternative embodiments. In the claims, any "means plus function" clause is intended to cover the structure described herein that performs the function, and is not only structurally equivalent but also equivalent structures. Other replacements, improvements, changes, and omissions may be made in the design, operating conditions, and arrangement of the exemplary embodiments without departing from the scope of the present invention. Therefore, the invention is not limited to the specific embodiments, but extends to various modifications that still fall within the scope of the appended claims.

[0060] Additionally, in order to provide a concise description of exemplary embodiments, all features of an actual embodiment (i.e., those features that are not relevant to the best mode presently contemplated for carrying out the invention or those that are not relevant to implementing the invention) may not be described.

[0061] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should all be included in the scope of the claims of the present invention.

Claims

1. A gas turbine combustion device, characterized in that: include, The mounting unit (100) comprises a mounting shell (101), a flame tube (102) disposed in the mounting shell (101), an air intake cavity (103) disposed between the mounting shell (101) and the flame tube (102), and an air intake support plate (104) disposed in the air intake cavity; A mixing unit (200) comprising a main fuel supply pipe (201) provided on the mounting shell (101), a duty fuel supply pipe (202) provided on the mounting shell (101), a main fuel supply chamber (203) provided on one end of the main fuel supply pipe (201) close to the air inlet chamber, a mixing portion (204) provided on a side of the duty fuel supply pipe (202) close to the flame tube (102), and an injection portion (205) provided on the main fuel supply chamber (203); Wherein, one end of the duty fuel supply pipe (202) close to the flame tube (102) is a closed end (M); The mixing section (204) comprises a mixing assembly (204a) provided on a side of the service fuel supply pipe (202) close to the flame tube (102), and an air intake assembly (204b) provided on the mixing assembly (204a); The mixing assembly (204a) comprises a service fuel jet hole (204a-1) provided on a side of the service fuel supply pipe (202) close to the flame tube (102), and a swirler (204a-2) provided in a gap between the service fuel jet hole (204a-1); The air intake assembly (204b) comprises an air hood (204b-1) arranged on a side of the swirler (204a-2) away from the duty fuel supply pipe (202), and a funnel-shaped cover shell (204b-2) arranged on an end of the air hood (204b-1) away from the duty fuel supply pipe (202); The injection portion (205) comprises an injection assembly (205a) arranged on the main fuel supply chamber (203), and a spray mixing assembly (205b) arranged on the injection assembly (205a); The injection assembly (205a) comprises a main fuel delivery pipe (205a-1) arranged on the main fuel supply cavity (203), a main fuel annular pipe (205a-2) arranged on a side of the main fuel delivery pipe (205a-1) away from the main fuel supply cavity (203), and a main fuel jet column (205a-3) arranged on the main fuel annular pipe (205a-2); The main fuel annular tube (205a-2) is coaxially arranged with the flame tube (102), and the diameter of each stage of the main fuel annular tube (205a-2) decreases in sequence along the axial direction of the flame tube (102) and in the opposite direction of the main fuel delivery direction.

2. The gas turbine combustion device according to claim 1, characterized in that: The spray mixing assembly (205b) comprises a main fuel micro-mixing column (205b-1) arranged on the main fuel annular tube (205a-2) and perpendicular to the main fuel jet column (205a-3), and a main fuel micro-mixing hole (205b-2) arranged on the main fuel micro-mixing column (205b-1).

3. A combustion method for a gas turbine combustion device, comprising the gas turbine combustion device according to claim 2, the method comprising: Air enters the air intake cavity (103) from the rear of the mounting housing (101) via the compressor, passes through the air intake support plate (104), and then flows into the flame tube (102); The fuel passes through the duty fuel supply pipe (202) and enters the gap of the swirler (204a-2) from the duty fuel jet hole (204a-1), mixes with the air entering the air hood (204b-1), and then passes out to the flame tube (102), where it is ignited by the igniter to form a duty flame.

4. The combustion method of a gas turbine combustion device according to claim 3, characterized in that: The fuel passes through the duty fuel supply pipe (202) and the duty fuel jet hole (204a-1) into the gap of the swirler (204a-2), and is mixed with the air therein, generating a swirl under the action of the swirler (204a-2), thereby forming a stable reflux zone.

5. The combustion method of a gas turbine combustion device according to claim 4, characterized in that: When the air passes through each group of the main fuel ring tubes (205a-2), a vortex or turbulence with a small resistance coefficient is formed downstream thereof.

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