Combined nozzle combustion chamber

Abstract

The present disclosure provides a combined nozzle combustion chamber, which includes a flame tube body, wherein the flame tube body encloses a combustion zone, and the air inlet end of the flame tube body is provided with: a central diffusion combustion nozzle for realizing diffusion combustion of fuel and air in the combustion zone; a plurality of unit micro-mixing combustion nozzles for realizing micro-mixing premixing combustion of fuel and air in the combustion zone; and a plurality of lean direct injection combustion nozzles for realizing lean direct injection combustion of fuel and air in the combustion zone. The combined nozzle combustion chamber can realize uniform mixing of fuel and air at a micro scale, reduce the peak temperature of the flame during combustion, and meet the low emission requirements.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas turbine combustion, and in particular relates to a combined nozzle combustion chamber. Background Art

[0002] Aero-derivative gas turbines are widely used in distributed power generation, ship propulsion, gas compression, and offshore platform power generation. In the design of gas turbines, the emission of nitrogen oxides needs to be considered.

[0003] In the related art, in order to reduce the emission of nitrogen oxides, lean premixed combustion is often used to control the flame temperature. However, when the hydrogen content in the fuel increases, thermoacoustic oscillation and flashback are prone to occur. Therefore, in the design of gas turbines, it is urgent to solve the problem of thermoacoustic oscillation and flashback on the basis of meeting the nitrogen oxide emission. Summary of the invention

[0004] In view of this, the present disclosure provides a combined nozzle combustion chamber to at least partially solve the above technical problems.

[0005] One aspect of the present disclosure provides a combined nozzle combustion chamber, comprising a flame tube body, wherein the flame tube body encloses a combustion zone, and an air inlet end of the flame tube body is provided with:

[0006] Central diffusion combustion nozzle, used to achieve diffusion combustion of fuel and air in the combustion zone;

[0007] Multiple unit micro-mixing combustion nozzles are used to achieve micro-mixing premixed combustion of fuel and air in the combustion zone;

[0008] A plurality of lean direct injection combustion nozzles are used to realize lean direct injection combustion of fuel and air in a combustion zone.

[0009] According to an embodiment of the present disclosure, wherein:

[0010] The central diffusion combustion nozzle is arranged at the center of the flame tube body;

[0011] The multiple unit micro-mixing combustion nozzles are divided into at least one annular micro-mixing combustion combination, and in each annular micro-mixing combustion combination, the multiple unit micro-mixing combustion nozzles are distributed and arranged along the circumference of the flame tube body;

[0012] The multiple lean direct injection combustion nozzles are divided into at least one annular lean direct injection combustion combination, and in each annular lean direct injection combustion combination, the multiple lean direct injection combustion nozzles are distributed and arranged along the circumference of the flame tube body;

[0013] The annular micro-mixed combustion combination and the annular lean direct injection combustion combination are alternately distributed along the radial direction of the flame tube.

[0014] According to an embodiment of the present disclosure, the above-mentioned combined nozzle combustion chamber further includes:

[0015] a central diffusion flame fuel cavity, wherein the central diffusion flame fuel cavity is in communication with a fuel inlet of a central diffusion combustion nozzle;

[0016] At least one annular micro-mixed combustion flame fuel cavity, wherein at least one micro-mixed combustion flame fuel cavity is matched with at least one annular micro-mixed combustion combination, and the micro-mixed combustion flame fuel cavity is connected to the fuel inlet of the unit micro-mixed combustion nozzle;

[0017] At least one annular lean direct injection combustion flame fuel cavity, wherein at least one lean direct injection combustion flame fuel cavity is matched with at least one annular lean direct injection combustion combination one by one, and the lean direct injection combustion flame fuel cavity is connected to the fuel inlet of the lean direct injection combustion nozzle;

[0018] Each central diffusion flame fuel cavity, each micro-mixed combustion flame fuel cavity, and each lean direct injection combustion flame fuel cavity are respectively connected to an independent fuel intake nozzle.

[0019] According to an embodiment of the present disclosure, the above-mentioned combined nozzle combustion chamber further includes:

[0020] The nozzle head end cover is fixedly installed at the air inlet end of the flame tube body and is used to support the fixed central diffusion combustion nozzle, multiple unit micro-mixing combustion nozzles, and multiple lean direct injection combustion nozzles;

[0021] The casing is arranged outside the flame tube body, and an annular cavity is formed between the inner wall of the casing and the outer wall of the flame tube body. The annular cavity is provided with an air inlet, which is connected to the outside and is used to introduce air into the annular cavity;

[0022] The casing end cover is arranged at the front end of the casing, and is used to support and fix the casing, and is used to support and fix the central diffusion flame fuel cavity, the micro-mixed combustion flame fuel cavity, and the lean direct injection combustion flame fuel cavity;

[0023] The support tube has two ends connected to the casing end cover and the flame tube body respectively, and a nozzle air inlet area is formed inside the support tube, wherein an air introduction hole is provided in the wall of the support tube, and the annular cavity is connected to the nozzle air inlet area through the air introduction hole;

[0024] Among them, the air inlets of the central diffusion combustion nozzle, the unit micro-mixing combustion nozzle and the lean direct injection combustion nozzle are located in the nozzle intake area.

[0025] According to an embodiment of the present disclosure, a unit micro-mixing combustion nozzle comprises a nozzle housing, wherein the nozzle housing is provided with:

[0026] a fuel intake chamber configured to admit fuel;

[0027] A premixing chamber, wherein an air inlet hole is provided in the cavity wall of the premixing chamber, the air inlet hole is configured to allow air to enter, and the outlet end of the premixing chamber is connected to the combustion zone, wherein the premixing chamber and the fuel inlet cavity are connected via a fuel injection hole, and the premixing chamber is used to: mix the air entering through the air inlet hole and the fuel from the fuel inlet cavity to form a premixed gas, and then inject the premixed gas into the combustion zone, so as to realize micro-mixed premixed combustion of the fuel and air in the combustion zone;

[0028] Wherein, a nozzle cooling air film hole is provided in the cavity wall near the outlet end of the premixing chamber;

[0029] The air inlet holes include a primary air inlet hole and a secondary air inlet hole, and the primary air inlet hole and the secondary air inlet hole are arranged along the gas flow direction in the premixing chamber.

[0030] According to an embodiment of the present disclosure, wherein:

[0031] The nozzle housing adopts a circular tubular structure;

[0032] The fuel intake cavity includes a closed-end cylindrical intake pipe, which is coaxially arranged with the nozzle housing so that an annular premixing chamber is formed between the outer surface of the intake pipe and the inner surface of the nozzle housing;

[0033] The front end of the intake pipe is provided with a fuel injection hole, and the end of the intake pipe is provided with a concave center body.

[0034] According to an embodiment of the present disclosure, the central diffusion combustion nozzle comprises:

[0035] A sleeve, the sleeve is provided with an air inlet and a diffusion gas outlet, the air inlet is configured to admit air, and the diffusion gas outlet is communicated with the combustion zone;

[0036] A fuel nozzle, wherein the inlet end of the fuel nozzle is configured to allow fuel to flow in, the outlet end of the fuel nozzle is provided with a fuel injection hole, and the fuel nozzle and the sleeve are connected through the fuel injection hole;

[0037] A venturi tube, the venturi tube is arranged in the sleeve, and the fuel nozzle and the venturi tube are connected through the fuel injection hole;

[0038] The swirl cup is arranged at the air inlet of the sleeve so that a swirl is formed in the sleeve after the air enters;

[0039] Among them, the central diffusion combustion nozzle is used to: after the air entering through the air inlet and the fuel sprayed through the fuel nozzle are diffused by the sleeve, they are sprayed into the combustion zone through the diffusion gas outlet of the sleeve to realize the diffusion combustion of the fuel and air in the combustion zone.

[0040] According to an embodiment of the present disclosure, the lean direct injection combustion nozzle is provided with:

[0041] a central fuel delivery passage, wherein an inlet end of the central fuel delivery passage is configured to admit fuel;

[0042] Multiple air delivery channels are distributed circumferentially around a central fuel delivery channel, an inlet end of the air delivery channel is configured to allow air to pass through, an outlet end of the air delivery channel is connected to a combustion zone, each air delivery channel is separately connected to a central fuel delivery channel, so that the fuel in the central fuel delivery channel can be dispersedly passed into multiple air delivery channels, and the air delivery channels and the central fuel delivery channel are connected at an outlet position close to a lean direct injection combustion nozzle, and the air delivery channels are used to premix the air introduced from the outside and the fuel from the central fuel delivery channel and then inject them into the combustion zone, so as to realize lean direct injection combustion of the fuel and air in the combustion zone.

[0043] According to an embodiment of the present disclosure, the lean direct injection combustion nozzle comprises:

[0044] A central fuel delivery pipe, wherein a central fuel delivery channel is formed in the central fuel delivery pipe, an inlet end of the central fuel delivery pipe is configured to allow fuel to flow in, and an outlet end of the central fuel delivery pipe is provided with a plurality of fuel ejection holes;

[0045] A plurality of air delivery pipes, the plurality of air delivery pipes are circumferentially distributed around the central fuel delivery pipe, an air delivery channel is formed in the air delivery pipe, the air delivery pipe includes a slope inlet end and a direct injection outlet, the slope inlet end is configured to allow air to pass through, the direct injection outlet is connected to the combustion zone, and a fuel injection hole is provided near the direct injection outlet, the plurality of air delivery pipes and the plurality of fuel injection holes are matched one by one, so that the fuel in the central fuel delivery pipe can be dispersedly passed into the plurality of air delivery pipes through the plurality of fuel injection holes, and the air delivery pipe is used to perform lean premixing of the air entering through the slope inlet end and the fuel entering through the fuel injection hole, and then inject the mixture into the combustion zone through the direct injection outlet;

[0046] Wherein, the plurality of air delivery pipes distributed circumferentially around the central fuel delivery pipe are straight pipes, the central axis of the air delivery pipe is parallel to the central axis of the central fuel delivery pipe, and the cross section of the straight pipe is circular or petal-shaped; or

[0047] The plurality of air delivery pipes distributed circumferentially around the central fuel delivery pipe are spiral pipes, and the cross section of the spiral pipes is circular or petal-shaped.

[0048] According to an embodiment of the present disclosure, the lean direct injection combustion nozzle comprises:

[0049] A central fuel delivery pipe, wherein a central fuel delivery channel is formed in the central fuel delivery pipe, the central fuel delivery pipe comprises a straight pipe section, a transition section and a forming section which are connected in sequence front and back, the inlet end of the straight pipe section is configured to allow fuel to pass through, the cross section of the forming section is a petal-shaped structure, and the outlet end of the forming section is provided with a plurality of fuel ejection holes;

[0050] The end tube shell is arranged around the outside of the forming section so that a plurality of fan-shaped air delivery channels are formed between the inner wall of the end tube shell and the outer wall of the forming section, and each fan-shaped air delivery channel corresponds to at least one fuel ejection hole, so that the fuel in the central fuel delivery pipe can be dispersed into the plurality of fan-shaped air delivery channels through the plurality of fuel ejection holes. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Figure 1 is a schematic diagram of the distribution structure of various types of nozzles in a combined nozzle combustion chamber according to an embodiment of the present disclosure;

[0052] Figure 2 It is a schematic diagram of the distribution structure of various types of nozzles in the flame tube body in the combined nozzle combustion chamber according to an embodiment of the present disclosure;

[0053] Figure 3 is a schematic diagram of the communication structure between various types of nozzles and various types of fuel chambers in a combined nozzle combustion chamber according to an embodiment of the present disclosure;

[0054] Figure 4 is a cross-sectional view of the internal structure of a combined nozzle combustion chamber according to an embodiment of the present disclosure;

[0055] Figure 5A is a schematic structural diagram of a unit micro-mixing combustion nozzle according to an embodiment of the present disclosure;

[0056] Figure 5B is a structural schematic diagram of a unit micro-mixing combustion nozzle according to another embodiment of the present disclosure;

[0057] Figure 6 is a schematic structural diagram of a central diffusion combustion nozzle according to an embodiment of the present disclosure;

[0058] Fig. 7A is a schematic diagram of the external structure of a lean direct injection combustion nozzle according to an embodiment of the present disclosure;

[0059] Figure 7B yes Fig. 7A The schematic diagram of the internal structure of the lean direct injection combustion nozzle is shown;

[0060] Figure 7C is a structural schematic diagram of a lean direct injection combustion nozzle according to another embodiment of the present disclosure;

[0061] Fig.7D yes Figure 7CThe schematic diagram of the internal structure of the lean direct injection combustion nozzle is shown;

[0062] Fig. 7E is a structural schematic diagram of a lean direct injection combustion nozzle according to another embodiment of the present disclosure;

[0063] Figure 7F yes Fig. 7E The schematic diagram of the end structure of the lean direct injection combustion nozzle shown;

[0064] Figure 7G is a structural schematic diagram of a lean direct injection combustion nozzle according to another embodiment of the present disclosure;

[0065] Figure 7H yes Figure 7G The internal structure schematic diagram of the lean direct injection combustion nozzle is shown;

[0066] Figure 8 is a system schematic diagram of a gas turbine power generation system according to an embodiment of the present invention.

[0067] Description of reference numerals:

[0068] 1. Central diffusion combustion nozzle;

[0069] 2. Unit micro-mixing combustion nozzle;

[0070] 3. Lean direct injection combustion nozzle;

[0071] 6. Combined nozzle combustion chamber;

[0072] 11. Sleeve;

[0073] 12. Swirl cup;

[0074] 13. Fuel nozzle;

[0075] 14. Venturi tube;

[0076] 15. Fuel injection hole;

[0077] 21. Nozzle housing;

[0078] 22. Fuel intake chamber;

[0079] 23. Fuel injection hole;

[0080] 24. Primary air inlet;

[0081] 25. Secondary air intake hole;

[0082] 26. Premixing chamber;

[0083] 27. Nozzle cooling air film hole;

[0084] 28. Concave centrosome;

[0085] 31. Central fuel delivery channel;

[0086] 32. Air delivery channel;

[0087] 33. Slope entrance end;

[0088] 34. End cap;

[0089] 35. Fuel ejection hole;

[0090] 36. Terminal tube shell;

[0091] 37. Straight pipe section;

[0092] 38. Transition section;

[0093] 39. Forming segments;

[0094] 41. Fuel chamber bottom plate;

[0095] 42. Fuel chamber top plate;

[0096] 43. Fuel chamber annular baffle;

[0097] 44. Nozzle head end cap;

[0098] 45. Central fuel intake nozzle,

[0099] 46. ​​Mild-mix fuel intake nozzle;

[0100] 47. Central diffusion flame fuel chamber;

[0101] 48. Inner micro-mixed combustion flame fuel chamber;

[0102] 49. Lean direct injection combustion flame fuel chamber;

[0103] 50. Outer micro-mixed combustion flame fuel chamber;

[0104] 51. Lean direct injection fuel intake nozzle

[0105] 61. Receiver;

[0106] 62. Flame tube body;

[0107] 63. Receiver front flange;

[0108] 64. Receiver end cover;

[0109] 65. Bolt mounting hole;

[0110] 66. Support tube;

[0111] 67. Exhaust end of flame tube;

[0112] 68. Air inlet hole;

[0113] 69. Light the fire and light the mouth;

[0114] 321, direct injection outlet;

[0115] 601, annular cavity;

[0116] 602, nozzle air inlet area;

[0117] 71. Compressor;

[0118] 72. Turbine;

[0119] 73. Generator;

[0120] 74. Start the motor;

[0121] f1. fuel;

[0122] f2, acceleration fuel;

[0123] p1, premixed gas;

[0124] A. High pressure air;

[0125] E. Exhaust gas;

[0126] G. High temperature gas. DETAILED DESCRIPTION

[0127] In order to make the objectives, technical solutions and advantages of the present disclosure more clearly understood, the present disclosure is further described in detail below in combination with specific embodiments and with reference to the accompanying drawings.

[0128] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the present disclosure. In the following detailed description, for ease of explanation, many specific details are set forth to provide a comprehensive understanding of the embodiments of the present disclosure. However, it is apparent that one or more embodiments may also be implemented without these specific details. In addition, in the following description, descriptions of known structures and technologies are omitted to avoid unnecessary confusion of the concepts of the present disclosure.

[0129] The terms used herein are only for describing specific embodiments and are not intended to limit the present disclosure. The terms "comprise", "include", etc. used herein indicate the existence of the features, steps, operations and / or components, but do not exclude the existence or addition of one or more other features, steps, operations or components.

[0130] All terms (including technical and scientific terms) used herein have the meanings commonly understood by those skilled in the art, unless otherwise defined. It should be noted that the terms used herein should be interpreted as having a meaning consistent with the context of this specification, and should not be interpreted in an idealized or overly rigid manner.

[0131] In the case of using expressions such as "at least one of A, B, and C, etc.", it should generally be interpreted in accordance with the meaning of the expression generally understood by those skilled in the art (for example, "a system having at least one of A, B, and C" should include but is not limited to a system having A alone, B alone, C alone, A and B, A and C, B and C, and / or A, B, C, etc.). In the case of using expressions such as "at least one of A, B, or C, etc.", it should generally be interpreted in accordance with the meaning of the expression generally understood by those skilled in the art (for example, "a system having at least one of A, B, or C" should include but is not limited to a system having A alone, B alone, C alone, A and B, A and C, B and C, and / or A, B, C, etc.).

[0132] Traditional gas turbines mostly use natural gas as the main fuel component, but natural gas combustion inevitably produces a large amount of carbon dioxide emissions, so there is an urgent need to find a carbon-free fuel to replace natural gas. Hydrogen is a carbon-free fuel with a high calorific value and has great potential as the main fuel for gas turbines in the new era. Combining hydrogen energy with gas turbine technology and replacing natural gas as fuel with clean hydrogen-rich / hydrogen fuel can significantly reduce carbon emissions from gas turbines. When hydrogen accounts for 80%, carbon emissions can be reduced by about 50%.

[0133] However, hydrogen has a higher chemical reactivity. Traditional gas turbine combustion chambers that directly burn hydrogen fuel are more prone to flashback problems than natural gas, affecting the heat-affected zone at the head of the combustion chamber and causing the service life of the combustion chamber to decrease. At the same time, the higher flame adiabatic temperature can easily cause high temperatures in local areas, increasing nitrogen oxide emissions. This is also a major difference between hydrogen gas turbines and traditional gas turbines.

[0134] In the related technology, gas turbines running on natural gas usually adopt a swirl premixing structure to reduce nitrogen oxide emissions. The swirl generates strong turbulent shearing action to promote the full mixing of fuel and air in the premixing section, and then send them into the combustion chamber to achieve spatial homogeneous combustion, thereby suppressing nitrogen oxide emissions. However, when the hydrogen content in the fuel increases, due to the extremely high flame propagation speed of hydrogen, the hydrogen flame may propagate upstream and stabilize inside the nozzle, causing flashback and hanging fire, affecting the safe operation of the burner; therefore, the traditional large-scale swirl premixing nozzle is no longer applicable to hydrogen fuel. Therefore, a micro-mixing combustion nozzle technology is proposed, which transforms a large-sized swirl premixing nozzle into several tiny-sized micro-mixing combustion units. On the one hand, the outlet air jet velocity increases after the unit nozzle size is reduced, which effectively reduces the risk of flashback during the combustion of hydrogen and hydrogen-rich fuels. On the other hand, the fuel participating in the combustion is dispersed and transported to a large number of micro-mixing combustion units, which can achieve uniform mixing of fuel and air at a micro scale and reduce the peak flame temperature during combustion. In addition, multiple micro-premixing nozzles simultaneously generate small flames, which can also achieve uniform temperature distribution in the flame tube, shorten the length of the high-temperature zone, and meet low emission requirements.

[0135] However, the hydrogen-fueled gas turbine combustion chambers in the related art mostly adopt a single micro-mixing nozzle structure, which exposes the following problems during use: with the further increase of the hydrogen content in the fuel (hydrogen volume fraction greater than 80%), or even when burning hydrogen-rich fuel, this micro-mixing nozzle produces complex flame interference and serious thermoacoustic oscillation problems. This low-frequency and large-amplitude pressure oscillation can seriously damage the burner and flame tube mechanical structure, seriously threatening the safe operation of the combustion chamber; the single micro-mixing nozzle mostly operates in a relatively low equivalence range, the combustion zone temperature is low, and changes in the adjustment instructions can easily lead to poor flame combustion stability, which in turn creates the risk of flameout and shutdown.

[0136] Therefore, in view of the above problems, it is urgent to design a gas turbine combustion chamber system (including combustion chamber and burner nozzle) that can take into account the above problems at the same time. The redesign of the burner not only needs to consider the anti-flashback and low emission design of the burner itself, but also needs to take into account the requirements of the overall design of the combustion chamber, including the ability to adjust the different loads of the gas turbine, the ability to suppress thermal and acoustic instability, the outlet temperature distribution uniformity index and the lower pressure loss coefficient.

[0137] In view of this, an embodiment of the present disclosure provides a combined nozzle combustion chamber, including a flame tube barrel, wherein the flame tube barrel encloses a combustion zone, and at the air intake end of the flame tube barrel is provided: a central diffusion combustion nozzle for realizing diffusion combustion of fuel and air in the combustion zone; a plurality of unit micro-mixing combustion nozzles for realizing micro-mixing premixed combustion of fuel and air in the combustion zone; and a plurality of lean direct injection combustion nozzles for realizing lean direct injection combustion of fuel and air in the combustion zone.

[0138] Figure 1 is a schematic diagram of the distribution structure of various types of nozzles in a combined nozzle combustion chamber according to an embodiment of the present disclosure; Figure 2 It is a schematic diagram of the distribution structure of various types of nozzles within the flame tube body in the combined nozzle combustion chamber according to an embodiment of the present disclosure.

[0139] like Figure 1 , Figure 2 As shown, the combined nozzle combustion chamber 6 of the embodiment of the present disclosure includes a flame tube cylinder 62, wherein the flame tube cylinder 62 encloses a combustion zone, and is provided at the air intake end of the flame tube cylinder 62 with: a central diffusion combustion nozzle 1 for realizing diffusion combustion of fuel and air in the combustion zone; a plurality of unit micro-mixing combustion nozzles 2 for realizing micro-mixing premixed combustion of fuel and air in the combustion zone; and a plurality of lean direct injection combustion nozzles 3 for realizing lean direct injection combustion of fuel and air in the combustion zone.

[0140] According to the embodiment of the present disclosure, in the combined nozzle combustion chamber 6, since the flame stability of the central diffusion combustion nozzle 1 is good and it is not easy to go out, the central diffusion combustion nozzle 1 can be set in the middle position of the combined nozzle combustion chamber 6 for use as a duty class. The diffusion combustion flame has high stability and low thermal acoustic oscillation. By introducing the central diffusion combustion nozzle 1, the flame stability can be effectively improved, the ignition of the gas turbine is facilitated, and the stable propagation and combustion of the flame are maintained, thereby reducing the risk of flameout during load regulation changes.

[0141] According to the embodiments of the present disclosure, the central diffusion combustion nozzle has good thermal stability and small thermoacoustic oscillation due to the use of diffusion combustion, but the nitrogen oxide emissions are relatively high.

[0142] According to the embodiment of the present disclosure, the unit micro-mixing combustion nozzle adopts the method of premixed combustion. The structural flame stability of premixed combustion in the prior art is poor, and it is easy to have flashback problems, and the warm-up oscillation is large. The unit micro-mixing nozzle in the embodiment of the present disclosure is relatively small in scale, for example, the diameter is in the range of 5 to 15 mm, which realizes mixing at a micro scale, can improve the mixing efficiency, and improve the uniformity of the flame temperature in the flame tube; and because the multiple unit micro-mixing nozzles are distributed in an array, each nozzle outlet will produce a relatively independent small flame, so the generation of high-temperature areas in the flame tube can be avoided, and the temperature distribution at the outlet of the combined nozzle combustion chamber will be more uniform, reducing the peak flame temperature and suppressing nitrogen oxide emissions; and the small flame formed by the unit micro-mixing nozzle is relatively small in size, which also plays a positive role in shortening the length of the flame tube of the combined nozzle combustion chamber; the outlet of the unit micro-mixing nozzle has a high jet velocity, which can effectively suppress the flashback phenomenon during the combustion of high-hydrogen-content fuels. However, the above-mentioned unit micro-mixing combustion nozzle in the embodiment of the present disclosure is more prone to thermoacoustic oscillation.

[0143] According to the embodiments of the present disclosure, the lean direct injection combustion nozzle can realize lean direct injection combustion of fuel and air in the combustion zone, and its performance is between that of the central diffusion combustion nozzle and the unit micro-mixing combustion nozzle. It has lower nitrogen oxide emission performance, better flame stability, and is not prone to thermoacoustic oscillation.

[0144] By combining the three combustion modes of the central diffusion combustion nozzle, the unit micro-mixing combustion nozzle and the lean direct injection combustion nozzle, a combined nozzle combustion chamber with multiple injection units is formed, which can combine the advantages of multiple combustion modes to improve the comprehensive performance of the burner. The structure of the combined nozzle combustion chamber has low nitrogen oxide emission performance, good flame stability, and is not prone to thermoacoustic oscillation. At the same time, this structure can increase the heat load and load adjustment ratio of the combined nozzle combustion chamber, and ensure that when one of the nozzles is extinguished, the adjacent nozzle can re-ignite the extinguished nozzle, thereby maintaining flame stability.

[0145] According to the embodiments of the present disclosure, the structure of the combined nozzle combustion chamber can reduce the wear of the combined nozzle combustion chamber, extend the maintenance interval time and reduce the operating costs due to its stable performance. At the same time, the structure of the combined nozzle combustion chamber can also suppress noise and thermoacoustic oscillations with superior performance, thereby ensuring that the industrial gas turbine can safely and stably use a high proportion of hydrogen-containing fuel.

[0146] According to an embodiment of the present disclosure, a central diffusion combustion nozzle 1 is arranged at the center of the flame tube barrel 62; a plurality of unit micro-mixing combustion nozzles 2 are divided into at least one annular micro-mixing combustion combination, and in each annular micro-mixing combustion combination, a plurality of unit micro-mixing combustion nozzles are circumferentially distributed and arranged along the flame tube barrel 62; a plurality of lean direct injection combustion nozzles 3 are divided into at least one annular lean direct injection combustion combination, and in each annular lean direct injection combustion combination, a plurality of lean direct injection combustion nozzles 3 are circumferentially distributed and arranged along the flame tube barrel; the annular micro-mixing combustion combination and the annular lean direct injection combustion combination are alternately distributed radially along the flame tube barrel.

[0147] like Figure 1 and Figure 2As shown, the multiple unit micro-mixing combustion nozzles 2 are divided into four annular micro-mixing combustion combinations, and the multiple lean direct injection combustion nozzles 3 can be divided into two annular lean direct injection combustion combinations. The structure of the combined nozzle combustion chamber 6 can be that the central diffusion combustion nozzle 1 is arranged at the center of the flame tube barrel 62, and the structure of the combined nozzle combustion chamber 6 is sequentially arranged from the center of the flame tube barrel 63 to the outside of the central diffusion combustion nozzle, two annular micro-mixing combustion combinations, two annular micro-mixing combustion combinations, and two adjacent annular micro-mixing combustion combinations. The arrangement is alternating, but not limited to this. For example, the structure of the combined nozzle combustion chamber 6 can also be sequentially arranged from the center of the flame tube barrel 63 to the outside of the central diffusion combustion nozzle, two annular micro-mixing combustion combinations, two annular micro-mixing combustion combinations, two adjacent annular micro-mixing combustion combinations, and two annular micro-mixing combustion combinations, or it can be a central diffusion combustion nozzle, two annular micro-mixing combustion combinations, and two annular micro-mixing combustion combinations.

[0148] According to the embodiment of the present disclosure, since the flame stability of the central diffusion combustion nozzle 1 is good and not easy to extinguish, the flame stability and ignition performance can be effectively improved by setting the central diffusion combustion nozzle 1 in the middle position of the combined nozzle combustion chamber 6 for use as a duty class. In addition, by alternately distributing the annular micro-mixed combustion combination and the annular lean direct injection combustion combination along the radial direction of the flame tube, the micro-mixed premixed combustion flame and the lean direct injection combustion flame are mixed in the radial direction. The mixed flame formed by the mixing has high flame stability and good temperature uniformity, effectively reducing the emission of nitrogen oxides, and at the same time facilitating the ignition of the gas turbine and maintaining the stable propagation and combustion of the flame, reducing the risk of extinguishing during load regulation changes.

[0149] Figure 3 It is a schematic diagram of the connection structure between various types of nozzles and various types of fuel chambers in the combined nozzle combustion chamber according to an embodiment of the present disclosure.

[0150] like Figure 3 As shown, the combined nozzle combustion chamber 6 further includes: a central diffusion flame fuel chamber 47, wherein the central diffusion flame fuel chamber 47 is connected to the fuel inlet of the central diffusion combustion nozzle 1; at least one annular micro-mixed combustion flame fuel chamber ( Figure 3There is an inner micro-mixed combustion flame fuel cavity 48 and an outer micro-mixed combustion flame fuel cavity 50), wherein at least one micro-mixed combustion flame fuel cavity is matched one-to-one with at least one annular micro-mixed combustion combination, and the micro-mixed combustion flame fuel cavity is connected to the fuel inlet of the unit micro-mixed combustion nozzle 2; at least one annular lean direct injection combustion flame fuel cavity 49, wherein at least one lean direct injection combustion flame fuel cavity 49 is matched one-to-one with at least one annular lean direct injection combustion combination, and the lean direct injection combustion flame fuel cavity is connected to the fuel inlet of the lean direct injection combustion nozzle 3; each central diffusion flame fuel cavity 47, each micro-mixed combustion flame fuel cavity, and each lean direct injection combustion flame fuel cavity 49 are respectively connected to independent fuel intake nozzles ( Figure 3 They are respectively shown as a central fuel intake nozzle 45, a mild-mix fuel intake nozzle 46 and a lean direct injection fuel intake nozzle 51).

[0151] According to the embodiment of the present disclosure, the fuel supplied from the external fuel pipeline can be divided into a first portion of fuel, a second portion of fuel and a third portion of fuel. The first portion of fuel can enter the central diffusion flame fuel cavity 47 through the central fuel intake nozzle 45 and then flow into the central diffusion combustion nozzle 1; the second portion of fuel can enter the micro-mixed combustion flame fuel cavity through the micro-mixed fuel intake nozzle 46. Figure 3 It shows that it includes two annular micro-mixed combustion combinations, which are respectively connected to the inner micro-mixed combustion flame fuel cavity 48 and the outer micro-mixed combustion flame fuel cavity 50, that is, the second part of the fuel can enter the inner micro-mixed combustion flame fuel cavity 48 and the outer micro-mixed combustion flame fuel cavity 50 through the micro-mixed fuel intake nozzle 46, and then flow into the unit micro-mixed combustion nozzle 2; the third part of the fuel can enter the lean direct injection combustion flame fuel cavity 49 through the lean direct injection fuel intake nozzle 51, and then flow into the lean direct injection combustion nozzle 3.

[0152] According to the embodiments of the present disclosure, Figure 3 As shown, each of the multiple annular micro-mixed combustion combinations matches a micro-mixed combustion flame fuel cavity, the two inner micro-mixed combustion combinations may match the inner micro-mixed combustion flame fuel cavity 48, the two outer micro-mixed combustion combinations may match the outer micro-mixed combustion flame fuel cavity 50, and each of the multiple annular lean direct injection combustion combinations matches a lean direct injection combustion flame fuel cavity 49.

[0153] According to an embodiment of the present disclosure, the combined nozzle combustion chamber 6 may further include a fuel chamber bottom plate 41, a fuel chamber top plate 42 and a fuel chamber annular partition 43. Each central diffusion flame fuel chamber 47, each micro-mixed combustion flame fuel chamber, and each lean direct injection combustion flame fuel chamber 49 are separated by a fuel chamber annular partition 43, so that each ring combustion unit has an independent annular fuel supply chamber and a corresponding fuel intake nozzle, and each ring combustion unit can be supplied with fuel separately and the fuel flow rate can be independently adjusted.

[0154] One end of each central diffusion flame fuel cavity 47, each micro-mixed combustion flame fuel cavity, and each lean direct injection combustion flame fuel cavity 49 is connected to the fuel cavity bottom plate 41, and the other end is connected to the fuel cavity top plate 42. The other side of the fuel cavity bottom plate 41 connected to each central diffusion flame fuel cavity 47, each micro-mixed combustion flame fuel cavity, and each lean direct injection combustion flame fuel cavity 49 is respectively connected to an independent fuel intake nozzle, and the other side of the fuel cavity top plate 42 connected to each central diffusion flame fuel cavity 47, each micro-mixed combustion flame fuel cavity, and each lean direct injection combustion flame fuel cavity 49 is respectively connected to the central diffusion combustion nozzle 1, the unit micro-mixed combustion nozzle 2, and the lean direct injection combustion nozzle 3.

[0155] Figure 4 It is a cross-sectional view of the internal structure of the combined nozzle combustion chamber according to an embodiment of the present disclosure.

[0156] like Figure 4 As shown, the above-mentioned combined nozzle combustion chamber 6 also includes: a nozzle head end cover 44, which is fixedly installed on the air inlet end of the flame tube barrel 62, and is used to support the fixed central diffusion combustion nozzle 1, multiple unit micro-mixing combustion nozzles 2, and multiple lean direct injection combustion nozzles 3; the nozzle head end cover 44 can be opened at a position corresponding to the fixed central diffusion combustion nozzle 1, multiple unit micro-mixing combustion nozzles 2, and multiple lean direct injection combustion nozzles 3, so that the central diffusion combustion nozzle 1, multiple unit micro-mixing combustion nozzles 2, and multiple lean direct injection combustion nozzles 3 are fixed on the nozzle head end cover 44.

[0157] According to an embodiment of the present disclosure, the above-mentioned combined nozzle combustion chamber 6 also includes: a casing 61, which is arranged on the outside of the flame tube barrel 62, and an annular cavity 601 is formed between the inner wall of the casing 61 and the outer wall of the flame tube barrel 62, and the annular cavity 601 is provided with an air inlet, which is connected to the outside and is used to introduce air into the annular cavity 601; a casing end cover 64, which is arranged at the front end of the casing, and is used to support and fix the casing 61, and is used to support and fix the central diffusion flame fuel cavity 47, the micro-mixed combustion flame fuel cavity, and the lean direct injection combustion flame fuel cavity 49; a support tube 66, the two ends of the barrel of the support tube 66 are respectively connected to the casing end cover 64 and the flame tube barrel 62, and a nozzle air intake area 602 is formed inside the support tube, wherein an air introduction hole 68 is provided in the barrel wall of the support tube 66, and the annular cavity 601 is connected with the nozzle air intake area 602 through the air introduction hole 68; wherein, the air inlets of the central diffusion combustion nozzle 1, the unit micro-mixed combustion nozzle 2, and the lean direct injection combustion nozzle 3 are located in the nozzle air intake area 602.

[0158] The combined nozzle combustion chamber 6 further comprises: a casing front flange 63, a bolt mounting hole 65, a flame tube exhaust end 67, and an ignition nozzle 69. The bolt mounting hole 65 is provided on the casing end cover 64, and the casing front flange 63 has holes corresponding to the bolt mounting holes 65, so that the casing 61 is fixed to the casing end cover 64 through the casing front flange 63.

[0159] According to the embodiment of the present disclosure, the air compressor sucks in air from the external environment and compresses it. The compressed high-pressure air A flows into the combined nozzle combustion chamber 6, first flows upstream along the annular cavity 601 to reach the head of the combined nozzle combustion chamber 6, and then enters the nozzle air intake area 602 through the air inlet hole 68 on the support tube 66, and then enters each combustion unit respectively, and after being fully mixed with the fuel, forms a high-speed and uniform premixed fuel gas, and then enters the combustion area for combustion.

[0160] Figure 5A It is a schematic structural diagram of a unit micro-mixing combustion nozzle according to an embodiment of the present disclosure.

[0161] As shown in FIG5 , the unit micro-mixing combustion nozzle 2 includes a nozzle housing 21, wherein the nozzle housing 21 is provided with: a fuel intake chamber 22, the fuel intake chamber 22 is configured to pass the fuel f1; a premixing chamber 26, the cavity wall of the premixing chamber 26 is provided with an air intake hole, the air intake hole is configured to pass the air, and the outlet end of the premixing chamber 26 is connected to the combustion zone. The premixing chamber 26 and the fuel intake chamber 22 are connected through the fuel injection hole 23.

[0162] According to an embodiment of the present invention, through the above-mentioned structural arrangement, the air flow entering from the air inlet hole and the fuel flow entering from the fuel injection hole 23 form a fuel / air lateral cross jet, which promotes the full mixing of fuel and air in the unit micro-mixing nozzle 2 through strong turbulent interaction, thereby further reducing nitrogen oxide emissions.

[0163] According to the embodiment of the present disclosure, the premixing chamber 26 is used to: mix the air entering through the air intake hole and the fuel f1 from the fuel intake chamber 22 to form a premixed gas p1, and then spray the premixed gas into the combustion zone to achieve micro-mixed premixed combustion of the fuel and air in the combustion zone; wherein, a nozzle cooling air film hole 27 is provided in the cavity wall near the outlet end of the premixing chamber 26. The nozzle cooling air film hole 27 is arranged near the outlet of the nozzle housing 21, and several layers are evenly arranged along the circumference, which can reduce the wall temperature and the fuel / air ratio of the wall boundary layer, and is used to cool the tube wall temperature, break the inner boundary layer of the tube wall, and help reduce the temperature of the premixed gas p1 in the premixing chamber 26. Compared with the technology of the micro-mixed combustion unit in the related art, the unit micro-mixed combustion nozzle provided in the embodiment of the present disclosure can further improve the nozzle's anti-flashback and anti-fire performance, thereby ensuring the safe operation of the combined nozzle combustion chamber 6.

[0164] According to an embodiment of the present disclosure, the air intake hole includes a primary air intake hole 24 and a secondary air intake hole 25, and the primary air intake hole 24 and the secondary air intake hole 25 are arranged along the gas flow direction in the premixing chamber 26. Under the same intake hole area, two-stage air intake holes are provided, which can make the mixing of air and fuel more uniform compared to only providing the primary air intake hole 24. Because the two-stage air holes are staggered in the circumferential direction, uniform air intake without dead angles in the circumferential direction of 360° is guaranteed, so that the mixing of air and fuel is more uniform in the entire space.

[0165] The mixing process in the unit micro-mixing combustion nozzle 2 is as follows: inside the unit micro-mixing combustion nozzle 2, the fuel flow f1 flowing from the entrance of the fuel intake cavity 22 forms a high-speed jet fuel-unit micro-mixing combustion nozzle accelerated fuel flow f2 after passing through the fuel injection hole 23; at the same time, air (combustion reaction air flow a5) enters the nozzle from the multi-row circumferentially arranged multi-stage air intake holes opened on the nozzle shell 21, and is quickly mixed with the unit micro-mixing nozzle accelerated fuel flow f2. After multi-stage sufficient mixing, a high-speed uniform premixed gas p1 is formed, and the premixed gas p1 can be ejected from the nozzle at a high speed and burn in the combustion zone. By adopting a fuel / air transverse cross-jet structure, the fuel and air are fully mixed in the unit micro-mixing combustion nozzle 2 through strong turbulent interaction, thereby improving the uniformity of the flame temperature in the flame tube, reducing the flame peak temperature, and suppressing nitrogen oxide emissions.

[0166] Figure 5B It is a schematic structural diagram of a unit micro-mixing combustion nozzle according to another embodiment of the present disclosure.

[0167] like Figure 5B As shown, the nozzle housing 21 adopts a circular tubular structure, and the diameter of the nozzle housing 21 is 5 to 15 mm.

[0168] The structure of the unit micro-mixing nozzle 2 of this embodiment is Figure 5A The embodiments are substantially the same, except that the fuel intake cavity 22 includes a tubular intake pipe with a closed end, the intake pipe is coaxially arranged with the nozzle housing 21, so that an annular premixing chamber 26 is formed between the outer surface of the intake pipe and the inner surface of the nozzle housing; a fuel injection hole 23 is provided at the front end of the intake pipe, and a concave center body 28 is provided at the end of the intake pipe.

[0169] The end of the concave center body 28 adopts an inwardly concave curved surface shape to ensure that a reflow zone that develops upstream will not be generated. The front stagnation point of the reflow zone cannot continue to develop upstream when it reaches the concave surface, thereby further reducing the risk of nozzle flashback.

[0170] Figure 6 It is a schematic structural diagram of a central diffusion combustion nozzle according to an embodiment of the present disclosure.

[0171] like Figure 6 As shown, the central diffusion combustion nozzle 1 includes: a sleeve 11, a swirl cup 12, a fuel nozzle 13, a venturi 14 and a fuel injection hole 15.

[0172] The sleeve 11 is provided with an air inlet and a diffusion gas outlet, wherein the air inlet is configured to allow air to enter, and the diffusion gas outlet is connected to the combustion zone. The diffusion gas outlet of the sleeve 11 is an expansion type outlet to limit the radial expansion of the flame and provide space for the front stagnation point of the recirculation zone.

[0173] The inlet end of the fuel nozzle 13 is configured to allow fuel to flow in, and the outlet end of the fuel nozzle 13 is provided with a fuel injection hole 15. The fuel nozzle 13 and the sleeve 11 are connected through the fuel injection hole 15, and the diameter of the fuel injection hole 15 is 1-3 mm.

[0174] The venturi tube 14 is disposed in the sleeve 11 , and the fuel nozzle 13 and the venturi tube 14 are connected through the fuel injection hole 15 to further increase the airflow diffusion speed and improve the combustion stability.

[0175] The swirl cup 12 is arranged at the air inlet of the sleeve 11 so that a swirl is formed in the sleeve 11 after the air enters, thereby improving the combustion stability.

[0176] Among them, the central diffusion combustion nozzle 1 is used to: after the air entering through the air inlet and the fuel injected through the fuel nozzle 13 are diffused by the sleeve 11, they are sprayed into the combustion zone through the diffusion gas outlet of the sleeve 11 to realize the diffusion combustion of the fuel and air in the combustion zone.

[0177] Fig. 7A is a schematic diagram of the external structure of a lean direct injection combustion nozzle according to an embodiment of the present disclosure; Figure 7B yes Fig. 7A Schematic diagram of the internal structure of the lean direct injection combustion nozzle shown.

[0178] like Fig. 7A and Figure 7B As shown, the lean direct injection combustion nozzle 3 is provided with: a central fuel delivery channel 31 and a plurality of air delivery channels 32.

[0179] Among them, the inlet end of the central fuel delivery channel 31 is configured to pass fuel; multiple air delivery channels 32 are distributed circumferentially around the central fuel delivery channel 31, the inlet end of the air delivery channel 32 is configured to pass air, and the outlet end of the air delivery channel is connected to the combustion zone, each air delivery channel 32 is separately connected to the central fuel delivery channel 31, so that the fuel in the central fuel delivery channel 31 can be dispersed and passed into multiple air delivery channels 32, and the air delivery channels 32 and the central fuel delivery channel 31 are connected at a position close to the outlet of the lean direct injection combustion nozzle 3, and the air delivery channel 32 is used to inject the air introduced from the outside and the fuel from the central fuel delivery channel 31 into the combustion zone after lean premixing, so as to realize lean direct injection combustion of fuel and air in the combustion zone.

[0180] Among them, the mixing process inside the lean direct injection combustion nozzle 3 is as follows: inside the lean direct injection combustion nozzle 3, the fuel flow flowing from the inlet end of the central fuel delivery channel 31 passes through the central fuel delivery channel 31 and flows into the air delivery channel 32 at the outlet position close to the lean direct injection combustion nozzle 3, and is mixed with the air flowing in through the air delivery channel 32 and ejected.

[0181] According to the embodiment of the present disclosure, similar to the micro-mixing combustion unit, the lean direct injection combustion unit also has a small-sized air (oxidant) circulation channel, but the difference is that the lean direct injection combustion unit described in the embodiment of the present disclosure forms multiple small-scale air delivery channels in the central fuel delivery channel. Compared with the micro-mixing combustion unit, it can achieve smaller-scale combustion, and the small flames formed at the outlets of the multiple air delivery pipes 32 are smaller in size and have a more uniform temperature distribution, further reducing nitrogen oxide emissions, and on this basis further improving the flame's anti-extinguishing ability, making the flame stability higher.

[0182] According to the embodiment of the present disclosure, the micro-mixing combustion unit injects fuel inside the air circulation channel and forms a combustion flame at the outlet. The fuel and air have been fully mixed before combustion, and there is a certain risk of flashback and thermoacoustic oscillation, and the flame stability is poor. The lean direct injection combustion unit of the embodiment of the present disclosure realizes fuel and air mixing and injection near the outlet of the air circulation channel. The fuel and air meet at the outlet and burn while mixing. There is no risk of flashback and thermoacoustic oscillation, and the flame stability is good and it is not easy to extinguish.

[0183] Figure 7C is a structural schematic diagram of a lean direct injection combustion nozzle according to another embodiment of the present disclosure; Fig.7D yes Figure 7C The schematic diagram of the internal structure of the lean direct injection combustion nozzle is shown; Fig. 7E is a structural schematic diagram of a lean direct injection combustion nozzle according to another embodiment of the present disclosure; Figure 7F yes Fig. 7E The schematic diagram of the end face structure of the lean direct injection combustion nozzle is shown.

[0184] like Figure 7C to Figure 7F As shown, the lean direct injection combustion nozzle 3 includes: a central fuel delivery pipe and a plurality of air delivery pipes.

[0185] A central fuel delivery channel 31 is formed in the central fuel delivery pipe, the inlet end of the central fuel delivery pipe is configured to allow fuel to flow in, and the outlet end of the central fuel delivery pipe is provided with a plurality of fuel ejection holes.

[0186] According to an embodiment of the present disclosure, a plurality of air delivery pipes are circumferentially distributed around a central fuel delivery pipe, an air delivery channel 32 is formed in the air delivery pipe, the air delivery pipe includes a slope inlet end 33 and a direct injection outlet 321, the slope inlet end 33 is configured to allow air to pass through, the direct injection outlet 321 is connected to the combustion zone, and a fuel injection hole 35 is provided near the direct injection outlet 321, and the plurality of air delivery pipes and the plurality of fuel injection holes 35 are matched one by one, so that the fuel in the central fuel delivery pipe can be dispersed into the plurality of air delivery pipes through the plurality of fuel injection holes 35, and the air delivery pipe is used to carry out lean premixing of the air entering through the slope inlet end 33 and the fuel entering through the fuel injection hole 35, and then inject them into the combustion zone through the direct injection outlet 321;

[0187] According to an embodiment of the present disclosure, the plurality of air delivery tubes distributed circumferentially around the central fuel delivery tube are straight tubes, the central axis of the air delivery tubes is parallel to the central axis of the central fuel delivery tube, and the cross section of the straight tubes is circular or petal-shaped.

[0188] For example, in Fig. 7A and Figure 7BIn the embodiment, the plurality of air delivery pipes circumferentially distributed around the central fuel delivery pipe are straight pipes, the central axis of the air delivery pipes is parallel to the central axis of the central fuel delivery pipe, and the cross section of the straight pipes is circular.

[0189] According to an embodiment of the present disclosure, the multiple air delivery pipes distributed circumferentially around the central fuel delivery pipe may also be spiral pipes, which are conducive to forming a weak swirl to further improve flame stability. The cross-section of the spiral pipe is circular or petal-shaped.

[0190] For example, in Figure 7C to Figure 7F In the embodiment, the plurality of air delivery pipes circumferentially distributed around the central fuel delivery pipe may also be spiral pipes. Figure 7C and Fig.7D The cross section of the spiral tube shown in is circular. Fig. 7E The cross section of the spiral tube in the lean direct injection combustion nozzle 3 shown in FIG is petal-shaped, as shown in FIG. Figure 7F As shown in , it helps to form a weak swirl to further improve flame stability.

[0191] According to an embodiment of the present disclosure, the inlet end of the air delivery channel 32 gradually decreases in length radially outward to form a sloped inlet end 33, which serves to allow the circumferential incoming air to enter the air delivery pipe more evenly. The central fuel delivery channel 31 is flush with the end of the air delivery channel 32, and an end cover 34 is provided at the end of the central fuel delivery channel 31 so that the fuel can be sprayed through the fuel spray hole 35 when it reaches the end of the central fuel delivery channel 31. The fuel spray hole 35 corresponds to the air delivery channel 32 one by one, that is, one air delivery channel 32 corresponds to one fuel spray hole 35.

[0192] According to the embodiments of the present disclosure, a plurality of air delivery channels 32 are arranged in each lean direct injection combustion nozzle 3. In each air delivery channel 32, a single stream of fuel ejected from a single fuel ejection hole 35 arranged at the end of the central fuel delivery channel 31 can be mixed with a single stream of air in the air delivery channel 32 in a one-to-one mode at the outlet of the air delivery channel 32, thereby avoiding the mutual influence and uneven distribution of multiple streams of fuel ejected from multiple fuel ejection holes 35 and air when they are mixed at the outlet of a large-sized pipeline. Compared with the existing lean direct injection combustion technology, it realizes injection and rapid mixing at a smaller scale, can improve the mixing and combustion efficiency, and can effectively reduce the peak temperature of the flame during the combustion process.

[0193] Figure 7G is a structural schematic diagram of a lean direct injection combustion nozzle according to another embodiment of the present disclosure; Figure 7H yes Figure 7G Schematic diagram of the internal structure of the lean direct injection combustion nozzle.

[0194] like Figure 7G and Figure 7HAs shown, the lean direct injection combustion nozzle 3 includes: a central fuel delivery pipe and an end tube shell 37.

[0195] Among them, a central fuel delivery channel 31 is formed in the central fuel delivery pipe, and the central fuel delivery pipe includes a straight pipe section 38, a transition section 39 and a forming section 40 which are connected in sequence front and back. The inlet end of the straight pipe section 38 is configured to allow the fuel to pass through. The cross-section of the forming section 40 is a petal-shaped structure, and a plurality of fuel ejection holes 35 are provided at the outlet end of the forming section.

[0196] The end tube shell 37 is arranged around the outside of the forming section so that a plurality of fan-shaped air delivery channels 32 are formed between the inner wall of the end tube shell 37 and the outer wall of the forming section 40, and each fan-shaped air delivery channel 32 corresponds to at least one fuel ejection hole 35, so that the fuel in the central fuel delivery pipe can be dispersed into the plurality of fan-shaped air delivery channels 32 through the plurality of fuel ejection holes 35.

[0197] According to an embodiment of the present disclosure, Figure 7G and Figure 7H In the lean direct injection combustion nozzle 3, the cross-section of the straight pipe section 38 is circular, and after passing through the transition section 39, the cross-section of the forming section 40 is a petal-shaped structure. The petal-shaped structure can be formed by the lobe structure 36 and the inner wall of the end tube shell 37 and the outer wall of the forming section 40 to form a plurality of fan-shaped air delivery channels 32. Each fan-shaped air delivery channel 32 is independent of each other. A fuel ejection hole 35 is arranged on the side wall of each lobe structure 36 adjacent to the air delivery channel 32. The fuel ejection hole 35 is close to the end cover 34 and corresponds to the air delivery channel 32, that is, one air delivery channel 32 corresponds to two fuel ejection holes 35.

[0198] Figure 8 is a system schematic diagram of a gas turbine power generation system according to an embodiment of the present invention.

[0199] like Figure 8 As shown, the gas turbine power generation system includes a compressor 71, a combined nozzle combustion chamber 6, a turbine 72, a generator 73 and a starter motor 74.

[0200] Among them, the compressor 71 is configured to compress air; the combined nozzle combustion chamber 6 is connected to the compressor 71, and is configured to introduce fuel and high-pressure air A originating from the compressor 71, so that the fuel and air are burned in the combined nozzle combustion chamber 6 to generate high-temperature combustion gas G of a predetermined temperature; the turbine 72 includes a turbine, wherein the turbine 72 is connected to the combined nozzle combustion chamber 6, and is configured to use the high-temperature combustion gas of a predetermined temperature originating from the radial combustion chamber to drive the turbine to rotate; the generator 73 is mechanically connected to the output shaft of the turbine, and is configured to generate electrical energy under the drive of the turbine.

[0201] According to the embodiment of the present disclosure, the air compressor 71 sucks air from the external environment and compresses it. The compressed high-pressure air A flows into the combined nozzle combustion chamber 6, first flows upstream along the annular cavity 601 to the head of the combined nozzle combustion chamber 6, then enters the nozzle intake area 602 through the air introduction hole 68 on the support tube 66, and then enters each combustion unit, and after being fully mixed with the fuel, forms a high-speed and uniform premixed fuel gas, and then enters the combustion area for combustion. The high-temperature combustion gas G generated flows through the turbine 72 and expands to do work, and the exhaust gas E generated after doing work is discharged into the atmosphere. The generator 73 generates electricity under the high-speed rotation drive of the turbine 72.

[0202] The specific embodiments described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A combined nozzle combustion chamber, comprising a flame tube body, wherein the flame tube body encloses a combustion zone, and an air inlet end of the flame tube body is provided with: A central diffusion combustion nozzle for achieving diffusion combustion of fuel and air in the combustion zone; A plurality of unit micro-mixing combustion nozzles are used to achieve micro-mixing premixed combustion of fuel and air in the combustion zone; a plurality of lean direct injection combustion nozzles for achieving lean direct injection combustion of fuel and air in the combustion zone; The central diffusion combustion nozzle is arranged at the center of the flame tube body; The multiple unit micro-mixing combustion nozzles are divided into at least one annular micro-mixing combustion combination, and in each of the annular micro-mixing combustion combinations, the multiple unit micro-mixing combustion nozzles are distributed and arranged along the circumference of the flame tube body; The multiple lean direct injection combustion nozzles are divided into at least one annular lean direct injection combustion combination, and in each of the annular lean direct injection combustion combination, the multiple lean direct injection combustion nozzles are distributed and arranged along the circumference of the flame tube body; The annular micro-mixed combustion combination and the annular lean direct injection combustion combination are alternately distributed along the radial direction of the flame tube body.

2. The combined nozzle combustion chamber according to claim 1, further comprising: a central diffusion flame fuel cavity, wherein the central diffusion flame fuel cavity is in communication with a fuel inlet of a central diffusion combustion nozzle; At least one annular micro-mixed combustion flame fuel cavity, wherein at least one micro-mixed combustion flame fuel cavity is matched with at least one annular micro-mixed combustion combination, and the micro-mixed combustion flame fuel cavity is connected to the fuel inlet of the unit micro-mixed combustion nozzle; At least one annular lean direct injection combustion flame fuel cavity, wherein at least one lean direct injection combustion flame fuel cavity is matched with at least one annular lean direct injection combustion combination one by one, and the lean direct injection combustion flame fuel cavity is connected to the fuel inlet of the lean direct injection combustion nozzle; Each of the central diffusion flame fuel chambers, each of the micro-mixed combustion flame fuel chambers, and each of the lean direct injection combustion flame fuel chambers are respectively connected to independent fuel intake nozzles.

3. The combined nozzle combustion chamber according to claim 1, further comprising: The nozzle head end cover is fixedly mounted on the air inlet end of the flame tube body, and is used to support and fix the central diffusion combustion nozzle, the multiple unit micro-mixing combustion nozzles, and the multiple lean direct injection combustion nozzles; A casing is arranged outside the flame tube body, an annular cavity is formed between the inner wall of the casing and the outer wall of the flame tube body, the annular cavity is provided with an air inlet, the air inlet is communicated with the outside, and is used to introduce air into the annular cavity; A casing end cover is arranged at the front end of the casing, and is used to support and fix the casing, and is used to support and fix the central diffusion flame fuel cavity, the mild-mixed combustion flame fuel cavity, and the lean direct injection combustion flame fuel cavity; A support tube, wherein both ends of the support tube are connected to the casing end cover and the flame tube body respectively, and a nozzle air inlet area is formed inside the support tube, wherein an air introduction hole is provided in the wall of the support tube, and the annular cavity is connected to the nozzle air inlet area through the air introduction hole; Among them, the air inlets of the central diffusion combustion nozzle, the unit micro-mixing combustion nozzle, and the lean direct injection combustion nozzle are located in the nozzle intake area.

4. The combined nozzle combustion chamber according to claim 1, wherein: The unit micro-mixing combustion nozzle comprises a nozzle housing, wherein the nozzle housing is provided with: a fuel intake cavity configured to admit fuel; A premixing chamber, wherein an air inlet hole is provided in the cavity wall of the premixing chamber, wherein the air inlet hole is configured to allow air to enter, wherein the outlet end of the premixing chamber is connected to the combustion zone, wherein the premixing chamber and the fuel inlet cavity are connected via a fuel injection hole, and the premixing chamber is used to: mix the air entering through the air inlet hole and the fuel from the fuel inlet cavity to form a premixed gas, and then inject the premixed gas into the combustion zone, so as to achieve micro-mixed premixed combustion of fuel and air in the combustion zone; Wherein, a nozzle cooling air film hole is provided in the cavity wall near the outlet end of the premixing chamber; The air inlet holes include a primary air inlet hole and a secondary air inlet hole, and the primary air inlet holes and the secondary air inlet holes are arranged along the gas flow direction in the premixing chamber.

5. The combined nozzle combustion chamber according to claim 4, wherein: The nozzle housing adopts a circular tubular structure; The fuel intake cavity comprises a closed-end cylindrical intake pipe, the intake pipe being coaxially arranged with the nozzle housing so that an annular premixing chamber is formed between the outer surface of the intake pipe and the inner surface of the nozzle housing; The front end of the air intake pipe is provided with the fuel injection hole, and the end of the air intake pipe is provided with a concave center body.

6. The combined nozzle combustion chamber according to claim 1, wherein: The central diffusion combustion nozzle comprises: a sleeve, the sleeve being provided with an air inlet and a diffusion gas outlet, the air inlet being configured to admit air, the diffusion gas outlet being in communication with the combustion zone; A fuel nozzle, wherein the inlet end of the fuel nozzle is configured to allow fuel to flow in, the outlet end of the fuel nozzle is provided with a fuel injection hole, and the fuel nozzle and the sleeve are connected through the fuel injection hole; A venturi tube, wherein the venturi tube is disposed in the sleeve, and the fuel nozzle and the venturi tube are connected through the fuel injection hole; A swirl cup, the swirl cup being arranged at the air inlet of the sleeve so that a swirl is formed in the sleeve after the air enters; Among them, the central diffusion combustion nozzle is used to: spray the air entering through the air inlet and the fuel sprayed through the fuel nozzle into the combustion zone through the diffusion gas outlet of the sleeve after the diffusion effect of the sleeve, so as to realize the diffusion combustion of the fuel and air in the combustion zone.

7. The combined nozzle combustion chamber according to claim 1, wherein: The lean direct injection combustion nozzle is provided with: a central fuel delivery passage, wherein an inlet end of the central fuel delivery passage is configured to admit fuel; A plurality of air delivery channels are circumferentially distributed around the central fuel delivery channel, the inlet end of the air delivery channel is configured to introduce air, the outlet end of the air delivery channel is connected to the combustion zone, each of the air delivery channels is separately connected to the central fuel delivery channel, so that the fuel in the central fuel delivery channel can be dispersed and introduced into the plurality of air delivery channels, and the air delivery channels and the central fuel delivery channel are connected at a position close to the outlet of the lean direct injection combustion nozzle, and the air delivery channel is used to inject the air introduced from the outside and the fuel from the central fuel delivery channel into the combustion zone after lean premixing, so as to realize lean direct injection combustion of the fuel and air in the combustion zone.

8. The combined nozzle combustion chamber according to claim 7, wherein: The lean direct injection combustion nozzle comprises: A central fuel delivery pipe, wherein the central fuel delivery channel is formed in the central fuel delivery pipe, the inlet end of the central fuel delivery pipe is configured to allow fuel to flow in, and the outlet end of the central fuel delivery pipe is provided with a plurality of fuel ejection holes; A plurality of air delivery pipes, the plurality of air delivery pipes are circumferentially distributed around the central fuel delivery pipe, the air delivery channel is formed in the air delivery pipe, the air delivery pipe comprises a ramp inlet end and a direct injection outlet, the ramp inlet end is configured to allow air to pass through, the direct injection outlet is connected to the combustion zone, and the fuel injection hole is provided near the direct injection outlet, the plurality of air delivery pipes and the plurality of fuel injection holes are matched one by one, so that the fuel in the central fuel delivery pipe can be dispersedly passed into the plurality of air delivery pipes through the plurality of fuel injection holes, and the air delivery pipe is used to carry out lean premixing of the air entering through the ramp inlet end and the fuel entering through the fuel injection hole, and then inject the mixture into the combustion zone through the direct injection outlet; Wherein, the plurality of air delivery pipes distributed circumferentially around the central fuel delivery pipe are straight pipes, the central axis of the air delivery pipe is parallel to the central axis of the central fuel delivery pipe, and the cross section of the straight pipe is circular or petal-shaped; or The plurality of air delivery pipes circumferentially distributed around the central fuel delivery pipe are spiral pipes, and the cross section of the spiral pipes is circular or petal-shaped.

9. The combined nozzle combustion chamber according to claim 7, wherein: The lean direct injection combustion nozzle comprises: A central fuel delivery pipe, wherein the central fuel delivery channel is formed in the central fuel delivery pipe, the central fuel delivery pipe comprises a straight pipe section, a transition section and a forming section connected in sequence, the inlet end of the straight pipe section is configured to allow fuel to flow in, the cross section of the forming section is a petal-shaped structure, and the outlet end of the forming section is provided with a plurality of fuel ejection holes; An end tube shell is arranged around the outside of the forming section so that a plurality of fan-shaped air delivery channels are formed between the inner wall of the end tube shell and the outer wall of the forming section, and each fan-shaped air delivery channel corresponds to at least one fuel ejection hole, so that the fuel in the central fuel delivery pipe can be dispersed into the plurality of fan-shaped air delivery channels through the plurality of fuel ejection holes.

Images