WO2018090383A1

WO2018090383A1 - Combustion chamber of gas turbine engine, and nozzle thereof

Info

Publication number: WO2018090383A1
Application number: PCT/CN2016/106667
Authority: WO
Inventors: 王志强; 杨瑞; 左成艺; 曹晶
Original assignee: 深圳智慧能源技术有限公司
Priority date: 2016-11-21
Filing date: 2016-11-21
Publication date: 2018-05-24

Abstract

A nozzle (12) of a combustion chamber of a gas turbine engine, the nozzle comprising: a main nozzle member (20) forming an internal fuel gas channel (24) and a fuel gas outlet (26) in fluid communication with the fuel gas channel (24). The nozzle (12) further comprises an outer wall (22). The outer wall (22) comprises a cylindrical portion (36) and an end portion (38) located at a terminal end of the cylindrical portion (36). The cylindrical portion (36) surrounds the main nozzle member (20) and is spaced apart from the main nozzle member (20) in the radial direction to form an air channel (28) between the main nozzle member (20) and the outer wall (22). The air channel (28) is in fluid communication with the fuel gas outlet (26). The cylindrical portion (36) forms a mixed gas outlet (30) in fluid communication with the air channel (28), such that a fuel gas jetted from the fuel gas outlet (26) is mixed with the air in the air channel (28), and then jetted from the mixed gas outlet (30).

Description

Gas turbine combustion chamber and its nozzle

Technical field

[0001] The present invention relates to a gas turbine, and more particularly to a combustion chamber of a gas turbine and a nozzle thereof.

Background technique

[0002] In a gas turbine combustor, fuel gas and air pass through a nozzle to achieve premixing and speed type change, achieve a reasonable velocity distribution at the nozzle outlet, and match a reasonable fuel-air mixing ratio, enter the combustion chamber for combustion, and form a stable Flow field and combustion field. However, existing gas turbine combustor nozzles have problems in that the gas and air are not uniformly mixed in the premixing passage, which tends to cause unstable combustion, generate more polluting emissions, and may cause tempering in the premixing passage, A component such as a valuable cyclone installed in the premixed passage causes ablation and destruction.

[0003] During the process of spraying the flame into the combustion chamber, the nozzle in the gas turbine combustion chamber may have a high pressure in the nozzle, so that the flame ejected from the nozzle is directly sprayed onto the inner wall of the flame tube or the internal components. Even direct injection onto adjacent nozzles causes severe ablation and damage, greatly reducing the service life of the gas turbine combustor and its nozzles.

[0004] Therefore, there is an urgent need for a reasonably effective gas turbine combustor structure and nozzle structure to solve at least one of the problems set forth above.

technical problem

In view of the above, the present invention provides a nozzle for a gas turbine combustor that can solve at least one of the above problems.

The present invention also provides a gas turbine combustor to which the above nozzle is applied.

Problem solution

Technical solution

[0007] A nozzle of a gas turbine combustor, comprising a main nozzle, the main nozzle forming an internal gas passage and a gas outlet in fluid communication with the gas passage, the nozzle further comprising a nozzle outer wall, the nozzle outer wall including a nozzle An outer wall cylindrical portion and a nozzle outer wall end portion at an end of the nozzle outer wall cylindrical portion, the nozzle outer wall cylindrical portion surrounding the main nozzle and radially spaced from the main nozzle to be An air passage is formed between the main nozzle and the outer wall of the nozzle, the air passage is in fluid communication with the gas outlet, and the outer wall portion of the nozzle forms a mixed gas outlet that is in fluid communication with the air passage, so that the gas outlet is sprayed from the gas outlet The discharged gas is mixed with the air in the air passage and ejected from the mixed gas outlet

[0008] In an embodiment, the main nozzle includes a main nozzle cylindrical portion and a main nozzle end portion at an end of the main nozzle cylindrical portion, and the main nozzle cylindrical portion defines the internal gas passage, The gas outlet extends through the main nozzle barrel, and the main nozzle end is a closed end such that gas in the gas passage can only be ejected from the gas outlet.

In one embodiment, the gas outlet is located adjacent to the closed end, the gas outlet corresponds to the mixed gas outlet in a radial direction, and the internal gas passage extends in the axial direction.

[0010] In an embodiment, the gas outlet has a pore size smaller than an aperture of the mixed gas outlet.

[0011] In an embodiment, the nozzle outer wall end portion is provided with an end through hole and is axially spaced from the main nozzle end portion.

[0012] In an embodiment, a swirler is formed in the air passage to form a swirling flow of air in the air passage.

[0013] In an embodiment, the main nozzle includes a main nozzle cylindrical portion, and the cyclone includes a plurality of blades disposed on an outer circumferential surface of the main nozzle cylindrical portion.

[0014] In an embodiment, the vane is fixedly coupled to at least one of an outer circumferential surface of the main nozzle cylindrical portion and an inner circumferential surface of the nozzle outer wall.

[0015] In an embodiment, the number of the gas outlet and the mixed gas outlet are two and correspond to each other, and the mixed gas injection directions defined by the two mixed gas outlets are opposite.

[0016] The present invention also provides a gas turbine combustor comprising an annular flame cylinder, the annular flame cylinder forming an annular combustion chamber, the annular combustion chamber defining an axial direction and a circumferential direction around the axial direction; a plurality of nozzles in the annular combustion chamber, the plurality of nozzles being uniformly arranged along the circumferential direction, the nozzles for injecting a mixed gas mixed with gas and air into the combustion chamber; each nozzle is provided with at least one A mixed gas outlet, the mixed gas outlet defining a mixed gas injection direction, the mixed gas injection direction being a direction toward an adjacent nozzle.

[0017] In an embodiment, two nozzles are provided for each nozzle, and the two mixture outlets are defined The mixed gas injection direction is reversed.

[0018] In an embodiment, the mixed gas injection direction is along the circumferential direction.

[0019] In an embodiment, each of the nozzles includes: a main nozzle including a main nozzle cylinder extending along the axial direction, the main nozzle cylinder end is closed, the main nozzle barrel The nozzle has an internal gas passage and a gas outlet extending through the main nozzle barrel; a nozzle outer wall, the nozzle outer wall includes a nozzle outer wall cylindrical portion, and the nozzle outer wall cylindrical portion surrounds the main nozzle cylindrical portion Radially spaced from the main nozzle cylindrical portion to form an annular air passage between the main nozzle cylindrical portion and the nozzle outer wall cylindrical portion, the mixed gas outlet penetrating through the nozzle outer wall cylindrical portion and The gas outlets correspond in the radial direction such that the gas ejected from the gas outlet is mixed with the air in the air passage and ejected from the mixed gas outlet.

Advantageous effects of the invention

Beneficial effect

[0020] In summary, the present invention provides a gas turbine combustor and a nozzle thereof, the nozzle includes a main nozzle and a nozzle outer wall disposed around the main nozzle, the main nozzle forms a gas passage, and the outer wall of the nozzle is radially spaced from the main nozzle An air passage is formed between the two, a gas outlet is arranged on the main nozzle, and a mixed gas outlet corresponding to the gas outlet is arranged on the outer wall of the nozzle, so that the gas discharged from the gas outlet is mixed with the air in the air passage and then ejected from the mixed gas outlet. The injection direction of the mixed gas outlet of each nozzle faces the adjacent nozzle. The nozzle structure of the invention is ingeniously designed to better mix the gas and the air, and inject the mixed gas into the combustion chamber of the combustion chamber for combustion, thereby avoiding damage of the flame wall by the high temperature flame. The combustion chamber of the gas turbine of the invention has a simple structure and novel concept, can minimize damage to various components of the combustion chamber, improve combustion efficiency of the combustion chamber, and reduce production cost.

Brief description of the drawing

DRAWINGS

1 is a top plan view of a combustion chamber along a transverse cross section according to an embodiment of the present invention.

2 is a schematic structural view of an outer wall and an inner wall of a flame tube of the combustion chamber of FIG. 1.

3 is a side view of the nozzle of the combustion chamber of FIG. 1.

4 is a longitudinal cross-sectional view of the nozzle of FIG. 3.

5 is a top plan view of a combustion chamber along a transverse cross section according to another embodiment of the present invention. 6 is a schematic structural view of the outer wall of the flame tube of the combustion chamber of FIG. 5.

7 is a schematic structural view of an outer wall and an inner wall of a flame tube of the combustion chamber of FIG. 5.

8 is a bottom plan view of the combustion chamber of FIG. 5 along a transverse cross section. [0028] FIG.

9 is a longitudinal cross-sectional view of the hollow body structure of the combustion chamber of FIG. 5.

10 is a simplified schematic view showing the formation of a square corner in a gas flow and an air flow in a combustion chamber according to another embodiment of the present invention.

11 is a schematic structural view of another embodiment of the nozzle structure in the above embodiment.

12 is an enlarged schematic view showing a partial structure of the nozzle of FIG. 11.

13 is a top plan view of the nozzle structure of FIG. 11.

Embodiments of the invention

[0034] Before the embodiments are described in detail, it is understood that the invention is not limited to The invention may be embodied in other ways. Further, it should be understood that the phraseology and terminology used herein are for the purpose of description The words "including", "comprising", "having", and the like, are used in this context to include the items listed thereafter, their equivalents, and other additional items. In particular, when describing "a certain component", the present invention does not limit the number of the components to one, and may include a plurality.

[0035] As shown in FIGS. 1 and 2, the present invention provides a gas turbine combustor, the combustion chamber including an annular flame cylinder 10 and a plurality of nozzles 12, the annular flame cylinder 10 forming an annular combustion chamber 14, and a plurality of nozzles 12 are disposed at Within the annular combustion chamber 14, a plurality of nozzles 12 are used to inject a mixture of gas and air mixed into the annular combustion chamber 14. More specifically, in the illustrated embodiment, the annular flame tube 10 includes an outer ring flame tube 16 and an inner ring flame tube 18 having a radially spaced, combustion chamber 14 formed in the inner ring flame tube 18 and the outer ring flame tube 16 between.

The annular combustion chamber 14 defines an axial direction and a circumferential direction around the axial direction, and a plurality of nozzles 12 are fixed to the end walls of the flame cylinder 10, arranged in the circumferential direction and extending in the axial direction. Preferably, a plurality of nozzles 12 are evenly arranged in the circumferential direction.

As shown in FIGS. 3 and 4, the nozzle 12 includes a main nozzle 20 and a nozzle outer wall 22 disposed around the main nozzle 20. The main nozzle 20 forms an internal gas passage 24 and a gas outlet 26 in fluid communication with the internal gas passage 24. An air passage 28 is formed between the nozzle outer wall 22 and the main nozzle 20, and the gas outlet 26 is in fluid phase with the air passage 28. The nozzle outer wall 22 is provided with at least one mixed gas outlet 30 in fluid communication with the air passage 28 such that the gas discharged from the gas outlet 26 is mixed with the air in the air passage 28 and then ejected from the mixed gas outlet 30.

Specifically, the main nozzle 20 includes a main nozzle cylindrical portion 32 and a main nozzle end portion 34 at the end of the main nozzle cylindrical portion 32, wherein the main nozzle cylindrical portion 32 defines an internal gas passage 24, and the internal gas passage 24 Extending along the axial direction, the gas inlet end of the main nozzle barrel 32 communicates with an external gas delivery conduit to receive foreign gas. The main nozzle end 34 is a closed end such that the gas within the gas passage 24 can only be ejected from the gas outlet 26.

[0039] In the illustrated embodiment, the gas outlet 26 is disposed through the main nozzle barrel 32, the number of gas outlets 26 is two, and the two gas outlets 26 are respectively disposed toward the adjacent nozzles, and a gas outlet is provided. The position of 26 is near the main nozzle end 34, the closed end.

[0040] The nozzle outer wall 22 includes a nozzle outer wall cylindrical portion 36 and a nozzle outer wall end portion 38 at the end of the nozzle outer wall cylindrical portion 36, and the nozzle outer wall cylindrical portion 36 surrounds the main nozzle 20 and is radially spaced from the main nozzle 20, thereby An air passage 28 is formed between the main nozzle 20 and the outer nozzle wall 22, and the air passage 28 is in fluid communication with the gas outlet 26. In the illustrated embodiment, the nozzle outer wall end 38 is spaced from the main nozzle end 34 in the axial direction, and therefore, the air passage 28 also includes a gap formed between the nozzle outer wall end 38 and the main nozzle end 34. space.

[0041] Each of the nozzles 12 is provided with at least one mixed gas outlet 30, that is, at least one mixed gas outlet 30 that is in fluid communication with the air passage 28 is formed on the nozzle outer wall cylindrical portion 36. Specifically, the mixed gas outlet 30 penetrates the nozzle outer wall cylindrical portion 36 and corresponds to the gas outlet 26 in the radial direction so that the gas discharged from the gas outlet 26 is mixed with the air in the air passage 28 and then sprayed from the mixed gas outlet 30. Out.

[0042] In the illustrated embodiment, the number of the mixed gas outlets 30 formed on the nozzle outer wall cylindrical portion 36 is two, and the two mixed gas outlets 30 respectively correspond to the two gas outlets 26 in the radial direction, The gas ejected from the two gas outlets 26 is mixed with the air in the air passage 28 and then ejected from the two mixed gas outlets 30, respectively.

[0043] Each mixed gas outlet 30 defines a mixed gas injection direction. In the illustrated embodiment, each nozzle 12 is provided with two gas outlets 26 and two mixed gas outlets 30, two gas outlets 26 and two, respectively. The mixed gas outlets 30 correspond in the radial direction, and the mixed gas injection directions defined by the two mixed gas outlets 30 are opposite. In this embodiment, the mixed gas injection direction is substantially along the circumferential direction. Specifically, the mixed gas injection direction is a direction toward an adjacent nozzle 12, and therefore, the two mixed gas outlets 30 of each nozzle 12 The mixed gas injection directions are respectively directed toward the directions of the two nozzles adjacent to the nozzle 12.

[0044] In the illustrated embodiment, the nozzle outer wall end 38 is provided with an end through bore 40 that is in fluid communication with the air passage 28 and the annular combustion chamber 14, and thus, within the air passage 28. Air can flow from the end through bores 40 into the annular combustion chamber 14 to form an integral flow of air within the air passages 28 for cooling the wall faces 36 and ends 38.

[0045] In the illustrated embodiment, the gas outlet 26 and the mixed gas outlet 30 formed by the nozzle 12 are both disposed in a circular shape, and the gas outlet 26 has a smaller pore diameter than the mixed gas outlet 30, such that the gas is formed by the gas outlet 26. The jet can form a jet of air through the mixed gas outlet 30, promoting the mixing of the gas and the air through the mixed gas outlet 30, thereby promoting combustion and shortening the length of the flame.

[0046] As described above, the injection direction of the mixture injected from the mixed gas outlet 30 is toward the direction of an adjacent nozzle 12, and when the flame pressure is large, the mixture injected from the mixed gas outlet 30 is either The flame generated by the mixed gas may be directly sprayed onto the adjacent nozzles 12, which causes a large damage to the nozzles 12, so that the nozzles 12 are easily damaged. In order to avoid this, in order to solve the above problem more steadily, the present invention further improves the combustion chamber and proposes two embodiments.

[0047] Embodiment 1:

[0048] As shown in FIGS. 5-9, the combustion chamber further includes a plurality of flame blocking structures for preventing the flame generated by the mixed gas or the mixed gas from being directly injected onto the adjacent nozzles 12, specifically, each of the two A flame blocking structure is disposed between adjacent nozzles 12.

[0049] As described above, each of the nozzles 12 is provided with two mixed gas outlets 30, and the mixed gas outlets defined by the two mixed gas outlets 30 are sprayed in opposite directions. Referring to FIG. 5, the mixed gas injection direction of the opposite two mixed gas outlets 30 of any two adjacent nozzles 12 has an intersection point, and the flame blocking structure is disposed at the intersection to block the mixture injected by the mixed gas outlet 30. The flame produced.

[0050] The flame blocking structure comprises a hollow body 42. The hollow body 42 has a hollow body wall portion 44 and an internal cavity 46 formed by the hollow body wall portion 44. The hollow body 42 is disposed along the axial direction, and an axial end of the hollow body 42 is fixed to the flame cylinder 10, specifically to the end wall of the flame cylinder 10 to which the nozzle 12 is fixed. The axial end of the hollow body 42 is a tongue-and-groove structure for communicating with outside air for receiving cooling air outside the flame tube 10, thereby allowing the cooling air to fill the internal cavity 46.

[0051] As shown in FIG. 9, the other axial end portion 48 of the hollow body 42 and the hollow body wall portion 44 are each provided with a fluid with the internal cavity 46. A number of through holes that communicate. With this porous structure, air from the interior cavity 46 of the hollow body 42 can pass through the hollow body wall portion 44 and the axial end portion 48 to protect the flame barrier structure from burning. The air of the internal cavity 46 can also enter the annular combustion chamber 14 through the hollow body wall portion 44 and the through hole in the axial end portion 48 to allow the combustion of the gas within the annular combustion chamber 14 to be more sufficient.

[0052] The hollow body 42 has a blocking surface facing the adjacent nozzles 12, which is a surface where the flame contacts the hollow body 42, and a nozzle 12 is disposed on each side of each hollow body 42 along the circumferential direction. Thus, each hollow body 42 has two blocking faces. When the flame of one of the nozzles 12 is ejected toward the other adjacent nozzle, the flame is ejected onto the blocking surface of the hollow body 42 to be blocked. Since the hollow body wall portion 44 is of a porous structure, the cooling air of the hollow body inner cavity 46 can pass through the through holes of the hollow body wall portion 44 and the axial end portion 48 to form a barrier film on the blocking surface and the outer surface of the end portion. The protective hollow body 42 is not burned. In the present embodiment, the blocking surface is designed as a curved surface, for example, the hollow body 42 is designed as a hollow cylinder 42. In other embodiments, the hollow body 42 may have other shapes, such as an elliptical cylinder, a rectangular parallelepiped, a polyhedron, etc., as long as it can block the flame of one of the nozzles without being sprayed to an adjacent nozzle.

[0053] With continued reference to FIG. 5, each nozzle 12 has two mixed gas outlets 30, each of which outputs a mixture of gas toward a corresponding adjacent hollow body 42, each of which has a centerline. The hollow cylinder 42 has a center line parallel to the axial direction, and a center line of each mixed gas outlet 30 passes through a center line of the hollow body 42 corresponding to the mixed gas outlet 30, that is, each hollow body The center line of 42 is located in the mixed gas injection direction of the opposite two mixed gas outlets 30 of the adjacent two nozzles 12, that is, at the intersection of their center lines.

Referring to FIG. 8, in a radial section, the centers of all the hollow bodies 42 are located on the same circle as the centers of all the nozzles 12. Of course, in other embodiments, the hollow body 42 and the nozzle 12 may be disposed in other directions in the circumferential direction, not necessarily on the same circle.

[0055] Embodiment 2:

[0056] As shown in FIG. 10, a part of the structure of the annular flame tube 10 is illustrated, including an outer ring flame tube 16, an inner ring flame tube 18, and a combustion chamber formed between the inner ring flame tube 18 and the outer ring flame tube 16. 14 and a plurality of nozzles disposed in the combustion chamber 14. Each nozzle is provided with a first mixed gas outlet and a second mixed gas outlet, each mixed gas outlet defining a spray direction. The configuration of the annular flame tube 10 and the nozzle 12 described above may be the same as that of the foregoing embodiment, and thus will not be described herein. [0057] The following description will be given in detail by taking any two adjacent nozzles as an example.

[0058] The two adjacent nozzles include a first nozzle 12a and a second nozzle 12b, the first nozzle 12a includes a first mixed gas outlet 50 and a second mixed gas outlet 52, and the second nozzle 12b includes a first mixing Air outlet 54 and second mixed gas outlet 56. The first mixed gas outlet 50 of the first nozzle 12a is located on the side facing the second nozzle 12b, and the second mixed gas outlet 56 of the second nozzle 12b is located on the side facing the first nozzle 12a.

[0059] The outer ring flame tube 16 is provided with a first air flow injection structure 62 for injecting a first air flow 66 toward the inner ring flame tube 18, the first air flow 66 defining a first Air flow direction. The inner ring flame tube 18 is provided with a second air flow injection structure 64 for injecting a second air flow 68 towards the outer ring flame tube 16, the second air flow 68 defining a second air flow direction .

[0060] In a radial section, the first mixture outlet 50 of the first nozzle 12a defines a first injection direction 58 that faces one of the inner ring flame tube 18 and the outer ring flame tube 16 The line L between the centers of the first nozzle 12a and the second nozzle 12b is deviated. The second mixture outlet 56 of the second nozzle 12b defines a second injection direction 60 that faces the inner ring flame tube 18 and the outer ring flame tube 16 with the other side offset from the first nozzle 12a and the second nozzle 12b The line between the centers of L.

[0061] It should be understood that the injection direction of the first air flow 66 is the first air flow direction, the injection direction of the second air flow 68 is the second air flow direction, and the mixed air flow or flame along the first nozzle 12a. The direction in which the first mixed gas outlet 50 is ejected is the first injection direction 58, and the direction in which the mixed gas stream or flame is ejected along the second mixed gas outlet 56 of the second nozzle 12b is the second injection direction 60.

[0062] The first mixed gas outlet 50 of the first nozzle 12a, the second mixed gas outlet 56 of the second nozzle 12b, the first air flow injection structure 62, and the second air flow injection structure 64 are arranged in a square corner. In other words, the mixed gas stream or flame ejected in the first injection direction 58, the mixed gas stream or flame ejected in the second injection direction 60, the first air stream 66 and the second air stream 68 are rounded at four corners.

[0063] In the embodiment shown in FIG. 10, the first injection direction 58 is offset from the outer ring flame cylinder 16 by a line L between the centers of the first nozzle 12a and the second nozzle 12b, the first injection direction 58. The angle L of the line L deviating from the center of the first nozzle 12a and the second nozzle 12b is 1° -

15°. The second injection direction 60 is offset from the inner circle flame tube 18 by a line L between the centers of the first nozzle 12a and the second nozzle 12b, and the second injection direction 60 is offset between the centers of the first nozzle 12a and the second nozzle 12b. The angle of the line L is 1° - 15°. [0064] It should be understood that in other embodiments, the first injection direction 58 may also be offset from the inner circle flame tube 18 by a line L between the centers of the first nozzle 12a and the second nozzle 12b, depending on design requirements. The second injection direction 60 may also be offset from the outer ring flame tube 16 by a line L between the centers of the first nozzle 12a and the second nozzle 12b as long as the mixed gas flow or flame ejected in the first injection direction 58 can be caused. The mixed airflow or flame sprayed in the two injection directions 60, and the airflow formed by the first airflow 66 and the second airflow 68 are rounded at four corners, which is not limited by the present invention.

[0065] In the illustrated embodiment, the first air flow injection structure 62 is one or more first air holes 62 provided on the outer ring flame tube 16, and the high pressure air outside the flame tube passes through the first air hole 62. The first air stream 66 is injected into the combustion chamber 14 toward the inner ring flame. Similarly, the second air flow injection structure 64 is one or more second air holes 64 disposed on the inner ring flame tube 18. The high pressure air outside the flame tube passes through the second air hole 64 toward the outer circumference of the combustion chamber 14. The flame tube ejects the second air stream 68. In addition, the inner ring flame tube 18 and the outer ring flame tube 16 are provided with a plurality of through cooling holes, so that the outside air can enter the combustion chamber through the cooling holes to form a gas film on the wall surface of the flame tube to block the high temperature flame.

In this embodiment, the apertures of the first air hole 62 and the second air hole 64 are larger than the aperture of the cooling hole, and the specific values thereof are designed according to the aerodynamic parameters.

[0067] The specific operating principle of the tangential circle is: the first flame ejected in the first injection direction 58 of the first nozzle 12a of the first nozzle 12a is ejected from the first airflow injection structure 62. The first air flow 6 6 intersects, the first air flow 66 can change the direction of travel of the first flame to the first air flow direction, since the first flame itself has a certain momentum in the first injection direction 58, thus two strands The airflows intersect and follow an arcuate path. The second flame ejected in the second injection direction 60 of the second mixture outlet 56 of the second nozzle 12b intersects the second air stream 68 ejected from the second airflow injection structure 64, and the second air stream 68 may The direction of travel of the second flame is changed to the direction of the second air flow. Since the second flame itself has a certain momentum of travel in the second injection direction 60, the two streams intersect and follow another arcuate path. The two curved paths are formed to form a four-corner circular path. Under the action of the first air flow 66 and the second air flow 68, the mixed air flow circulates along the four-corner circular path, and an intermediate position between adjacent nozzles is formed. The swirling flow effectively prevents the flame ejected from the mixed gas outlet from being directly sprayed onto the adjacent nozzle 12. At the same time, this swirl is equivalent to lengthening the length of the flame in a shorter axial space, thus making combustion more efficient, better emissions, and further reducing the axial size of the combustion chamber. The final gas turbine is also It can have a smaller axial dimension.

[0068] As shown in FIGS. 11-13, in order to enable more uniform mixing of the gas and air, a swirler 74 is disposed in the air passage 28 of the nozzle 12 to cause the air entering the air passage 28 to form a swirl. Increase the air flow intensity so that it can mix quickly and evenly with the gas to improve combustion efficiency and thus reduce nitrogen oxide emissions. In the illustrated embodiment, the swirler 74 includes a plurality of vanes 76 disposed on the outer peripheral surface of the main nozzle cylindrical portion 32, and the inner side of the vane 76 is fixedly coupled to the outer peripheral surface of the main nozzle cylindrical portion 32, the vane 76 The outer side is fixedly coupled to the inner peripheral surface of the nozzle outer wall cylindrical portion 36. In other undescribed embodiments, the blade may be fixedly coupled only to one of the outer circumferential surface of the main nozzle cylindrical portion and the inner circumferential surface of the nozzle outer wall.

[0069] It should be understood that the swirler 74 is implemented as an arcuate elongated blade 76 in this embodiment. In other embodiments, the swirler 74 can also be implemented in other configurations as long as it can be made in the air passage. The air forms a swirl.

[0070] In summary, the present invention provides a gas turbine combustor and a nozzle thereof, the nozzle includes a main nozzle and a nozzle outer wall disposed around the main nozzle, the main nozzle forms a gas passage, and the outer wall of the nozzle is radially spaced from the main nozzle to An air passage is formed between the two, a gas outlet is arranged on the main nozzle, and a mixed gas outlet corresponding to the gas outlet is arranged on the outer wall of the nozzle, so that the gas discharged from the gas outlet is mixed with the air in the air passage and then ejected from the mixed gas outlet. The injection direction of the mixed gas outlet of each nozzle faces the adjacent nozzle. The nozzle structure of the invention is ingeniously designed to better mix the gas and the air, and inject the mixed gas into the combustion chamber of the combustion chamber for combustion, thereby avoiding damage of the flame wall by the high temperature flame. Secondly, in some embodiments, a plurality of flame blocking structures are disposed in the combustion chamber, and a flame blocking structure is disposed between the adjacent two nozzles to prevent the flame sprayed from the nozzles from being directly sprayed onto the adjacent nozzles to cause damage thereto. Extend the life of the combustion chamber. Again, in some embodiments, the combustion chamber may also be provided with an air flow injection structure on the outer ring flame tube and the inner ring flame tube, the air flow injection structure being configured to be a mixture of the injected air flow and the opposite two nozzles. The flame ejected from the gas outlet forms a tangential circle, and the air flow can change the traveling direction of the jet flame, and then circulate along the four corners, effectively avoiding damage of the combustion chamber and the nozzle by the jet flame, and improving gas combustion in the combustion chamber. effectiveness. The gas turbine combustor of the invention has simple structure and novel concept, can minimize damage to various components of the combustion chamber, improve combustion efficiency of the combustion chamber, and reduce production cost. The concepts described herein may be embodied in other forms without departing from the spirit and scope. The specific embodiments disclosed are to be considered as illustrative and not restrictive. Therefore, the scope of the invention is to be determined by the appended claims Any changes which come within the meaning and range of the claims are intended to be within the scope of the claims.

Claims

Claim

[Claim 1] A nozzle of a gas turbine combustor, comprising a main nozzle, the main nozzle forming an internal gas passage and a gas outlet in fluid communication with the gas passage, wherein the nozzle further comprises:

a nozzle outer wall, the nozzle outer wall includes a nozzle outer wall cylindrical portion and a nozzle outer wall end portion at an end of the nozzle outer wall cylindrical portion, the nozzle outer wall cylindrical portion surrounding the main nozzle and radially opposite to the main nozzle Intervaling thereby forming an air passage between the main nozzle and the outer wall of the nozzle, the air passage being in fluid communication with the gas outlet, the nozzle outer wall cylindrical portion forming a mixed gas outlet in fluid communication with the air passage, such that The gas discharged from the gas outlet is mixed with the air in the air passage and then ejected from the mixed gas outlet.

[Claim 2] The nozzle of the gas turbine combustor according to claim 1, wherein the main nozzle includes a main nozzle cylindrical portion and a main nozzle end portion at an end of the main nozzle cylindrical portion, The main nozzle cylinder defines the internal gas passage, the gas outlet extends through the main nozzle cylinder, and the main nozzle end is a closed end, so that the gas in the gas passage can only be from the gas outlet ejection.

[Claim 3] The nozzle of the gas turbine combustor according to claim 2, wherein a position of the gas outlet is close to the closed end, and the gas outlet corresponds to the mixed gas outlet in a radial direction. The gas outlet has a smaller pore diameter than the mixed gas outlet, and the internal gas passage extends in the axial direction.

[Claim 4] The nozzle of the gas turbine combustor according to claim 2, wherein the nozzle outer wall end portion is provided with an end through hole and is axially spaced from the main nozzle end portion.

[Claim 5] The nozzle of a gas turbine combustor according to claim 1, wherein a swirler is formed in the air passage to form a swirling flow of air in the air passage.

[Claim 6] The nozzle of a gas turbine combustor according to claim 1, wherein the main nozzle includes a main nozzle cylindrical portion, and the cyclone includes a peripheral portion provided on the main nozzle cylindrical portion Several blades on the surface.

[Claim 7] The nozzle of the gas turbine combustor according to claim 1, wherein the number of the gas outlet and the mixed gas outlet are two and correspond to each other, and two mixed gas outlets are set The mixed mixture is sprayed in the opposite direction.

[Claim 8] A gas turbine combustor comprising:

An annular flame tube, the annular flame tube forming an annular combustion chamber, the annular combustion chamber defining an axial direction and a circumferential direction around the axial direction;

a plurality of nozzles disposed in the annular combustion chamber, the plurality of nozzles being evenly arranged along the circumferential direction, the nozzles for injecting a mixed gas mixed with gas and air into the combustion chamber;

The nozzle is provided with at least one mixed gas outlet, and the mixed gas outlet defines a mixed gas injection direction, and the mixed gas injection direction is toward an adjacent nozzle.

[Claim 9] The gas turbine combustor according to claim 8, wherein each of the nozzles is provided with two mixed gas outlets, and the mixed gas outlets defined by the two mixed gas outlets are sprayed in opposite directions.

[Claim 10] The gas turbine combustor of claim 9, wherein each nozzle comprises: a main nozzle, the main nozzle including a main nozzle barrel extending along the axial direction, the main nozzle The end of the cylindrical portion is closed, the main nozzle cylindrical portion has an internal gas passage and a gas outlet extending through the main nozzle cylindrical portion;

a nozzle outer wall, the nozzle outer wall includes a nozzle outer wall cylindrical portion, the nozzle outer wall cylindrical portion surrounds the main nozzle cylindrical portion and is radially spaced from the main nozzle cylindrical portion to be in the main nozzle cylindrical shape Forming an annular air passage between the portion and the outer wall of the nozzle, the mixed gas outlet penetrating through the cylindrical portion of the outer wall of the nozzle and radially corresponding to the gas outlet, so that the gas and the gas discharged from the gas outlet are The air in the air passage is mixed and ejected from the mixed gas outlet.