WO2018090384A1 - 燃气轮机燃烧室 - Google Patents

燃气轮机燃烧室 Download PDF

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Publication number
WO2018090384A1
WO2018090384A1 PCT/CN2016/106668 CN2016106668W WO2018090384A1 WO 2018090384 A1 WO2018090384 A1 WO 2018090384A1 CN 2016106668 W CN2016106668 W CN 2016106668W WO 2018090384 A1 WO2018090384 A1 WO 2018090384A1
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WO
WIPO (PCT)
Prior art keywords
nozzle
mixed gas
flame
hollow body
wall
Prior art date
Application number
PCT/CN2016/106668
Other languages
English (en)
French (fr)
Inventor
王志强
杨瑞
曹晶
王俊
Original Assignee
深圳智慧能源技术有限公司
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Filing date
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Application filed by 深圳智慧能源技术有限公司 filed Critical 深圳智慧能源技术有限公司
Priority to PCT/CN2016/106668 priority Critical patent/WO2018090384A1/zh
Publication of WO2018090384A1 publication Critical patent/WO2018090384A1/zh

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Definitions

  • the present invention relates to gas turbines, and more particularly to a gas turbine combustor.
  • 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.
  • the present invention proposes a gas turbine combustor to solve at least one of the problems set forth above.
  • the present invention provides a gas turbine combustor comprising: an 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 for injecting a mixture toward an adjacent nozzle, a flame blocking structure is disposed between each two adjacent nozzles for preventing a flame generated by the mixed gas from being directly injected into the phase Adjacent to the nozzle.
  • two nozzle outlets are provided for each nozzle, and the mixed gas injection directions defined by the two mixture outlets are opposite.
  • the flame blocking structure includes a hollow body having an internal cavity, and a wall portion of the hollow body is provided with a plurality of through holes in fluid communication with the internal cavity. An axial end of the hollow body is fixed to the flame tube for receiving cooling air outside the flame tube such that the cooling air fills the internal cavity.
  • the other axial end of the hollow body is provided with a plurality of through holes that are in fluid communication with the internal cavity.
  • the hollow body has a blocking surface facing an adjacent nozzle, and the blocking surface is a curved surface.
  • the hollow body is a hollow cylinder or an elliptical cylinder, and the cylinder or elliptical cylinder has a center line parallel to the axial direction.
  • the center of the hollow body and the center of the nozzle are on the same circle.
  • each nozzle includes: a main nozzle, the main nozzle includes a main nozzle cylindrical portion extending along the axial direction, and a tip end of the main nozzle cylindrical portion is a closed end, the main The 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, and the nozzle outer wall cylindrical portion surrounds the main nozzle cylindrical portion And an annular air passage is formed between the main nozzle cylindrical portion and the nozzle outer wall cylindrical portion in a radial direction from the main nozzle cylindrical portion, the mixed gas outlet penetrating through the nozzle outer wall cylindrical portion and Radially corresponding to the gas outlet, 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.
  • each nozzle has two mixed gas outlets, each mixed gas outlet spraying a mixture toward a corresponding adjacent flame blocking structure, each mixed gas outlet having a centerline, each flame
  • the barrier structure includes a hollow body having a centerline parallel to the axial direction, and a centerline of each of the mixed gas outlets passes through a centerline of the hollow body corresponding to the mixed gas outlet.
  • the outer wall of the nozzle has an end portion of the outer wall of the nozzle, and the end portion of the outer wall of the nozzle is provided with an end portion.
  • the through hole is axially spaced apart from the closed end of the main nozzle barrel.
  • 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.
  • a plurality of flame blocking structures are arranged in the combustion chamber, and a flame blocking structure is arranged between the adjacent two nozzles to prevent the flame sprayed from the nozzles from being directly sprayed onto the adjacent nozzles to damage them and prolong the service life of the combustion chamber.
  • the gas turbine combustor of the invention has simple structure and novel concept, can minimize damage to components of the combustion chamber, improve combustion efficiency of the combustion chamber, and reduce production cost.
  • FIG. 1 is a top plan view of a combustion chamber along a transverse cross section according to an embodiment of the present invention.
  • FIG. 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.
  • FIG. 3 is a side view of the nozzle of the combustion chamber of FIG. 1.
  • FIG. 4 is a longitudinal cross-sectional view of the nozzle of FIG. 3.
  • FIG. 5 is a top plan view of a combustion chamber along a transverse cross section according to another embodiment of the present invention.
  • FIG. 6 is a schematic structural view of the outer wall of the flame tube of the combustion chamber of FIG. 5.
  • FIG. 7 is a schematic structural view of the outer wall and the inner wall of the flame tube of the combustion chamber of FIG. 5.
  • FIG. 8 is a bottom plan view of the combustion chamber of FIG. 5 along a transverse cross section.
  • FIG. 9 is a longitudinal cross-sectional view of the hollow body structure of the combustion chamber of FIG. 5.
  • Figure 10 is a simplified schematic diagram showing the formation of a quarter-circle of a gas stream and an air stream of a combustion chamber in accordance with another embodiment of the present invention.
  • FIG. 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.
  • FIG. 13 is a top plan view of the nozzle structure of FIG. 11.
  • the present invention provides a gas turbine combustor, the combustor 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.
  • 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 tube 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.
  • the nozzle 12 includes a main nozzle 20 and a nozzle outer wall 22 disposed around the main nozzle 20, the main nozzle 20 forming 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 communication 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, so that the gas outlet 26 is provided. The discharged gas is mixed with the air in the air passage 28 and then ejected from the mixed gas outlet 30.
  • 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 in the gas passage 24 can only be from the gas outlet 2
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • Each mixed gas outlet 30 defines a mixed gas injection direction.
  • 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.
  • the mixed gas injection direction is substantially along the circumferential direction.
  • the mixed gas injection direction is a direction toward an adjacent nozzle 12, and therefore, the mixed gas injection directions of the two mixed gas outlets 30 of each nozzle 12 are respectively directed to two nozzles adjacent to the nozzle 12. The direction.
  • 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.
  • 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 formed by the gas outlet 26 Shoot The flow 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.
  • 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.
  • the present invention further improves the combustion chamber and proposes two embodiments.
  • Embodiment 1 is a diagrammatic representation of Embodiment 1:
  • the combustion chamber further includes a plurality of flame blocking structures for preventing the flame generated by the mixed gas or the mixture from being directly injected onto the adjacent nozzles 12, specifically, each of the two A flame blocking structure is disposed between adjacent nozzles 12.
  • 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.
  • 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.
  • 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.
  • the other axial end portion 48 of the hollow body 42 and the hollow body wall portion 44 are each provided with a plurality of through holes in fluid communication with the internal cavity 46.
  • the air of the inner 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 blocking structure from being burnt.
  • 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, so that the combustion of the gas in the annular combustion chamber 14 is more sufficient.
  • 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 both sides of each hollow body 42 along the circumferential direction.
  • each hollow body 42 has two blocking faces.
  • the flame of one of the nozzles 12 is sprayed toward the other adjacent nozzle, Its flame is sprayed onto the blocking surface of the hollow body 42 to be blocked.
  • 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.
  • the blocking surface is designed as a curved surface
  • the hollow body 42 is designed as a hollow cylinder 42.
  • the hollow body 42 may have other shapes, such as elliptical cylinders, cuboids, polyhedrons, etc., as long as the flame of one of the nozzles is blocked from being sprayed to an adjacent nozzle.
  • 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.
  • the centers of all the hollow bodies 42 are located on the same circle as the centers of all the nozzles 12.
  • the hollow body 42 and the nozzle 12 may be disposed in other directions in the circumferential direction, not necessarily on the same circle.
  • Embodiment 2 is a diagrammatic representation of Embodiment 1
  • annular flame tube 10 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 therefore will not be described herein.
  • 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.
  • 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.
  • Inner ring The 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.
  • 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.
  • 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
  • the mixed air flow or flame along the first nozzle 12a is the first injection direction 58
  • 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.
  • 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.
  • 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.
  • 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° -
  • 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°.
  • 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.
  • the first airflow spray structure 62 is one or more provided on the outer ring flame tube 16.
  • the first air holes 62 through which the high pressure air outside the flame tube is injected into the combustion chamber 14 toward the inner ring flame tube.
  • 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.
  • 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 14 through the cooling holes to form a gas film on the wall surface of the flame tube to block the high temperature flame.
  • 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.
  • 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.
  • 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.
  • 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.
  • the leaves The sheet may be fixedly connected only to one of the outer circumferential surface of the main nozzle cylindrical portion and the inner circumferential surface of the nozzle outer wall.
  • 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.
  • the present invention provides a gas turbine combustor and a nozzle thereof.
  • the nozzle includes a main nozzle and an outer wall of the nozzle 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.
  • 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.
  • 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 combustion chamber 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.

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Abstract

一种燃气轮机燃烧室，包括环形火焰筒(10)，环形火焰筒(10)形成环形燃烧腔(14)，环形燃烧腔(14)定义一轴向和围绕轴向的圆周方向；以及设置在环形燃烧腔(14)内的若干喷嘴(12)，若干喷嘴(12)沿圆周方向均匀排列，喷嘴(12)用于将混合有燃气和空气的混合气喷入燃烧腔(14)。每个喷嘴(12)设有至少一个用于朝向一相邻的喷嘴(12)喷射混合气的混合气出口(30)，每两个相邻的喷嘴（12）之间设置一个火焰阻挡结构，用于阻止混合气产生的火焰直接喷射到相邻的喷嘴(12)上。该燃气轮机燃烧室结构简单，可最大程度降低对燃烧室各元件的损坏，提高燃烧室的燃烧效率。

Description

燃气轮机燃烧室
技术领域
[0001] 本发明涉及燃气轮机， 特别是涉及一种燃气轮机燃烧室。
背景技术
[0002] 燃气轮机燃烧室中， 燃料气和空气通过喷嘴实现预混合和速度型的改变， 在喷 嘴出口达到合理的速度分布， 并匹配合理的燃料空气混合比例， 进入燃烧室进 行燃烧， 形成稳定的流场和燃烧场。 然而， 现有的燃气轮机燃烧室喷嘴存在燃 气和空气在预混通道混合不均匀的问题， 这样容易导致燃烧不稳定， 产生较多 污染排放物， 预混通道有可能会发生回火， 对喷嘴以及安装在预混通道内贵重 的旋流器等元件造成烧蚀和毁坏。
[0003] 燃气轮机燃烧室内的喷嘴在喷射火焰至燃烧腔内的过程中， 有可能会因为喷嘴 内的压力过高， 造成喷嘴喷射出来的火焰会直接喷射到火焰筒内壁或内设元器 件上， 甚至是直接喷射到相邻的喷嘴上， 对其造成严重的烧蚀和损毁， 大大降 低燃气轮机燃烧室及其喷嘴的使用寿命。
[0004] 因此， 急需一种合理有效的燃气轮机燃烧室结构及喷嘴结构来解决上述提出的 至少一种问题。
技术问题
[0005] 有鉴于此， 本发明提出一种燃气轮机燃烧室以解决上述提出的至少一种问题。
问题的解决方案
技术解决方案
[0006] 本发明提出一种燃气轮机燃烧室， 包括： 环形火焰筒， 所述环形火焰筒形成环 形燃烧腔， 所述环形燃烧腔定义一轴向和围绕所述轴向的圆周方向； 以及设置 在所述环形燃烧腔内的若干喷嘴， 所述若干喷嘴沿所述圆周方向均匀排列， 所 述喷嘴用于将混合有燃气和空气的混合气喷入所述燃烧腔； 每个喷嘴设有至少 一个用于朝向一相邻的喷嘴喷射混合气的的混合气出口， 每两个相邻的喷嘴之 间设置一个火焰阻挡结构， 用于阻止所述混合气产生的火焰直接喷射到所述相 邻的喷嘴上。
[0007] 在一实施例中， 每个喷嘴设置两个混合气出口， 且所述两个混合气出口定义的 混合气喷射方向相反。
[0008] 在一实施例中， 所述火焰阻挡结构包括空心体， 所述空心体具有内部空腔， 所 述空心体的壁部设有与所述内部空腔流体相通的若干通孔， 所述空心体的一轴 向端部固定在所述火焰筒上， 用于接收所述火焰筒外部的冷却空气使得所述冷 却空气充满所述内部空腔。
[0009] 在一实施例中， 所述空心体的另一轴向端部设有与所述内部空腔流体相通的若 干通孔。
[0010] 在一实施例中， 所述空心体具有一面向一相邻的喷嘴的阻挡面， 所述阻挡面为 弧形面。
[0011] 在一实施例中， 所述空心体为一空心圆柱体或椭圆柱体， 所述圆柱体或椭圆柱 体具有平行于所述轴向的中心线。
[0012] 在一实施例中， 在一径向截面中， 所述空心体的中心和所述喷嘴的中心位于同 一个圆上。
[0013] 在一实施例中， 每个喷嘴包括： 主喷嘴， 所述主喷嘴包括沿所述轴向延伸的主 喷嘴筒状部， 所述主喷嘴筒状部末端为封闭端， 所述主喷嘴筒状部具有一内部 燃气通道以及贯穿所述主喷嘴筒状部的燃气出口； 喷嘴外壁， 所述喷嘴外壁包 括喷嘴外壁筒状部， 所述喷嘴外壁筒状部环绕所述主喷嘴筒状部且与所述主喷 嘴筒状部在径向上间隔从而在所述主喷嘴筒状部和喷嘴外壁筒状部之间形成环 形空气通道， 所述混合气出口贯穿所述喷嘴外壁筒状部且与所述燃气出口在径 向上对应， 使得从所述燃气出口喷出的燃气与所述空气通道内的空气混合后从 所述混合气出口喷出。
[0014] 在一实施例中， 每个喷嘴具有两个混合气出口， 每个混合气出口朝向一对应的 相邻火焰阻挡结构喷射混合气， 每个混合气出口具有一中心线， 每个火焰阻挡 结构包括一空心体， 所述空心体具有一与所述轴向平行的中心线， 每个混合气 出口的中心线穿过与该混合气出口对应的空心体的中心线。
[0015] 在一实施例中， 所述喷嘴外壁具有喷嘴外壁端部， 所述喷嘴外壁端部设有端部 通孔并与所述主喷嘴筒状部的封闭端在轴向上间隔幵。
发明的有益效果
有益效果
[0016] 综上所述， 本发明提供了一种燃气轮机燃烧室及其喷嘴， 喷嘴包括主喷嘴及环 绕主喷嘴设置的喷嘴外壁， 主喷嘴形成燃气通道， 喷嘴外壁与主喷嘴在径向上 间隔以在二者之间形成空气通道， 主喷嘴上设置燃气出口， 喷嘴外壁上设置与 燃气出口对应的混合气出口， 使得燃气出口喷出的燃气与空气通道内的空气混 合后从混合气出口喷出， 每个喷嘴的混合气出口的喷射方向朝向相邻喷嘴。 本 发明的喷嘴结构设计巧妙， 能更好地混合燃气和空气， 并将混合气喷射入燃烧 室的燃烧腔内进行燃烧， 避免了高温火焰对火焰筒壁的损害。 其次， 燃烧室内 还设置若干火焰阻挡结构， 火焰阻挡结构设置在相邻两喷嘴之间， 以阻止从喷 嘴喷射出的火焰直接喷射到相邻的喷嘴上对其产生损坏， 延长燃烧室的使用寿 命。 本发明的燃气轮机燃烧室结构简单， 构思新颖， 可最大程度降低对燃烧室 各元件的损坏， 提高燃烧室的燃烧效率， 降低生产成本。
对附图的简要说明
附图说明
[0017] 图 1是本发明一实施例的燃烧室沿一横向截面的俯视示意图。
[0018] 图 2是图 1中燃烧室的火焰筒外壁和内壁的结构示意图。
[0019] 图 3是图 1中燃烧室的喷嘴的侧视图。
[0020] 图 4是图 3中喷嘴的纵向剖视图。
[0021] 图 5是本发明另一实施例的燃烧室沿一横向截面的俯视示意图。
[0022] 图 6是图 5中燃烧室的火焰筒外壁的结构示意图。
[0023] 图 7是图 5中燃烧室的火焰筒外壁和内壁的结构示意图。
[0024] 图 8是图 5中燃烧室沿一横向截面的仰视示意图。
[0025] 图 9是图 5中燃烧室的空心体结构的纵向剖视图。
[0026] 图 10是本发明另一实施例的燃烧室的燃气气流和空气气流形成四角切圆的简化 示意图。
[0027] 图 11是上述实施例中喷嘴结构的另一实施例的结构示意图。 [0028] 图 12是图 11中喷嘴的部分结构的放大示意图。
[0029] 图 13是图 11中喷嘴结构的俯视示意图。
本发明的实施方式
[0030] 在详细描述实施例之前， 应该理解的是， 本发明不限于本申请中下文或附图中 所描述的详细结构或元件排布。 本发明可为其它方式实现的实施例。 而且， 应 当理解， 本文所使用的措辞及术语仅仅用作描述用途， 不应作限定性解释。 本 文所使用的"包括"、 "包含"、 "具有"等类似措辞意为包含其后所列出之事项、 其 等同物及其它附加事项。 特别是， 当描述 "一个某元件 "吋， 本发明并不限定该元 件的数量为一个， 也可以包括多个。
[0031] 如图 1和图 2所示， 本发明提供一种燃气轮机燃烧室， 所述燃烧室包括环形火焰 筒 10和若干喷嘴 12， 环形火焰筒 10形成环形燃烧腔 14， 若干喷嘴 12设置在环形 燃烧腔 14内， 若干喷嘴 12用于将混合有燃气和空气的混合气喷入环形燃烧腔 14 内。 更具体地， 在所示的实施例中， 环形火焰筒 10包括具有径向间隔的外圈火 焰筒 16和内圈火焰筒 18， 燃烧腔 14形成于内圈火焰筒 18与外圈火焰筒 16之间。
[0032] 环形燃烧腔 14定义一轴向和围绕所述轴向的圆周方向， 若干喷嘴 12固定在火焰 筒 10的端壁上， 沿所述圆周方向排列且沿所述轴向延伸。 优选的是， 若干喷嘴 1 2沿所述圆周方向均匀排列。
[0033] 如图 3和图 4所示， 喷嘴 12包括主喷嘴 20及围绕主喷嘴 20设置的喷嘴外壁 22， 主 喷嘴 20形成一内部燃气通道 24以及与内部燃气通道 24流体相通的燃气出口 26， 喷嘴外壁 22与主喷嘴 20之间形成空气通道 28， 燃气出口 26与空气通道 28流体相 通， 喷嘴外壁 22上设置与空气通道 28流体相通的至少一混合气出口 30， 以使得 从燃气出口 26喷出的燃气与空气通道 28内的空气混合后从混合气出口 30喷出。
[0034] 具体而言， 主喷嘴 20包括主喷嘴筒状部 32以及位于主喷嘴筒状部 32末端的主喷 嘴端部 34， 其中主喷嘴筒状部 32定义内部燃气通道 24， 内部燃气通道 24沿所述 轴向延伸， 主喷嘴筒状部 32的燃气入口端与外部燃气输送管道连通， 以接收外 来燃气。 主喷嘴端部 34为封闭端， 以使得燃气通道 24内的燃气只能从燃气出口 2 [0035] 在所示的实施例中， 燃气出口 26贯穿主喷嘴筒状部 32设置， 燃气出口 26的数量 为两个， 两个燃气出口 26分别朝向相邻喷嘴的方向设置， 且设置燃气出口 26的 位置靠近主喷嘴端部 34， 即所述封闭端。
[0036] 喷嘴外壁 22包括喷嘴外壁筒状部 36以及位于喷嘴外壁筒状部 36末端的喷嘴外壁 端部 38， 喷嘴外壁筒状部 36环绕主喷嘴 20且与主喷嘴 20在径向上间隔， 从而在 主喷嘴 20与喷嘴外壁 22之间形成空气通道 28， 空气通道 28与燃气出口 26流体相 通。 在所示的实施例中， 喷嘴外壁端部 38在所述轴向上与主喷嘴端部 34间隔幵 ， 因此， 空气通道 28也包括喷嘴外壁端部 38与主喷嘴端部 34之间形成的空间。
[0037] 每个喷嘴 12设有至少一个混合气出口 30， 也即在喷嘴外壁筒状部 36上形成与空 气通道 28流体相通的至少一混合气出口 30。 具体来说， 混合气出口 30贯穿喷嘴 外壁筒状部 36且与燃气出口 26在径向上对应， 以使得从燃气出口 26喷出的燃气 与空气通道 28内的空气混合后从混合气出口 30喷出。
[0038] 在所示的实施例中， 喷嘴外壁筒状部 36上形成的混合气出口 30的数量为两个， 而且两个混合气出口 30分别与两个燃气出口 26在径向上对应， 以使得从两个燃 气出口 26喷出的燃气与空气通道 28内的空气混合后分别从两个混合气出口 30喷 出。
[0039] 每一混合气出口 30定义一混合气喷射方向， 在所示的实施例中， 每个喷嘴 12设 置两个燃气出口 26和两个混合气出口 30， 两个燃气出口 26分别与两个混合气出 口 30在径向上对应， 且两个混合气出口 30定义的混合气喷射方向相反。 本实施 例中， 所述混合气喷射方向大致沿着所述圆周方向。 具体而言， 所述混合气喷 射方向为朝着一相邻喷嘴 12的方向， 因此， 每一喷嘴 12的两个混合气出口 30的 混合气喷射方向分别朝向与该喷嘴 12相邻的两喷嘴的方向。
[0040] 在所示的实施例中， 喷嘴外壁端部 38设有端部通孔 40， 端部通孔 40同吋与空气 通道 28和环形燃烧腔 14流体相通， 因此， 空气通道 28内的空气可从端部通孔 40 流向环形燃烧腔 14内， 以形成空气通道 28内空气的整体流动， 进行壁面 36及端 部 38的冷却。
[0041 ] 在所示的实施例中， 喷嘴 12形成的燃气出口 26和混合气出口 30均设置为圆形， 且燃气出口 26的孔径小于混合气出口 30的孔径， 这样燃气出口 26形成的燃气射 流可以在通过混合气出口 30吋形成弓 I射空气的作用， 促进通过混合气出口 30的 燃气与空气的混合， 进而促进燃烧及缩短火焰的长度。
[0042] 如上所述， 从混合气出口 30喷射出来的混合气的喷射方向为朝着一相邻喷嘴 12 的方向， 当火焰压力较大吋， 从混合气出口 30喷射出来的混合气或者是混合气 产生的火焰可能会直接喷射到相邻的喷嘴 12上， 这样会对喷嘴 12产生较大损害 ， 使得喷嘴 12容易损坏。 为了避免这种情况的发生， 为了更为稳妥地解决上述 问题， 本发明对燃烧室进行了进一步地改进， 并提出两种实施方案。
[0043] 实施方案一:
[0044] 如图 5-9所示， 所述燃烧室还包括用于阻止混合气或混合气产生的火焰直接喷 射到相邻的喷嘴 12上的若干火焰阻挡结构， 具体来说， 每两个相邻的喷嘴 12之 间设置一个火焰阻挡结构。
[0045] 如前所述， 每个喷嘴 12设置两个混合气出口 30， 且两个混合气出口 30定义的混 合气喷射方向相反。 请参考图 5， 任意相邻两喷嘴 12的相对的两混合气出口 30的 混合气喷射方向具有一交点， 所述火焰阻挡结构设置于所述交点处， 以阻挡混 合气出口 30喷射的混合气产生的火焰。
[0046] 所述火焰阻挡结构包括一空心体 42， 空心体 42具有空心体壁部 44以及由空心体 壁部 44形成的内部空腔 46。 空心体 42沿所述轴向方向设置， 空心体 42的一轴向 端部固定在火焰筒 10上， 具体来说是固定在火焰筒 10的固定有喷嘴 12的那一端 壁上。 空心体 42的该轴向端部为幵口结构， 以与外部空气连通， 用于接收火焰 筒 10外部的冷却空气， 进而使得冷却空气充满内部空腔 46。
[0047] 如图 9， 空心体 42的另一轴向端部 48和空心体壁部 44均设有与内部空腔 46流体 相通的若干通孔。 利用这种多孔结构， 空心体 42的内部空腔 46的空气可以通过 空心体壁部 44和轴向端部 48， 保护火焰阻挡结构不被烧毁。 同吋内部空腔 46的 空气还可通过空心体壁部 44和轴向端部 48上的通孔进入环形燃烧腔 14内， 以使 得环形燃烧腔 14内的燃气燃烧更加充分。
[0048] 空心体 42具有面向相邻的喷嘴 12的阻挡面， 所述阻挡面即为火焰与空心体 42接 触的表面， 沿所述圆周方向每一空心体 42的两侧均设置一喷嘴 12， 因此每一空 心体 42具有两个阻挡面。 当其中一喷嘴 12的火焰朝向另一相邻的喷嘴喷射吋， 其火焰喷射到空心体 42的阻挡面上而被阻挡。 由于空心体壁部 44为多孔结构， 空心体内部空腔 46的冷却空气可以穿过空心体壁部 44和轴向端部 48的通孔而在 阻挡面和端部外表面上形成阻隔气膜， 保护空心体 42不被烧毁。 在本实施例中 ， 所述阻挡面设计为弧形面， 例如， 将空心体 42设计为空心圆柱体 42。 在其他 实施例中， 空心体 42也可以具有其它形状， 例如椭圆柱体， 长方体， 多面体等 等， 只要能阻挡其中一喷嘴的火焰而不至于喷射到相邻的一喷嘴即可。
[0049] 请继续参考图 5， 每个喷嘴 12具有两个混合气出口 30， 每个混合气出口 30朝向 一对应的相邻空心体 42喷射混合气， 每个混合气出口 30具有一中心线， 空心圆 柱体 42具有平行于所述轴向的中心线， 每个混合气出口 30的中心线穿过与该混 合气出口 30对应的空心体 42的中心线， 也就是说， 每个空心体 42的中心线位于 相邻两喷嘴 12的相对的两混合气出口 30的混合气喷射方向， 也即其中心线的交 点上。
[0050] 请参考图 8， 在一径向截面中， 所有空心体 42的中心与所有喷嘴 12的中心位于 同一个圆上。 当然， 在其它实施例中， 空心体 42与喷嘴 12在圆周方向上也可以 按照别的方式设置， 不一定设置在同一个圆上。
[0051] 实施方案二:
[0052] 如图 10所示， 例示了环形火焰筒 10的一部分结构， 包括外圈火焰筒 16、 内圈火 焰筒 18、 形成于内圈火焰筒 18与外圈火焰筒 16之间的燃烧腔 14及设置在燃烧腔 1 4内的若干喷嘴。 每个喷嘴设有第一混合气出口和第二混合气出口， 每一混合气 出口定义一喷射方向。 上述环形火焰筒 10和喷嘴 12的构造可与前述实施例中的 构造相同， 因此在此不再赘述。
[0053] 下面以任意相邻的两个喷嘴为例进行详细说明。
[0054] 所述任意相邻的两个喷嘴包括第一喷嘴 12a和第二喷嘴 12b， 第一喷嘴 12a包括 第一混合气出口 50和第二混合气出口 52， 第二喷嘴 12b包括第一混合气出口 54和 第二混合气出口 56。 其中第一喷嘴 12a的第一混合气出口 50位于面向第二喷嘴 12b 的一侧， 第二喷嘴 12b的第二混合气出口 56位于面向第一喷嘴 12a的一侧。
[0055] 外圈火焰筒 16设有第一空气流喷射结构 62， 第一空气流喷射结构 62用于喷射朝 向内圈火焰筒 18的第一空气流 66， 第一空气流 66定义一第一空气流方向。 内圈 火焰筒 18设有第二空气流喷射结构 64， 第二空气流喷射结构 64用于喷射朝向外 圈火焰筒 16的第二空气流 68， 第二空气流 68定义一第二空气流方向。
[0056] 在一径向截面中， 第一喷嘴 12a的第一混合气出口 50定义一第一喷射方向 58， 第一喷射方向 58朝向内圈火焰筒 18和外圈火焰筒 16其中之一侧偏离第一喷嘴 12a 和第二喷嘴 12b的中心之间的连线 L。 第二喷嘴 12b的第二混合气出口 56定义一第 二喷射方向 60， 第二喷射方向 60朝向内圈火焰筒 18和外圈火焰筒 16其中另一侧 偏离第一喷嘴 12a和第二喷嘴 12b的中心之间的连线 L。
[0057] 应当理解的是， 上述第一空气流 66的喷射方向即为第一空气流方向， 第二空气 流 68的喷射方向即为第二空气流方向， 混合气流或火焰沿第一喷嘴 12a的第一混 合气出口 50喷出的方向即为第一喷射方向 58， 混合气流或火焰沿第二喷嘴 12b的 第二混合气出口 56喷出的方向即为第二喷射方向 60。
[0058] 第一喷嘴 12a的第一混合气出口 50、 第二喷嘴 12b的第二混合气出口 56、 第一空 气流喷射结构 62和第二空气流喷射结构 64呈四角切圆布置。 换句话说， 沿第一 喷射方向 58喷射的混合气流或火焰、 沿第二喷射方向 60喷射的混合气流或火焰 、 第一空气流 66和第二空气流 68合围呈四角切圆。
[0059] 在如图 10所示的实施例中， 第一喷射方向 58朝向外圈火焰筒 16偏离第一喷嘴 12 a和第二喷嘴 12b的中心之间的连线 L， 第一喷射方向 58偏离第一喷嘴 12a和第二 喷嘴 12b的圆心之间的连线 L的角度为 1°-
15°。 第二喷射方向 60朝向内圈火焰筒 18偏离第一喷嘴 12a和第二喷嘴 12b的圆心 之间的连线 L， 第二喷射方向 60偏离第一喷嘴 12a和第二喷嘴 12b的中心之间的连 线 L的角度为 1°- 15°。
[0060] 应当理解的是， 在其他实施例中， 根据设计需求， 第一喷射方向 58也可以朝向 内圈火焰筒 18偏离第一喷嘴 12a和第二喷嘴 12b的圆心之间的连线 L， 第二喷射方 向 60也可以朝向外圈火焰筒 16偏离第一喷嘴 12a和第二喷嘴 12b的圆心之间的连线 L， 只要能使得沿第一喷射方向 58喷射的混合气流或火焰、 沿第二喷射方向 60喷 射的混合气流或火焰、 第一空气流 66和第二空气流 68合围形成的气流呈四角切 圆即可， 本发明不对此限定。
[0061] 在所示的实施例中， 第一空气流喷射结构 62为设在外圈火焰筒 16上的一个或多 个第一气孔 62， 火焰筒外部的高压空气通过该第一气孔 62而向燃烧腔 14内朝向 内圈火焰筒喷射该第一空气流 66。 类似地， 第二空气流喷射结构 64为设在内圈 火焰筒 18上的一个或多个第二气孔 64， 火焰筒外部的高压空气通过该第二气孔 6 4向燃烧腔 14内朝向外圈火焰筒喷射该第二空气流 68。 此外， 内圈火焰筒 18和外 圈火焰筒 16上设有若干贯穿的冷却孔， 以使得外部空气可经冷却孔进入燃烧腔 1 4内在火焰筒壁面形成气膜， 阻隔高温火焰。
[0062] 本实施例中， 第一气孔 62和第二气孔 64的孔径大于冷却孔的孔径， 其具体数值 根据气动参数设计。
[0063] 所述四角切圆的具体运行原理为： 第一喷嘴 12a的第一混合气出口 50喷出的沿 第一喷射方向 58前进的第一火焰与从第一空气流喷射结构 62喷出的第一空气流 6 6相交， 第一空气流 66可以改变第一火焰的行进方向为第一空气流方向， 由于第 一火焰本身具有一定的沿第一喷射方向 58的行进动量， 因此两股气流相交后沿 一弧形路径行进。 第二喷嘴 12b的第二混合气出口 56喷出的沿第二喷射方向 60前 进的第二火焰与从第二空气流喷射结构 64喷出的第二空气流 68相交， 第二空气 流 68可以改变第二火焰的行进方向为第二空气流方向， 由于第二火焰本身具有 一定的沿第二喷射方向 60的行进动量， 因此两股气流相交后沿另一弧形路径行 进。 两弧形路径合围形成一四角切圆路径， 在第一空气流 66和第二空气流 68的 作用下， 混合后的气流沿该四角切圆路径循环， 相邻喷嘴之间的中间位置形成 旋流， 有效避免混合气出口喷射出来的火焰直接喷射到相邻的喷嘴 12上。 同吋 ， 这种旋流相当于在更短的轴向空间内拉长了火焰的长度， 因此使得燃烧更充 分， 排放更好， 也使得燃烧室的轴向尺寸可以进一步降低， 最终的燃气轮机也 可以具有更小的轴向尺寸。
[0064] 如图 11-13所示， 为了使得燃气和空气能够更均匀地混合， 喷嘴 12的空气通道 2 8内设置一旋流器 74， 以使得进入空气通道 28内的空气形成旋流， 增大空气流动 强度， 使其能够与燃气快速均匀地混合， 提高燃烧效率， 从而降低氮氧化物的 排放。 在所示的实施例中， 旋流器 74包括设置在主喷嘴筒状部 32的外周面上的 若干叶片 76， 叶片 76的内侧固定连接在主喷嘴筒状部 32的外周面上， 叶片 76的 外侧固定连接至喷嘴外壁筒状部 36的内周面上。 在其它未描述的实施例中， 叶 片也可以只与所述主喷嘴筒状部的外周面和喷嘴外壁的内周面其中之一固定连 接。
[0065] 应当理解的是， 本实施例中旋流器 74实施为弧形长条形叶片 76， 在其他实施例 中， 旋流器 74也可以实施成其他结构， 只要能使得空气通道内的空气形成旋流 即可。
[0066] 综上所述， 本发明提供了一种燃气轮机燃烧室及其喷嘴， 喷嘴包括主喷嘴及环 绕主喷嘴设置的喷嘴外壁， 主喷嘴形成燃气通道， 喷嘴外壁与主喷嘴在径向上 间隔以在二者之间形成空气通道， 主喷嘴上设置燃气出口， 喷嘴外壁上设置与 燃气出口对应的混合气出口， 使得燃气出口喷出的燃气与空气通道内的空气混 合后从混合气出口喷出， 每个喷嘴的混合气出口的喷射方向朝向相邻喷嘴。 本 发明的喷嘴结构设计巧妙， 能更好地混合燃气和空气， 并将混合气喷射入燃烧 室的燃烧腔内进行燃烧， 避免了高温火焰对火焰筒壁的损害。 其次， 在一些实 施例中， 燃烧室内还设置若干火焰阻挡结构， 火焰阻挡结构设置在相邻两喷嘴 之间， 以阻止从喷嘴喷射出的火焰直接喷射到相邻的喷嘴上对其产生损坏， 延 长燃烧室的使用寿命。 再次， 在一些实施例中， 燃烧室还可在外圈火焰筒和内 圈火焰筒上设置空气流喷射结构， 空气流喷射结构构造成其喷射出的空气流与 相邻两喷嘴的相对的两混合气出口喷射出的火焰形成四角切圆， 空气流可改变 喷射火焰的行进方向， 进而沿所述四角切圆循环运转， 有效避免喷射火焰对燃 烧室及喷嘴造成损坏， 提高燃烧腔内的燃气燃烧效率。 本发明的燃气轮机燃烧 室结构简单， 构思新颖， 可最大程度降低对燃烧室各元件的损坏， 提高燃烧室 的燃烧效率， 降低生产成本。
[0067] 本文所描述的概念在不偏离其精神和特性的情况下可以实施成其它形式。 所公 幵的具体实施例应被视为例示性而不是限制性的。 因此， 本发明的范围是由所 附的权利要求， 而不是根据之前的这些描述进行确定。 在权利要求的字面意义 及等同范围内的任何改变都应属于这些权利要求的范围。

Claims

权利要求书
[权利要求 1] 一种燃气轮机燃烧室， 包括：
环形火焰筒， 所述环形火焰筒形成环形燃烧腔， 所述环形燃烧腔定义 一轴向和围绕所述轴向的圆周方向； 以及
设置在所述环形燃烧腔内的若干喷嘴， 所述若干喷嘴沿所述圆周方向 均匀排列， 所述喷嘴用于将混合有燃气和空气的混合气喷入所述燃烧 腔；
其特征在于， 每个喷嘴设有至少一个用于朝向一相邻的喷嘴喷射混合 气的的混合气出口， 每两个相邻的喷嘴之间设置一个火焰阻挡结构， 用于阻止所述混合气产生的火焰直接喷射到所述相邻的喷嘴上。
[权利要求 2] 如权利要求 1所述的燃气轮机燃烧室， 其特征在于， 每个喷嘴设置两 个混合气出口， 且所述两个混合气出口定义的混合气喷射方向相反。
[权利要求 3] 如权利要求 2所述的燃气轮机燃烧室， 其特征在于， 所述火焰阻挡结 构包括空心体， 所述空心体具有内部空腔， 所述空心体的壁部设有与 所述内部空腔流体相通的若干通孔， 所述空心体的一轴向端部固定在 所述火焰筒上， 用于接收所述火焰筒外部的冷却空气使得所述冷却空 气充满所述内部空腔。
[权利要求 4] 如权利要求 3所述的燃气轮机燃烧室， 其特征在于， 所述空心体的另 一轴向端部设有与所述内部空腔流体相通的若干通孔。
[权利要求 5] 如权利要求 3所述的燃气轮机燃烧室， 其特征在于， 所述空心体具有 一面向一相邻的喷嘴的阻挡面， 所述阻挡面为弧形面。
[权利要求 6] 如权利要求 3所述的燃气轮机燃烧室， 其特征在于， 所述空心体为一 空心圆柱体或椭圆柱体， 所述圆柱体或椭圆柱体具有平行于所述轴向 的中心线。
[权利要求 7] 如权利要求 6所述的燃气轮机燃烧室， 其特征在于， 在一径向截面中
， 所述空心体的中心和所述喷嘴的中心位于同一个圆上。
[权利要求 8] 如权利要求 1所述的燃气轮机燃烧室， 其特征在于， 每个喷嘴包括： 主喷嘴， 所述主喷嘴包括沿所述轴向延伸的主喷嘴筒状部， 所述主喷 嘴筒状部末端为封闭端， 所述主喷嘴筒状部具有一内部燃气通道以及 贯穿所述主喷嘴筒状部的燃气出口；
喷嘴外壁， 所述喷嘴外壁包括喷嘴外壁筒状部， 所述喷嘴外壁筒状部 环绕所述主喷嘴筒状部且与所述主喷嘴筒状部在径向上间隔从而在所 述主喷嘴筒状部和喷嘴外壁筒状部之间形成环形空气通道， 所述混合 气出口贯穿所述喷嘴外壁筒状部且与所述燃气出口在径向上对应， 使 得从所述燃气出口喷出的燃气与所述空气通道内的空气混合后从所述 混合气出口喷出。
[权利要求 9] 如权利要求 8所述的燃气轮机燃烧室， 其特征在于， 每个喷嘴具有两 个混合气出口， 每个混合气出口朝向一对应的相邻火焰阻挡结构喷射 混合气， 每个混合气出口具有一中心线， 每个火焰阻挡结构包括一空 心体， 所述空心体具有一与所述轴向平行的中心线， 每个混合气出口 的中心线穿过与该混合气出口对应的空心体的中心线。
[权利要求 10] 如权利要求 8所述的燃气轮机燃烧室， 其特征在于， 所述喷嘴外壁具 有喷嘴外壁端部， 所述喷嘴外壁端部设有端部通孔并与所述主喷嘴筒 状部的封闭端在轴向上间隔幵。
PCT/CN2016/106668 2016-11-21 2016-11-21 燃气轮机燃烧室 WO2018090384A1 (zh)

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CN106338084A (zh) * 2016-11-21 2017-01-18 深圳智慧能源技术有限公司 燃气轮机燃烧室
CN106439914A (zh) * 2016-11-21 2017-02-22 深圳智慧能源技术有限公司 燃气轮机燃烧室
CN206176456U (zh) * 2016-11-21 2017-05-17 深圳智慧能源技术有限公司 燃气轮机燃烧室
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CN103998745A (zh) * 2011-08-22 2014-08-20 马吉德·托甘 在燃气轮机上使用的具有分级切向燃料-空气喷嘴的筒状环形燃烧室
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