CN111829007A - Axial staged combustion chamber based on flame tube concave cavity structure - Google Patents
Axial staged combustion chamber based on flame tube concave cavity structure Download PDFInfo
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- CN111829007A CN111829007A CN202010739938.0A CN202010739938A CN111829007A CN 111829007 A CN111829007 A CN 111829007A CN 202010739938 A CN202010739938 A CN 202010739938A CN 111829007 A CN111829007 A CN 111829007A
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- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
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- 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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
Abstract
The invention is suitable for the technical field of gas turbines, and particularly relates to an axial staged combustion chamber based on a flame tube concave cavity structure. The axial staged combustion chamber based on the flame tube concave cavity structure provided by the embodiment of the invention has the advantages of simple structure and reasonable design. The designed auxiliary feeding piece can realize the bypass of partial air at low load, reduce the air-fuel ratio of the main combustion area and stabilize combustion; at high load, fuel is injected into the flame tube from the rear of the main combustion zone, so that the equivalence ratio of the main combustion zone is constant, and NOx emission is reduced. Air and fuel enter the auxiliary feeding piece and then are fully mixed, a uniform secondary combustion area is formed at the rear part of the flame tube, and NOx emission is not increased. And one side of the concave cavity structure, which is close to the flame tube, is gradually contracted, so that flame is prevented from entering the concave cavity.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to an axial staged combustion chamber based on a flame tube concave cavity structure.
Background
The gas turbine is one of the most widely applied rotating machines at present, the application field relates to various fields such as electric power, petrifaction and ships, and military use and civil use, and a gas turbine combustion chamber with higher performance, more stability, wider operation range and lower pollutants is a target which is always pursued by research and development personnel. Currently, staged combustion technology is the combustion technology most studied and applied by gas turbine designers, and includes radial staging, axial staging, and staged combustion technology combined with cavity trapped vortex.
The existing gas turbine combustor adopts a concave cavity structure to replace an on-duty combustor, stabilizes main combustion flame, and can be considered as axial staged combustion of a combustor head. The patent mainly replaces an on-duty combustor to stabilize main combustion flame, and due to the fact that the air and fuel quantity of the on-duty combustor are small, staged combustion in different load ranges cannot be achieved.
Disclosure of Invention
The embodiment of the invention aims to provide an axial staged combustion chamber based on a flame tube concave cavity structure, and aims to solve the problem that the conventional gas wheel combustor cannot realize staged combustion in different load ranges.
The embodiment of the invention is realized in such a way that the axial staged combustion chamber based on the flame tube cavity structure comprises a combustion chamber casing, and further comprises a flame tube, a main premixing cyclone, an on-duty cyclone and an auxiliary feed member, wherein the main premixing burner and the on-duty burner are positioned at the head part of the combustion chamber, an outer throat shell of the main premixing cyclone, an inner throat shell of the main premixing cyclone and the main premixing cyclone form a main premixing channel, the outer throat shell of the main premixing cyclone is connected with the flame tube, the on-duty cyclone is positioned at the center of the inner throat shell of the main premixing cyclone, and the auxiliary feed member is fixed on the outer wall of the flame tube and is used for mixing air and auxiliary fuel and injecting the mixed gas into the flame tube.
Preferably, the auxiliary feeding piece is a first flame tube cavity structure, the first flame tube cavity structure comprises an annular cavity structure shell, an annular mixing cavity is arranged in the middle of the cavity structure shell, the mixing cavity is communicated with a flame tube inner cavity, one side, close to a combustion chamber casing, of the cavity structure shell is provided with a plurality of cavity air diversion chutes communicated with the mixing cavity, two sides, located in the mixing cavity, of the cavity structure shell are respectively provided with a cavity structure left side fuel cavity and a cavity structure right side fuel cavity, the cavity structure left side fuel cavity and the cavity structure right side fuel cavity are respectively communicated with the mixing cavity through a cavity structure left side fuel jet hole and a cavity structure right side fuel jet hole, and the cavity structure left side fuel cavity and the cavity structure right side fuel cavity are respectively provided with a cavity structure left side fuel control valve and a cavity structure right side fuel control valve.
Preferably, the auxiliary feeding part is a sectional type flame tube cavity structure, the sectional type flame tube cavity structure comprises a sectional type cavity structure shell, the sectional type cavity structure shell is uniformly distributed with a plurality of groups along the outer diameter of a flame tube, the distribution interval is less than 10 degrees, the middle part of the sectional type cavity structure shell is provided with an annular mixing cavity, the mixing cavity is communicated with the inner cavity of the flame tube, one side of the sectional type cavity structure shell, which is close to a combustion chamber casing, is provided with a plurality of cavity air diversion chutes communicated with the mixing cavity, the two sides of the sectional type cavity structure shell, which are positioned on the mixing cavity, are respectively provided with a cavity structure left side fuel cavity and a cavity structure right side fuel cavity, the cavities on the left side of the cavity structure and the cavities on the right side of the cavity structure are communicated through pipelines, and the cavity structure left side fuel jet hole and the cavity structure right side fuel, the fuel cavity on the left side of the concave cavity structure and the fuel cavity on the right side of the concave cavity structure are respectively provided with a fuel control valve on the left side of the concave cavity structure and a fuel control valve on the right side of the concave cavity structure.
Preferably, the width of the mixing cavity is gradually reduced on the side close to the flame tube.
Preferably, the auxiliary feeding part is a second flame tube cavity structure, the second flame tube cavity structure comprises an annular cavity structure shell, an annular mixing cavity is arranged in the middle of the cavity structure shell, the mixing cavity is communicated with the inner cavity of the flame tube, one side of the cavity structure shell, which is close to the combustion chamber casing, is provided with a plurality of cavity air diversion chutes communicated with the mixing cavity, two sides of the cavity structure shell, which are positioned in the mixing cavity, are respectively provided with a cavity structure left side fuel cavity and a cavity structure right side fuel cavity, the cavity structure left side fuel cavity and the cavity structure right side fuel cavity are respectively communicated with the mixing cavity through a cavity structure left side fuel jet hole and a cavity structure right side fuel jet hole, the cavity structure left side fuel control valve and the cavity structure right side fuel control valve are respectively arranged on the cavity structure left side fuel cavity and the cavity structure right side fuel cavity, the width of the mixing cavity from one side of the combustion chamber casing to one, the junction of the mixing chamber and the flame tube is provided with a flame tube contraction section with a concave cavity structure outlet.
Preferably, the end parts of the main premixing swirler outer throat housing and the main premixing swirler inner throat housing are tilted, and the included angle between the end parts and the axis of the main premixing swirler outer throat housing and the main premixing swirler inner throat housing is 15-20 degrees.
Preferably, the number of the fuel jet holes on the left side of the cavity structure and the number of the fuel jet holes on the right side of the cavity structure are not less than 36.
The axial staged combustion chamber based on the flame tube concave cavity structure provided by the embodiment of the invention has the advantages of simple structure, reasonable design and the following main beneficial effects:
(1) the designed auxiliary feeding piece can realize the bypass of partial air at low load, reduce the air-fuel ratio of the main combustion area and stabilize combustion;
(2) at high load, fuel is injected into the flame tube from the rear of the main combustion zone, so that the equivalence ratio of the main combustion zone is constant, and NOx emission is reduced.
(3) One side of the concave cavity structure, which is close to the flame tube, is provided with a contraction structure, air and fuel are fully mixed after entering the auxiliary feeding piece and are sprayed into the flame tube to form a uniform combustion area, so that tempering is prevented.
Drawings
FIG. 1 is a schematic structural diagram of an axially staged combustor based on a flame tube cavity structure according to an embodiment of the invention;
FIG. 2 is a schematic structural diagram of a first liner bowl configuration according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a combustor basket having a first combustor basket bowl configuration according to an embodiment of the present invention;
FIG. 4 is a cross-sectional view of a first liner bowl configuration according to an embodiment of the present invention;
FIG. 5 is a cross-sectional view of a first alternative first liner bowl configuration liner according to an embodiment of the present invention;
FIG. 6 is a cross-sectional view of another first liner bowl configuration according to an embodiment of the present invention;
FIG. 7 is a schematic diagram of a flame tube with a second flame tube cavity configuration according to an embodiment of the invention;
FIG. 8 is a schematic structural diagram of a second liner cavity configuration according to an embodiment of the present invention.
In the drawings: 1. a combustion chamber casing; 2. a first flame tube cavity structure; 3. a flame tube; 4. a primary premix cyclone; 5. a combustion chamber end cap flange; 6. a duty burner; 7. a swirler on duty; 8. the outer throat shell of the main premixing swirler; 9. the inner throat shell of the main premixing swirler; 10. a housing of a reentrant structure; 11. a concave cavity structure contraction section; 12. a fuel control valve on the left side of the cavity structure; 13. the right fuel control valve of the concave cavity structure; 14. the right side fuel cavity of the concave cavity structure; 15. the left fuel jet hole of the concave cavity structure; 16. the right side of the concave cavity structure is provided with a fuel jet hole; 17. the left fuel cavity of the concave cavity structure; 18. a concave cavity air diversion chute; 19. a sectional flame tube cavity structure; 20. a second flame tube cavity structure; 21. the flame tube contraction section at the outlet of the concave cavity structure; 100. combustor inlet air; 101. primary premix air; 102. pilot cyclone inlet air; 103. a primary premix swirler fuel; 104. the on-duty burner diffuses fuel; 105. partially premixing fuel by using an on-duty combustor; 106. the concave cavity structure is used for introducing air; 107. fuel on the left side of the concave cavity structure; 108. fuel on the right side of the concave cavity structure; 109. premixing gas at the outlet of the concave cavity structure; 22. flame on duty; 23. premixing flame; 24. a secondary combustion zone.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Specific implementations of the present invention are described in detail below with reference to specific embodiments.
As shown in fig. 1, the structure of an axially staged combustion chamber based on a flame tube recessed cavity structure provided for an embodiment of the present invention includes a combustion chamber casing 1, and the axially staged combustion chamber based on a flame tube recessed cavity structure further includes a flame tube 3, a main premixing swirler 4, an on-duty swirler 7, and an auxiliary feed member, wherein the main premixing burner 4 and the on-duty burner 7 are located at a head portion of the combustion chamber, a main premixing swirler outer throat housing 8, a main premixing swirler inner throat housing 9, and the main premixing swirler 4 form a main premixing passage, the main premixing swirler outer throat housing 8 is connected with the flame tube 3, the on-duty burner 7 is located at a central position of the main premixing swirler inner throat housing 9, and the auxiliary feed member is fixed on an outer wall of the flame tube 3 and is used for mixing air and auxiliary fuel and injecting mixed gas into the flame tube 3.
In the embodiment of the invention, a combustion chamber end cover flange 5 is arranged at the end part of a combustion chamber casing 1, an on-duty burner 6 is fixed at the core part of the combustion chamber end cover flange 5, a flame tube 3 is arranged in the combustion chamber casing 1, one end of the flame tube 3 close to the on-duty burner 6 is provided with a main premixing swirler outer throat shell 8 and a main premixing swirler inner throat shell 9, one end of the flame tube 3 far away from the combustion chamber casing 1 is provided with a convergent section, the main premixing swirler inner throat shell 9 is fixed in the main premixing swirler outer throat shell 8, one end of the on-duty burner 6 far away from the combustion chamber end cover flange 5 extends into the core part of the main premixing swirler inner throat shell 9, an auxiliary feed piece is fixed on the outer wall of the convergent section in the flame tube 3, and the on-duty swirler 7 is arranged between the inner diameter of the main premixing swirler inner throat shell 9 and the outer diameter of the on-duty burner 6. In use, combustor inlet air 100 from the compressor passes through the annular passage between the combustor casing 1 and the combustor basket 3 and the auxiliary inlet member on the combustor basket 3, a portion of the air is diverted from the auxiliary inlet member, and the remaining air flows toward the combustor head. The combustor head air is divided into two streams: the main premixed air 101 enters the flame tube 3 along the premixing passage through the main premixing swirler 4; the on-duty swirler inlet air 102 enters the flame tube 3 through the on-duty swirler 7. The pilot swirler inlet air 102 and pilot burner premixed fuel 105 are partially mixed into the cone shroud at the end of the pilot burner 6 and mixed with pilot burner diffusion fuel 104 for combustion to form the pilot flame 22. The primary premixed air 101 mixes with the primary premixed swirler fuel injected by the primary premixed swirler 4 and enters the flame tube 3 to form the premixed flame 23. The high-temperature flue gas after the on-duty flame 22 and the premixed flame 23 are combusted flows in the flame tube 3, and collides with the air/fuel mixed gas in the auxiliary feeding member at the rear part of the flame tube 3, is mixed and combusted to form a secondary combustion area 24.
As shown in fig. 1, 2, 3 and 4, as a preferred embodiment of the present invention, the auxiliary feeding member is a first flame tube cavity structure 2, the first flame tube cavity structure 2 includes an annular cavity structure shell 10, an annular mixing cavity is disposed in the middle of the cavity structure shell 10, the mixing cavity is communicated with the inner cavity of the flame tube 3, one side of the cavity structure shell 10 close to the combustion chamber casing 1 is provided with a plurality of cavity air diversion chutes 18 communicated with the mixing cavity, two sides of the cavity structure shell 10 located at the mixing cavity are respectively provided with a cavity structure left side fuel cavity 17 and a cavity structure right side fuel cavity 14, the cavity structure left side fuel cavity 17 and the cavity structure right side fuel cavity 14 are respectively communicated with the mixing cavity through a cavity structure left side fuel jet hole 15 and a cavity structure right side fuel jet hole 16, and the cavity structure left side fuel cavity 17 and the cavity structure right side fuel cavity 14 are respectively provided with a cavity structure left side fuel control valve 12 and a cavity structure right side fuel control valve 14 13.
In the embodiment of the invention, the concave cavity structure shell 10 is annular and is fixed on the outer diameter of the flame tube 3; the total area of the holes of the concave cavity air diversion chute 18 is about 1.2-1.6 times of the outlet of the connection part of the mixing cavity and the flame tube 3. When the secondary combustion device is used, fuel enters the mixing cavity through the fuel jet hole 15 on the left side of the cavity structure and the fuel jet hole 16 on the right side of the cavity structure, air enters the mixing cavity through the air diversion chute 18 of the cavity structure, the fuel and the air are uniformly mixed in the mixing cavity and then are sprayed into the flame tube 3, and a secondary combustion area 24 is formed at the rear part of the flame tube 3.
As shown in FIGS. 1, 5 and 6, as a preferred embodiment of the present invention, the auxiliary feeding member is a segmented flame tube cavity structure 19, the segmented flame tube cavity structure 19 includes a segmented cavity structure casing, the segmented cavity structure casing is uniformly distributed with a plurality of groups along the outer diameter of the flame tube 3, the distribution interval is less than 10 degrees, an annular mixing chamber is arranged in the middle of the segmented cavity structure casing, the mixing chamber is communicated with the inner cavity of the flame tube 3, one side of the segmented cavity structure casing close to the combustion chamber casing 1 is provided with a plurality of cavity air diversion chutes 18 communicated with the mixing chamber, two sides of the segmented cavity structure casing at the mixing chamber are respectively provided with a cavity structure left side fuel chamber 17 and a cavity structure right side fuel chamber 14, the cavity structure left side fuel chamber 17 and the cavity structure right side fuel chamber 14 are communicated through a pipeline, the cavity structure left side fuel chamber 17 and the cavity structure right side fuel chamber 14 are respectively communicated through a cavity structure left side fuel 15 and a cavity structure right side fuel jet hole 16 are communicated with the mixing cavity, and a cavity structure left side fuel control valve 12 and a cavity structure right side fuel control valve 13 are respectively arranged on a cavity structure left side fuel cavity 17 and a cavity structure right side fuel cavity 14.
In the embodiment of the invention, 2-8 groups of sectional type concave cavity structure shells are uniformly distributed along the outer diameter of the flame tube 3, and the main premixing swirler 4 enables the airflow in the flame tube to rotate, so that the sectional type concave cavity structure shells have certain intervals, and the temperature distribution at the outlet of the combustion chamber is not uneven.
As shown in fig. 1, 5 and 6, as a preferred embodiment of the present invention, the width of the mixing chamber is gradually reduced on the side close to the liner 3.
In the embodiment of the invention, as the outlet of the mixing cavity is gradually reduced, the injection speed of the gas mixed by air and fuel is increased after the gas passes through the mixing cavity, so that the flame is prevented from returning to the mixing cavity.
As shown in fig. 7 and 8, as a preferred embodiment of the present invention, the auxiliary feeding member is a second flame tube cavity structure 20, the second flame tube cavity structure 20 includes an annular cavity structure housing 10, an annular mixing chamber is disposed in the middle of the cavity structure housing 10, the mixing chamber is communicated with the inner chamber of the flame tube 3, one side of the cavity structure housing 10 close to the combustion chamber casing 1 is provided with a plurality of cavity air diversion chutes 18 communicated with the mixing chamber, the cavity structure housing 10 is disposed at two sides of the mixing chamber and is respectively provided with a cavity structure left side fuel chamber 17 and a cavity structure right side fuel chamber 14, the cavity structure left side fuel chamber 17 and the cavity structure right side fuel chamber 14 are respectively communicated with the mixing chamber through a cavity structure left side fuel jet hole 15 and a cavity structure right side fuel jet hole 16, the cavity structure left side fuel chamber 17 and the cavity structure right side fuel chamber 14 are respectively provided with a cavity structure left side fuel control valve 12 and a cavity structure right side fuel control valve 13, the width of the mixing cavity from one side of the combustion chamber casing 1 to one side of the flame tube 3 is unchanged, and a concave cavity structure outlet flame tube contraction section 21 is arranged at the joint of the mixing cavity and the flame tube 3.
In the embodiment of the present invention, the concave cavity structure outlet liner convergent section 21 is a plate structure for reducing the communication area between the mixing chamber and the liner 3, thereby preventing the flame from returning to the mixing chamber.
As shown in fig. 1, as a preferred embodiment of the present invention, the ends of the main premix swirler outer throat housing 8 and the main premix swirler inner throat housing 9 are tilted, and the angles between the ends and the axes of the main premix swirler outer throat housing 8 and the main premix swirler inner throat housing 9 are between 15 ° and 20 °.
As shown in FIG. 1, as a preferred embodiment of the invention, the number of the fuel jet holes 15 on the left side of the concave cavity structure and the number of the fuel jet holes 16 on the right side of the concave cavity structure are not less than 36.
In the embodiment of the invention, the fuel jet holes 15 on the left side of the concave cavity structure and the fuel jet holes 16 on the right side of the concave cavity structure are both provided with a plurality of holes, so that the fuel can be divided into a plurality of strands to be sprayed, the atomization degree of the sprayed fuel is ensured, and the sprayed fuel can be quickly and uniformly mixed with air to be beneficial to later combustion.
When the invention is used, the inlet air 106 of the concave cavity structure entering from the concave cavity air diversion chute 18 accounts for about 20-25% of the total air flow. Air flow of 60% enters the flame tube 3 from the combustor head main premix burner and the on-duty burner 6. When the combustion chamber of the gas turbine is ignited under the starting working condition, only the diffusion fuel 104 of the on-duty combustor is injected, and the whole combustion chamber is subjected to diffusion combustion. As the gas turbine speed increases, the diffusion fuel continues to increase until the gas turbine reaches full speed.
When the gas turbine enters the load-up stage, the diffusion fuel 104 of the on-duty combustor is kept unchanged, and the part of the premixed fuel 105 of the on-duty combustor is added to push the load of the gas turbine to rise until the load of the gas turbine reaches about 20%. At this point, the pilot burner diffusion fuel 104 is switched to the main premixed swirler fuel 103, and the pilot burner diffusion fuel 104 maintains a total fuel amount of about 1.0%. At this time, the premixed flame 23 formed by the main premixed swirler fuel 103 is stably combusted under the stabilizing action of the on-duty flame 22 formed by the on-duty combustor diffusion fuel 104 and the on-duty combustor partial premixed fuel 105, the combustion chamber enters a premixed combustion mode, and the pollutant emission is low. The main premix swirler fuel 103 continues to be added, pushing the gas turbine load up to about 60% load. In the process, no fuel is injected into the auxiliary feeding piece, the cavity structure can bypass the total air flow of the combustion chamber by about 20-25%, the air/fuel ratio of the main combustion area is reduced, and the flame stability of the main combustion area is maintained.
After the gas turbine reaches 60% loadIf the main premixed swirler fuel 103 is added, the average flame temperature in the main combustion zone will exceed 1800K, resulting in NOXThe emissions increase. After the gas turbine is 60% loaded, the main premixed air/fuel ratio is maintained unchanged, and the redundant fuel is injected into the auxiliary feeding piece through the fuel jet holes 15 at the left side of the concave cavity structure and the fuel jet holes 16 at the right side of the concave cavity structure. The re-entrant inlet air is thoroughly mixed with the re-entrant left side fuel 107 and the re-entrant right side fuel 108 in the auxiliary feed to form a re-entrant outlet premix gas 109 to the liner 3. Because the air and the fuel are fully mixed in the auxiliary feeding piece, the air and the fuel are mixed with high-temperature flue gas after being combusted in the main combustion area after entering the flame tube 3, and a uniform secondary combustion area 24 is formed at the rear part of the flame tube 3. The premixed gas in the secondary combustion area 24 and the high-temperature flue gas form homogeneous reaction, NO flame frontal surface exists, and NO NO is generatedXAnd (5) discharging. The gas turbine can still maintain low pollutant emissions from 60% load to full load.
The auxiliary feeding piece sprays fuel under the high-load working condition of the gas turbine, and the air-fuel equivalence ratio in the auxiliary feeding piece ranges from 0 to 0.45. After the auxiliary feeding piece mixes the flame 23, the premixed gas 109 at the outlet of the concave cavity structure enters the flame tube 3 and then is mixed and reacted with the high-temperature flue gas which is combusted in the main combustion area, and the amount of the fuel in the auxiliary feeding piece does not influence the main combustion area. Under the high-load working condition of the gas turbine, combustion instability occurs in the combustion chamber, and the main premixed flame can be stabilized by adjusting the fuel quantity of the auxiliary feeding piece.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (8)
1. An axial staged combustion chamber based on a flame tube concave cavity structure comprises a combustion chamber casing (1), the axial staged combustion chamber based on the flame tube cavity structure is characterized by further comprising a flame tube (3), a main premixing cyclone (4), an on-duty cyclone (7) and an auxiliary feeding member, wherein the main premixing burner (4) and the on-duty burner (7) are positioned at the head of the combustion chamber, a main premixing channel is formed by an outer roating channel shell (8) of the main premixing cyclone, an inner roating channel shell (9) of the main premixing cyclone and the main premixing cyclone (4), the outer roating channel shell (8) of the main premixing cyclone is connected with the flame tube (3), the on-duty cyclone (7) is positioned at the center of the inner roating channel shell (9) of the main premixing cyclone, the auxiliary feeding member is fixed on the outer wall of the flame tube (3), for mixing air and auxiliary fuel and injecting the mixed gas into the flame tube (3).
2. The device comprises a flame tube (3), a duty burner (6), a duty swirler (7) and an auxiliary feeding member, wherein a combustion chamber end cover flange (5) is arranged at the end part of a combustion chamber casing (1), the duty burner (6) is fixed at the core part of the combustion chamber end cover flange (5), the flame tube (3) is arranged in the combustion chamber casing (1), one end close to the duty burner (6) is provided with a main premixing swirler outer roar shell (8) and a main premixing swirler inner roar shell (9), the main premixing swirler inner roar shell (9) is fixed in the main premixing swirler outer roar shell (8), one end of the duty burner (6) far away from the combustion chamber end cover flange (5) extends into the core part of the main premixing swirler inner roar shell (9), the auxiliary feeding member is fixed on the outer wall of the flame tube (3) and is used for mixing air and auxiliary fuel and injecting mixed gas into the flame tube (3), the pilot swirler (7) is arranged between the inner diameter of a throat shell (9) in the main premixing swirler and the outer diameter of the pilot burner (6).
3. The combustor of claim 1, wherein the auxiliary feeding component is a first combustor basket cavity (2), the first combustor basket cavity (2) comprises an annular cavity shell (10), an annular mixing cavity is arranged in the middle of the cavity shell (10), the mixing cavity is communicated with the inner cavity of the combustor basket (3), one side of the cavity shell (10) close to the combustor casing (1) is provided with a plurality of cavity air diversion chutes (18) communicated with the mixing cavity, the two sides of the cavity shell (10) at the mixing cavity are respectively provided with a cavity left side fuel cavity (17) and a cavity right side fuel cavity (14), the cavity left side fuel cavity (17) and the cavity right side fuel cavity (14) are respectively communicated with the mixing cavity through a cavity left side fuel jet hole (15) and a cavity right side fuel jet hole (16), the concave cavity structure left side fuel cavity (17) and the concave cavity structure right side fuel cavity (14) are respectively provided with a concave cavity structure left side fuel control valve (12) and a concave cavity structure right side fuel control valve (13).
4. The combustor of claim 1, wherein the auxiliary feeding member is a segmented combustor basket cavity structure (19), the segmented combustor basket cavity structure (19) comprises a segmented combustor basket cavity structure shell, the segmented combustor basket cavity structure shell is uniformly distributed with a plurality of groups along the outer diameter of the combustor basket (3) and has a distribution interval of less than 10 degrees, an annular mixing cavity is arranged in the middle of the segmented combustor basket cavity structure shell and is communicated with the inner cavity of the combustor basket (3), a plurality of cavity air diversion chutes (18) communicated with the mixing cavity are formed in one side of the segmented combustor basket cavity structure shell close to the combustor basket (1), the segmented combustor basket cavity structure shell is respectively provided with a cavity structure left side fuel cavity (17) and a cavity structure right side fuel cavity (14) at two sides of the mixing cavity, and the cavity structure left side fuel cavity (17) and the cavity structure right side fuel cavity (14) are communicated through pipelines, the cavity structure left side fuel cavity (17) and the cavity structure right side fuel cavity (14) are communicated with the mixing cavity through a cavity structure left side fuel jet hole (15) and a cavity structure right side fuel jet hole (16) respectively, and a cavity structure left side fuel control valve (12) and a cavity structure right side fuel control valve (13) are arranged on the cavity structure left side fuel cavity (17) and the cavity structure right side fuel cavity (14) respectively.
5. The combustor of claim 3, wherein the width of the mixing chamber is gradually reduced on the side close to the flame tube (3).
6. The combustor of claim 1, wherein the auxiliary feeding component is a second combustor basket cavity (20), the second combustor basket cavity (20) comprises an annular cavity shell (10), an annular mixing cavity is arranged in the middle of the cavity shell (10), the mixing cavity is communicated with the inner cavity of the combustor basket (3), one side of the cavity shell (10) close to the combustor casing (1) is provided with a plurality of cavity air diversion chutes (18) communicated with the mixing cavity, the two sides of the cavity shell (10) at the mixing cavity are respectively provided with a cavity left side fuel cavity (17) and a cavity right side fuel cavity (14), the cavity left side fuel cavity (17) and the cavity right side fuel cavity (14) are respectively communicated with the mixing cavity through a cavity left side fuel jet hole (15) and a cavity right side fuel jet hole (16), the left fuel cavity (17) and the right fuel cavity (14) of the concave cavity structure are respectively provided with a left fuel control valve (12) and a right fuel control valve (13) of the concave cavity structure, the width of the mixing cavity from one side of the combustion chamber casing (1) to one side of the flame tube (3) is unchanged, and the joint of the mixing cavity and the flame tube (3) is provided with an outlet flame tube contraction section (21) of the concave cavity structure.
7. The combustor of any one of claims 1 to 5, wherein the ends of the main premix swirler outer throat housing (8) and the main premix swirler inner throat housing (9) are tilted, and the angles between the ends and the axes of the main premix swirler outer throat housing (8) and the main premix swirler inner throat housing (9) are between 15 ° and 20 °.
8. The combustor of any one of claims 2 to 5, wherein the number of the fuel jet holes (15) on the left side of the recessed cavity structure and the number of the fuel jet holes (16) on the right side of the recessed cavity structure are not less than 36.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010739938.0A CN111829007A (en) | 2020-07-28 | 2020-07-28 | Axial staged combustion chamber based on flame tube concave cavity structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010739938.0A CN111829007A (en) | 2020-07-28 | 2020-07-28 | Axial staged combustion chamber based on flame tube concave cavity structure |
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| Publication Number | Publication Date |
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| CN111829007A true CN111829007A (en) | 2020-10-27 |
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| CN202010739938.0A Pending CN111829007A (en) | 2020-07-28 | 2020-07-28 | Axial staged combustion chamber based on flame tube concave cavity structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114659140A (en) * | 2022-03-21 | 2022-06-24 | 杭州汽轮动力集团有限公司 | Low-emission combustor for fuel classification of gas turbine |
| CN116293815A (en) * | 2023-03-22 | 2023-06-23 | 无锡明阳氢燃动力科技有限公司 | Low nitrogen hydrogen combustion chamber structure |
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| CN205447829U (en) * | 2016-03-22 | 2016-08-10 | 上海电气燃气轮机有限公司 | Burner for a gas turbine |
| CN107525095A (en) * | 2017-07-24 | 2017-12-29 | 西北工业大学 | A kind of axially staged can burner of gas turbine |
| CN107559882A (en) * | 2017-07-24 | 2018-01-09 | 西北工业大学 | A kind of axially staged low pollution combustor |
| CN110207147A (en) * | 2019-05-27 | 2019-09-06 | 长兴永能动力科技有限公司 | A kind of dry type low nitrogen burning room |
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| KR20020027056A (en) * | 2000-10-04 | 2002-04-13 | 황해웅 | Gas turbin combuster and Air impingement cooling method of gas turbin liner |
| CN205447829U (en) * | 2016-03-22 | 2016-08-10 | 上海电气燃气轮机有限公司 | Burner for a gas turbine |
| CN107525095A (en) * | 2017-07-24 | 2017-12-29 | 西北工业大学 | A kind of axially staged can burner of gas turbine |
| CN107559882A (en) * | 2017-07-24 | 2018-01-09 | 西北工业大学 | A kind of axially staged low pollution combustor |
| CN110207147A (en) * | 2019-05-27 | 2019-09-06 | 长兴永能动力科技有限公司 | A kind of dry type low nitrogen burning room |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114659140A (en) * | 2022-03-21 | 2022-06-24 | 杭州汽轮动力集团有限公司 | Low-emission combustor for fuel classification of gas turbine |
| CN116293815A (en) * | 2023-03-22 | 2023-06-23 | 无锡明阳氢燃动力科技有限公司 | Low nitrogen hydrogen combustion chamber structure |
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Application publication date: 20201027 |
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