CN106524225B - The three vortex system tissue burned flame cylinders suitable for advanced low pollution turbogenerator - Google Patents
The three vortex system tissue burned flame cylinders suitable for advanced low pollution turbogenerator Download PDFInfo
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- CN106524225B CN106524225B CN201610968110.6A CN201610968110A CN106524225B CN 106524225 B CN106524225 B CN 106524225B CN 201610968110 A CN201610968110 A CN 201610968110A CN 106524225 B CN106524225 B CN 106524225B
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 155
- 238000003466 welding Methods 0.000 claims abstract description 5
- 238000002156 mixing Methods 0.000 claims description 26
- 239000000446 fuel Substances 0.000 claims description 22
- 238000001816 cooling Methods 0.000 claims description 18
- 238000006243 chemical reaction Methods 0.000 claims description 12
- 230000007704 transition Effects 0.000 claims description 12
- 230000009471 action Effects 0.000 claims description 9
- 238000010008 shearing Methods 0.000 claims description 9
- 238000002347 injection Methods 0.000 claims description 6
- 239000007924 injection Substances 0.000 claims description 6
- 230000015572 biosynthetic process Effects 0.000 claims description 5
- 230000008520 organization Effects 0.000 claims description 4
- 230000003116 impacting effect Effects 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 238000003915 air pollution Methods 0.000 abstract 1
- 238000009510 drug design Methods 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 12
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000003344 environmental pollutant Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008033 biological extinction Effects 0.000 description 1
- 230000000739 chaotic effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Classifications
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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
- F23R3/58—Cyclone or vortex type combustion chambers
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention belongs to turbogenerator technical fields, and in particular to a kind of three vortex system tissue burned flame cylinders suitable for advanced low pollution turbogenerator.It forms the vortex structures of two large scales in flame tube head by the rational design of jet hole, belongs to the head zone of burner inner liner, vortex system size and burner inner liner feature structure geometric dimension are in the same order of magnitude.Inner wall, the end wall of the burner inner liner are linked together by way of welding, can be then connected through a screw thread and are fixed on engine high pressure nozzle ring or casing;The mode that outer wall is connected through a screw thread is fixed on engine crankcase.Program combustion process has apparent RQL feature, and relatively traditional baffling combustion burner inner liner can effectively improve efficiency of combustion, reduce Air-pollution From Combustion discharge, and compact-sized.
Description
Technical Field
The invention belongs to the technical field of turbine engines, and particularly relates to a flame tube suitable for combustion of a three-vortex system structure of an advanced low-pollution turbine engine.
Background
The turbine engine mainly comprises an air compression system, a combustion system and an expansion work-doing system. As shown in fig. 1. The combustion system, generally referred to as a combustion chamber, is mainly composed of an atomizing device and a flame tube. The function of the flame tube is to ensure that the air at the outlet of the compression system is fully mixed with the fuel and the chemical energy can be generated so as to convert the chemical energy of the fuel into heat energy. The baffled flame tube structure is one type of flame tube structure.
As shown in fig. 1, a conventional annular baffling flame tube, a sleeve 5, an oil thrower 3, a casing 2 and the like form a combustion chamber, the flame tube consists of an outer ring 1 and an inner ring 4, the outer ring 1 and the inner ring 4 are both free of interlayers, and the inner ring 4 is arched; the casing 2 and the outer ring 1 form an outer ring cavity, and the sleeve 5 and the inner ring 4 form an inner ring cavity. Part of air in the outer ring cavity enters the flame tube through holes in the outer ring 1, and the air in the inner ring cavity is introduced from the rest air in the outer ring cavity through the hollow turbine guider and finally enters the flame tube through holes in the inner ring 4; the fuel oil is thrown out from the uniformly distributed holes of the oil throwing disc 3, enters the flame tube to be atomized and is combusted with air to emit heat.
The existing annular baffling flame tube cannot meet the requirements of the combustion chamber of the advanced low-pollution turbine engine. The combustion chamber forms a chaotic vortex system structure in a head flow field, is beneficial to oil-gas mixing, and has the characteristics of low combustion efficiency of the head of a flame tube, large pollution emission and the like. Structurally, the traditional baffling flame tube structure needs to be provided with a certain axial section as a space for afterburning (further burning of fuel which is not completely burnt at the head of the flame tube) and mixing. Therefore, the length-diameter ratio of the flame tube is larger, the compactness is not high, the total length of the engine is easily increased, and the thrust-weight ratio of the engine is reduced.
Disclosure of Invention
Technical problem to be solved
The technical problem to be solved by the invention is as follows: how to provide a flow field structure in three vortex system that is applicable to small-size baffling formula flame tube structure, can form to have the RQL characteristic, can realize the high-efficient burning and the low pollutant discharge of fuel with less slenderness ratio, higher compactness.
(II) technical scheme
In order to solve the above technical problems, the present invention provides a flame tube for combustion of a three-turbine structure suitable for an advanced low-pollution turbine engine, comprising: the device comprises a combustion chamber inlet 1, a combustion chamber outer casing 2, a combustion chamber inner ring airflow channel 3, a combustion chamber outlet 4, a flame tube inner wall 5, a combustion chamber rear casing 6, a combustion chamber inner casing rear section 7, an oil thrower 8, a combustion chamber inner casing front section 9, a combustion chamber front casing 10 and a flame tube outer wall 11; wherein,
the inner ring airflow channel 3 of the combustion chamber is connected with the inner wall and the outer wall of the flame tube in a welding mode;
the oil thrower 8 is fixed on a rotating shaft of an engine through friction force in a form of compressing two ends and rotates at the same rotating speed along with the rotating shaft;
the inner wall 5 of the flame tube and the outer wall 11 of the flame tube are connected in a lap joint mode, and the outer wall 11 of the flame tube is fixed in a downstream static structure through a flange;
the inner wall 5 of the flame tube and the outer wall 11 of the flame tube are provided with jet hole groups with an organization vortex system structure, the aperture of the jet holes in the jet hole groups is distributed between 5mm and 10mm, in addition, the inner wall 5 of the flame tube and the outer wall 11 of the flame tube are also provided with divergent cooling holes with the diameter of 0.5 to 0.7mm, and the opening direction of the divergent cooling holes and the normal direction of the wall surface of the flame tube form an angle of 60 to 70 degrees; the density distribution of the divergent cooling holes is 5-8/cm2(ii) a Air can enter the inner part of the flame tube through the divergent cooling holes to perform combustion chemical reaction with the fuel;
the combustion chamber inlet air flows into a flow channel between the combustion chamber outer casing 2 and the flame tube outer wall 11 from the combustion chamber inlet 1; then, the flame tube is divided into two paths, one path passes through an inner ring airflow channel 3 of the combustion chamber, and the other path passes through a channel formed among a front section 9 of a casing in the combustion chamber, a front casing 10 of the combustion chamber and an outer wall 11 of the flame tube;
the air which passes through the annular air flow channel 3 in the combustion chamber is divided again, enters a channel formed between the inner wall 5 of the flame tube and the rear casing 6 and the rear section 7 of the combustion chamber casing, and then enters the interior of the flame tube through a jet hole arranged on the inner wall 5 of the flame tube to perform combustion chemical reaction with the fuel; the airflow passing through the channel among the front section 9 of the casing in the combustion chamber, the front casing 10 of the combustion chamber and the outer wall 11 of the flame tube enters the interior of the flame tube through the jet hole and the divergent cooling hole on the outer wall 11 of the flame tube to perform combustion chemical reaction with fuel;
the oil thrower 8 is used for atomizing fuel in the oil thrower in a rotating mode and spraying the fuel into the flame tube so as to participate in the combustion chemical reaction; after the air and the fuel are subjected to combustion chemistry, high-temperature hot combustion airflow is formed and is discharged out of the combustion chamber through the combustion chamber outlet 4;
wherein, along the main aspect of flowing of gas in the flame tube, the mainstream direction for short, describe the cross-sectional structure shape of flame tube:
the outer wall 11 of the flame tube consists of a main combustion section 23, a vertical afterburning section 22 and a horizontal mixing section 21; the jet hole group comprises a first jet hole 13, a second jet hole 12, a third jet hole 11, a fourth jet hole 16, a fifth jet hole 15 and a sixth jet hole 14;
the main combustion section 23 consists of a horizontal section and an arc transition section along the main flow direction of the outer wall 11 of the flame tube; the vertical afterburning section 22 is formed of a vertically straight structure; the blending section 21 is a combined structure of a straight section and an inclined section which are close to a combustion outlet; the three sections are of an integral structure and do not need to be connected; the first jet hole 13 is positioned in the transition section area of the main combustion section 23, the second jet hole 12 is positioned at the upper part of the vertical afterburning section 22, and the third jet hole 11 is positioned in the connecting area of the straight section and the inclined section of the horizontal blending section 21;
the inner wall 5 of the flame tube consists of a pre-combustion section 24, a second post-combustion section 25 and a second mixing section 26;
the pre-combustion section 24 is composed of a lower straight structure, a vertical structure and an upper straight structure, which are in transition through arc sections, and the three are integrated without connection; in the precombustion section 24, the length ratio of the lower straight structure, the vertical structure and the upper straight structure is 1.3: 1.2: 1; the fourth jet holes 16 are distributed in an upper straight structure with a larger radius; the second afterburning section 25 is an arc section and plays a role of connecting the pre-burning section and the mixing section, and meanwhile, the fifth jet holes 15 are distributed in the middle radius area of the arc section; the second mixing section 26 is composed of an arc section structure and an inclined section structure, and the sixth jet hole 14 is located in a transition area of the arc section structure and the inclined section structure.
The number distribution of the first jet hole 13, the second jet hole 12, the third jet hole 11, the fourth jet hole 16, the fifth jet hole 15 and the sixth jet hole 14 in the jet hole group is a multiple of 6; the precise position of the holes is determined according to the tissue requirements of the flow field structure; the number of the divergent cooling holes is determined according to the area of the holes;
the lower straight structure, the vertical structure and the upper straight structure of the pre-combustion section 24 of the inner wall 5 of the flame tube are matched to form a first vortex system structure 301, so that the functions of mixing and pre-combustion are achieved;
the combustion chamber inlet 1 and the combustion chamber outlet 4 are used for mixing completely combusted high-temperature gas, so that the uniformity of a temperature field at the outlet of the combustion chamber is ensured;
the inner wall 5 of the flame tube, the rear casing 6 of the combustion chamber and the outer casing 2 of the combustion chamber act together, and a second vortex system structure 302 and a third vortex system structure 303 are formed through the shearing action formed in the opposite direction of the jet flow columns, so that the main combustion and the afterburning are respectively realized.
The formation of the first vortex system structure 301 comes from the cooperation between the fourth jet hole 16 and the precombustion section 24, that is, the jet flow of the fourth jet hole 16 forms stagnation flow by impacting the wall surface of the precombustion section 24, so that the jet flow direction is changed, a straight jet flow is formed, and peripheral gas is injected, so that the formation of the first vortex system structure 301 is promoted;
similarly, the second vortex structure 302 forms the relative shearing and injection action of the jet flow from the fifth jet hole 15 and the first jet hole 13;
the third vortex structure 303 is formed by the common shearing and injection action of the jet flows from the second jet hole 12 and the first jet hole 13.
(III) advantageous effects
Compared with the prior art, the invention has the following remarkable characteristics:
(1) through the reasonable design of the jet hole, two large-scale vortex system structures are formed at the head of the flame tube, the large-scale vortex system structures belong to the head area of the flame tube, and the vortex system size and the geometrical size of the characteristic structure of the flame tube are in the same order of magnitude.
(2) Through the reasonable design of the jet holes, a large-scale vortex system structure which can supplement combustion and mix with the flame tube is formed in the radial outlet area of the flame tube, and the size of the large-scale vortex system structure is in the same order of magnitude as the size of the characteristic structure of the flame tube.
(3) The ratio of the axial length to the radial height of the flame tube is less than 1.
(4) The head space of the flame tube consists of a first vortex system structure and a second vortex system structure, wherein the oil-gas ratio in the first vortex system structure belongs to rich oil combustion, and the oil-gas ratio in the second vortex system structure is very small and belongs to lean oil combustion.
(5) The overall structure of the flame tube is C-shaped.
The inner wall and the end wall of the flame tube are connected together in a welding mode and then can be fixed on a high-pressure turbine guider or a casing of an engine through threaded connection; the outer wall is fixed on the engine casing in a threaded connection mode. This scheme combustion process has obvious RQL characteristic, and just can effectively improve combustion efficiency to traditional baffling burning flame tube, reduces the combustion pollution and discharges, and compact structure.
Drawings
FIG. 1 is a baffled flame tube configuration.
FIG. 2 is a characteristic view of the periodic structure of the combustion chamber 1/18.
FIG. 3 is a schematic view of the structure of the flame tube. The direction indicated by the broad curved arrow in the figure is the main flow direction of the gas in the flame tube, which is called the main flow direction for short.
Fig. 4 is a view showing the structure of the flow field inside the combustor basket. FIG. 4 shows the distribution of the vortex structure inside the combustion chamber. As can be seen from the figure, the positions and the diameters of the jet holes which are reasonably arranged in the invention can form the three-vortex-system structure in combination with the C-shaped structure of the flame tube.
Detailed Description
In order to make the objects, contents, and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
The research on low-pollution and low-emission turbine engine combustors at home and abroad has generally proved that the combustion organization structure with RQL (rich/fast extinction/lean (RQL) combustion technology) characteristics can effectively reduce the emission of combustion pollutants. Therefore, the scheme designs the flame tube scheme with the C-shaped structure according to the combustion mechanism.
Thus, the present invention provides a flame tube for combustion of a three-turbine structure suitable for advanced low-pollution turbine engines, as shown in fig. 2 to 4, comprising: the device comprises a combustion chamber inlet 1, a combustion chamber outer casing 2, a combustion chamber inner ring airflow channel 3, a combustion chamber outlet 4, a flame tube inner wall 5, a combustion chamber rear casing 6, a combustion chamber inner casing rear section 7, an oil thrower 8, a combustion chamber inner casing front section 9, a combustion chamber front casing 10 and a flame tube outer wall 11; wherein,
the inner ring airflow channel 3 of the combustion chamber is connected with the inner wall and the outer wall of the flame tube in a welding mode;
the oil thrower 8 is fixed on a rotating shaft of an engine through friction force in a form of compressing two ends and rotates at the same rotating speed along with the rotating shaft;
the inner wall 5 of the flame tube and the outer wall 11 of the flame tube are connected in a lap joint mode, and the outer wall 11 of the flame tube is fixed in a downstream static structure through a flange;
the inner wall 5 of the flame tube and the outer wall 11 of the flame tube are provided with jet hole groups with an organization vortex system structure, the aperture of the jet holes in the jet hole groups is distributed between 5mm and 10mm, in addition, the inner wall 5 of the flame tube and the outer wall 11 of the flame tube are also provided with divergent cooling holes with the diameter of 0.5 to 0.7mm, and the opening direction of the divergent cooling holes and the normal direction of the wall surface of the flame tube form an angle of 60 to 70 degrees; the density distribution of the divergent cooling holes is 5-8/cm2(ii) a Air can enter the inner part of the flame tube through the divergent cooling holes to perform combustion chemical reaction with the fuel;
as shown in FIG. 3, the combustor inlet air flows from the combustor inlet 1 into the flow path between the combustor outer casing 2 and the liner outer wall 11; then, the flame tube is divided into two paths, one path passes through an inner ring airflow channel 3 of the combustion chamber, and the other path passes through a channel formed among a front section 9 of a casing in the combustion chamber, a front casing 10 of the combustion chamber and an outer wall 11 of the flame tube;
the air which passes through the annular air flow channel 3 in the combustion chamber is divided again, enters a channel formed between the inner wall 5 of the flame tube and the rear casing 6 and the rear section 7 of the combustion chamber casing, and then enters the interior of the flame tube through a jet hole arranged on the inner wall 5 of the flame tube to perform combustion chemical reaction with the fuel; the airflow passing through the channel among the front section 9 of the casing in the combustion chamber, the front casing 10 of the combustion chamber and the outer wall 11 of the flame tube enters the interior of the flame tube through the jet hole and the divergent cooling hole on the outer wall 11 of the flame tube to perform combustion chemical reaction with fuel;
the oil thrower 8 is used for atomizing fuel in the oil thrower in a rotating mode and spraying the fuel into the flame tube so as to participate in the combustion chemical reaction; after the air and the fuel are subjected to combustion chemistry, high-temperature hot combustion airflow is formed and is discharged out of the combustion chamber through the combustion chamber outlet 4;
wherein, along the main aspect of flowing of gas in the flame tube, the mainstream direction for short, describe the cross-sectional structure shape of flame tube:
the outer wall 11 of the flame tube consists of a main combustion section 23, a vertical afterburning section 22 and a horizontal mixing section 21; the jet hole group comprises a first jet hole 13, a second jet hole 12, a third jet hole 11, a fourth jet hole 16, a fifth jet hole 15 and a sixth jet hole 14;
the main combustion section 23 consists of a horizontal section and an arc transition section along the main flow direction of the outer wall 11 of the flame tube; the vertical afterburning section 22 is formed of a vertically straight structure; the blending section 21 is a combined structure of a straight section and an inclined section which are close to a combustion outlet; the three sections are of an integral structure and do not need to be connected; the first jet hole 13 is positioned in the transition section area of the main combustion section 23, the second jet hole 12 is positioned at the upper part of the vertical afterburning section 22, and the third jet hole 11 is positioned in the connecting area of the straight section and the inclined section of the horizontal blending section 21;
the inner wall 5 of the flame tube consists of a pre-combustion section 24, a second post-combustion section 25 and a second mixing section 26;
the pre-combustion section 24 is composed of a lower straight structure, a vertical structure and an upper straight structure, which are in transition through arc sections, and the three are integrated without connection; in the precombustion section 24, the length ratio of the lower straight structure, the vertical structure and the upper straight structure is 1.3: 1.2: 1; the fourth jet holes 16 are distributed in an upper straight structure with a larger radius; the second afterburning section 25 is an arc section and plays a role of connecting the pre-burning section and the mixing section, and meanwhile, the fifth jet holes 15 are distributed in the middle radius area of the arc section; the second mixing section 26 is composed of an arc section structure and an inclined section structure, and the sixth jet hole 14 is located in a transition area of the arc section structure and the inclined section structure.
The number distribution of the holes of the first jet hole 13, the second jet hole 12, the third jet hole 11, the fourth jet hole 16, the fifth jet hole 15 and the sixth jet hole 14 in the jet hole group is multiple of 6, and each row of holes is distributed between 36-48; the precise position of the holes is determined according to the tissue requirements of the flow field structure; the number of the divergent cooling holes is determined according to the area of the holes;
the lower straight structure, the vertical structure and the upper straight structure of the pre-combustion section 24 of the inner wall 5 of the flame tube are matched to form a first vortex system structure 301, so that the functions of mixing and pre-combustion are achieved;
the combustion chamber inlet 1 and the combustion chamber outlet 4 are used for mixing completely combusted high-temperature gas, so that the uniformity of a temperature field at the outlet of the combustion chamber is ensured;
the inner wall 5 of the flame tube, the rear casing 6 of the combustion chamber and the outer casing 2 of the combustion chamber act together, and a second vortex system structure 302 and a third vortex system structure 303 are formed through the shearing action formed in the opposite direction of the jet flow columns, so that the main combustion and the afterburning are respectively realized.
As shown in fig. 2-4, the main flow path inside the flame tube is in a C-shaped structure, and three vortex structures in the same order of magnitude as the geometric dimension of the combustion chamber are organized inside the flame tube, so that the combustion chamber is named as a C-shaped three-vortex structure combustion chamber herein.
The formation of the first vortex system structure 301 comes from the cooperation between the fourth jet hole 16 and the precombustion section 24, that is, the jet flow of the fourth jet hole 16 forms stagnation flow by impacting the wall surface of the precombustion section 24, so that the jet flow direction is changed, a straight jet flow is formed, and peripheral gas is injected, so that the formation of the first vortex system structure 301 is promoted;
similarly, the second vortex structure 302 forms the relative shearing and injection action of the jet flow from the fifth jet hole 15 and the first jet hole 13;
the third vortex structure 303 is formed by the common shearing and injection action of the jet flows from the second jet hole 12 and the first jet hole 13.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (1)
1. A flame cartridge for combustion of the three-turbine system of an advanced low pollution turbine engine, comprising: the device comprises a combustion chamber inlet (1), a combustion chamber outer casing (2), a combustion chamber inner ring air flow channel (3), a combustion chamber outlet (4), a flame tube inner wall (5), a combustion chamber rear casing (6), a combustion chamber inner casing rear section (7), an oil thrower (8), a combustion chamber inner casing front section (9), a combustion chamber front casing (10) and a flame tube outer wall (11); wherein,
the inner ring airflow channel (3) of the combustion chamber is connected with the inner wall and the outer wall of the flame tube in a welding mode;
the oil thrower (8) is fixed on a rotating shaft of an engine in a form that two ends are compressed, and rotates at the same rotating speed along with the rotating shaft;
the inner wall (5) of the flame tube and the outer wall (11) of the flame tube are connected in a lap joint mode, and the outer wall (11) of the flame tube is fixed in a downstream static structure through a flange;
jet hole groups with an organization vortex system structure are arranged on the inner wall (5) and the outer wall (11) of the flame tube, the aperture of the jet holes in the jet hole groups is distributed between 5mm and 10mm, in addition, divergent cooling holes with the diameter of 0.5 to 0.7mm are also arranged on the inner wall (5) and the outer wall (11) of the flame tube, and the opening direction of the divergent cooling holes and the normal direction of the wall surface of the flame tube form an angle of 60 to 70 degrees; the density distribution of the divergent cooling holes is 5-8/cm2(ii) a Air can enter the inner part of the flame tube through the divergent cooling holes to perform combustion chemical reaction with the fuel;
the air at the inlet of the combustion chamber flows into a flow channel between the outer casing (2) of the combustion chamber and the outer wall (11) of the flame tube from the inlet (1) of the combustion chamber; then, the gas is divided into two paths, one path passes through an inner ring gas flow channel (3) of the combustion chamber, and the other path passes through a channel formed among a front section (9) of a casing in the combustion chamber, a front casing (10) of the combustion chamber and an outer wall (11) of the flame tube;
the air which passes through the annular air flow channel (3) in the combustion chamber is divided again and enters a channel formed between the inner wall (5) of the flame tube and the rear casing (6) and the rear section (7) of the combustion chamber casing, and then enters the interior of the flame tube through the jet holes formed in the inner wall (5) of the flame tube to perform combustion chemical reaction with the fuel; the airflow passing through the channel among the front section (9) of the casing in the combustion chamber, the front casing (10) of the combustion chamber and the outer wall (11) of the flame tube enters the interior of the flame tube through the jet holes and the divergent cooling holes on the outer wall (11) of the flame tube to perform combustion chemical reaction with fuel;
the oil thrower (8) is used for atomizing fuel in the oil thrower in a rotating mode and spraying the atomized fuel into the flame tube so as to participate in the combustion chemical reaction; after the air and the fuel are subjected to combustion chemistry, high-temperature hot combustion airflow is formed and is discharged out of the combustion chamber through a combustion chamber outlet (4);
the cross-sectional structural shape of the flame tube is described along the main flowing aspect of the gas in the flame tube, which is called main flow direction for short:
the outer wall (11) of the flame tube consists of a main combustion section (23), a vertical afterburning section (22) and a horizontal mixing section (21); the jet hole group comprises a first jet hole (13), a second jet hole (12), a third jet hole (11), a fourth jet hole (16), a fifth jet hole (15) and a sixth jet hole (14);
the main combustion section (23) consists of a horizontal section and an arc transition section along the main flow direction of the outer wall (11) of the flame tube; the vertical afterburning section (22) is formed by a straight structure in the vertical direction; the blending section (21) is a combined structure of a straight section and an inclined section which are close to a combustion outlet; the three sections are of an integral structure and do not need to be connected; the first jet hole (13) is positioned in the transition section area of the main combustion section (23), the second jet hole (12) is positioned at the upper part of the vertical afterburning section (22), and the third jet hole (11) is positioned in the junction area of the straight section and the inclined section of the horizontal blending section (21);
the inner wall (5) of the flame tube consists of a pre-combustion section (24), a second post-combustion section (25) and a second mixing section (26);
the pre-combustion section (24) consists of a lower straight structure, a vertical structure and an upper straight structure, which are in transition through an arc section and are integrated without connection; in the precombustion section (24), the length ratio of the lower straight structure, the vertical structure and the upper straight structure is 1.3: 1.2: 1; the fourth jet holes (16) are distributed in an upper straight structure with a larger radius; the second afterburning section (25) is an arc section and plays a role of connecting the pre-burning section and the mixing section, and meanwhile, the fifth jet holes (15) are distributed in the middle radius area of the arc section; the second mixing section (26) is composed of an arc section structure and an inclined section structure, and the sixth jet hole (14) is positioned in a transition area of the arc section structure and the inclined section structure;
the number distribution of the first jet hole (13), the second jet hole (12), the third jet hole (11), the fourth jet hole (16), the fifth jet hole (15) and the sixth jet hole (14) in the jet hole group is a multiple of 6; the precise position of the holes is determined according to the tissue requirements of the flow field structure; the number of the divergent cooling holes is determined according to the area of the holes;
the lower straight structure, the vertical structure and the upper straight structure of the pre-combustion section (24) of the inner wall (5) of the flame tube are matched to form a first vortex system structure (301) to play roles in mixing and pre-combustion;
the combustion chamber inlet (1) and the combustion chamber outlet (4) are used for mixing completely combusted high-temperature gas, so that the uniformity of a temperature field at the outlet of the combustion chamber is ensured;
the inner wall (5) of the flame tube, the rear casing (6) of the combustion chamber and the outer casing (2) of the combustion chamber act together, and a second vortex system structure (302) and a third vortex system structure (303) are formed through the shearing action formed in the opposite direction of the jet flow columns, so that the main combustion and the afterburning are respectively realized;
the first vortex system structure (301) is formed by the cooperation of the fourth jet hole (16) and the pre-combustion section (24), namely, the jet flow of the fourth jet hole (16) forms stagnation flow by impacting the wall surface of the pre-combustion section (24), so that the jet flow direction is changed, a straight jet flow is formed, peripheral gas is jetted, and the formation of the first vortex system structure (301) is promoted;
in the same way, the second vortex system structure (302) forms relative shearing and injection action of jet flows from the fifth jet hole (15) and the first jet hole (13);
the third vortex system structure (303) forms the joint shearing and injection action of the jet flow from the second jet hole (12) and the first jet hole (13).
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CN201610968110.6A CN106524225B (en) | 2016-10-31 | 2016-10-31 | The three vortex system tissue burned flame cylinders suitable for advanced low pollution turbogenerator |
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CN201610968110.6A CN106524225B (en) | 2016-10-31 | 2016-10-31 | The three vortex system tissue burned flame cylinders suitable for advanced low pollution turbogenerator |
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US10976053B2 (en) * | 2017-10-25 | 2021-04-13 | General Electric Company | Involute trapped vortex combustor assembly |
CN107906560B (en) * | 2017-11-09 | 2019-11-26 | 四川航天中天动力装备有限责任公司 | A kind of standing vortex declines type gas turbine combustors |
CN108167864A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | Burner inner liner and high-pressure turbine guider integral structure |
CN111059575B (en) * | 2018-10-16 | 2022-05-10 | 中发天信(北京)航空发动机科技股份有限公司 | Turbojet engine flame tube shell |
CN114491875B (en) * | 2022-04-07 | 2022-07-26 | 中国航发四川燃气涡轮研究院 | Porous laminate profile design method and porous laminate flame tube |
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