Combination cooling structure of flame tube of backflow combustion chamber and gas turbine engine

Abstract

The invention discloses a backflow combustor flame tube combined cooling structure and a gas turbine engine, the backflow combustor flame tube combined cooling structure comprises a head circular ring and a first Z-shaped gas film ring, a flame tube inner ring and a flame tube outer ring are arranged at the two ends of the head circular ring respectively, and a large elbow is arranged at the end, away from the head circular ring, of the flame tube outer ring; the end, away from the head circular ring, of the flame tube inner ring is provided with a small bent pipe, the first Z-shaped gas film ring comprises a first part, a second part and a third part which are sequentially connected in a Z shape, the first part is connected with the flame tube outer ring, the third part is connected with the large bent pipe, and the second part is provided with a first cooling hole in the thickness direction of the second part. The projection of the first cooling hole in the axial direction of the first cooling hole falls on the inner side of the large bent pipe. The overall strength and rigidity of the flame tube are improved on the basis that the cooling effect of the part, right facing the main combustion area, of the large bent pipe is improved, and the wall temperature control requirement is met.

Description

Technical Field

[0001] The invention relates to the technical field of flame tube cooling, and in particular to a reflow combustion chamber flame tube combined cooling structure and a gas turbine engine. Background Art

[0002] The recirculation combustion chamber is widely used in small and medium-sized aviation gas turbine engines because of its potential in shortening the axial length of the engine rotor. Generally speaking, the recirculation combustion chamber is mainly composed of a diffuser, a shell, a flame tube, a fuel nozzle and an igniter. The flame tube is a key component of the recirculation combustion chamber. The fuel burns inside the flame tube to produce high-temperature and high-pressure gas to drive the turbine to work. As the thermal cycle parameters of small and medium-sized aviation gas turbine engines gradually increase, the average temperature of the main combustion zone gas near the flame tube head is as high as (2000-2500) K. In order to meet the use requirements of the flame tube, the full divergence cooling technology is usually used to design the flame tube with a smaller thickness (generally within 2mm) and equal wall thickness. Multiple divergence holes with a certain angle are arranged on the flame tube wall according to a certain rule. The cold air in the cavity between the combustion chamber shell and the flame tube enters the high-temperature gas side of the flame tube from the divergence hole, and can flow along the high-temperature wall surface of the flame tube (i.e., the inner wall surface of the flame tube) to achieve cooling protection for the flame tube.

[0003] The existing flame tube used in the reflow combustion chamber usually includes a head ring, and the two ends of the head ring are respectively provided with a flame tube outer ring and a flame tube inner ring, and a large bend pipe and a small bend pipe are respectively provided at the ends of the flame tube outer ring and the flame tube inner ring away from the head ring; the connection between the head ring and the flame tube outer ring is located near the main combustion zone and the large bend pipe part is facing the inner side of the main combustion zone, so that the heat load intensity of the above-mentioned local position is high, and the above-mentioned fully divergent cooling structure cannot meet the wall temperature control requirements, which may easily cause poor cooling of the local part of the flame tube (the part of the flame tube outer ring close to the main combustion zone and the part of the large bend pipe facing the main combustion zone) to cause local wall deformation or cracks. Summary of the invention

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defect that the fully divergent cooling structure applied to the flame tube of the recirculation combustion chamber in the prior art cannot meet the wall temperature control requirements, and easily causes local poor cooling of the flame tube resulting in local wall deformation or cracks, thereby providing a recirculation combustion chamber flame tube combined cooling structure and a gas turbine engine.

[0005] In a first aspect, the present invention provides a flame tube combined cooling structure of a reflow combustion chamber, comprising a head ring, a flame tube outer ring, a flame tube inner ring, a large curved pipe and a small curved pipe, wherein the flame tube inner ring and the flame tube outer ring are respectively arranged at two ends of the head ring, the large curved pipe is arranged at one end of the flame tube outer ring away from the head ring, and the small curved pipe is arranged at one end of the flame tube inner ring away from the head ring, and further comprising:

[0006] A first Z-shaped air film ring is arranged between the outer ring of the flame tube and the large curved pipe, wherein the first Z-shaped air film ring comprises a first portion, a second portion and a third portion connected in sequence, wherein the first portion is connected to the outer ring of the flame tube, the third portion is connected to the large curved pipe, and the second portion is provided with a first cooling hole along the thickness direction of the second portion, and the projection of the first cooling hole along the axial direction of the first cooling hole falls on the inner side of the large curved pipe;

[0007] The first mechanical air film ring includes a first connecting portion arranged between the outer ring of the flame tube and the head ring and a second connecting portion arranged on the inner side of the first connecting portion, a first gap is surrounded between the first connecting portion and the second connecting portion, and a second cooling hole is arranged in the first connecting portion at a position corresponding to the first gap and penetrating along the thickness direction of the first connecting portion.

[0008] A combined cooling structure for a flame tube in a reflow combustion chamber according to the present invention has at least the following technical effects:

[0009] A first Z-shaped air film ring is provided between the outer ring of the flame tube and the large bend pipe, and a first cooling hole is provided through the second part of the first Z-shaped air film ring, so that cold air can pass through the first cooling hole and flow closely along the inner side of the large bend pipe along one end facing the outer ring of the flame tube to the end away from the outer ring of the flame tube, and cooperate with the original divergent holes of the large bend pipe to further promote the wall-adhering effect of the divergent cooling air film of the inner side of the large bend pipe away from the outer ring of the flame tube downstream area (that is, the part of the large bend pipe facing the main combustion zone), so that the divergent cooling effect of this part is further enhanced and the wall temperature gradient of the large bend pipe is reduced; a first mechanical air film ring is provided between the outer ring of the flame tube and the head ring, and a second cooling hole is provided through the first connecting part of the first mechanical air film ring, so that cold air can pass through the second cooling hole and contact the second connecting After the connection, the flow direction changes and flows along the first gap, and flows along the inner side surface of the outer ring of the flame tube along the end facing the head ring to the end away from the head ring. Combined with the original divergent holes in the outer ring of the flame tube, the wall-adhering effect of the divergent cooling air film in the area inside the outer ring of the flame tube close to the main combustion zone is further promoted, so that the divergent cooling effect of this part is further enhanced, and the wall temperature gradient of the outer ring of the flame tube is reduced; at the same time, the first Z-shaped air film ring and the first mechanical air film ring respectively make the wall thickness of the connection between the outer ring of the flame tube and the large bend pipe and the connection between the outer ring of the flame tube and the head ring thicker, so as to improve the cooling effect of the local area with high heat load intensity of the flame tube to meet the wall temperature control requirements, and improve the overall strength and rigidity of the flame tube. It is particularly suitable for reflow combustion chambers with relatively large size and aerodynamic force.

[0010] In an optional embodiment, a second mechanical air film ring is further included, which includes a third connecting portion arranged between the inner ring of the flame tube and the head ring and a fourth connecting portion arranged inside the third connecting portion, a second gap is enclosed between the third connecting portion and the fourth connecting portion, and a third cooling hole is arranged at a position of the third connecting portion corresponding to the second gap along the thickness direction of the third connecting portion.

[0011] In an optional embodiment, a third mechanical air film ring is arranged between the inner ring of the flame tube and the small bend pipe, and the third mechanical air film ring includes a fifth connecting part and a sixth connecting part, and the sixth connecting part is arranged at an interval on the inward side of the fifth connecting part, and the projection of the fifth connecting part along the thickness direction of the fifth connecting part at least partially overlaps with the sixth connecting part, one end of the fifth connecting part is connected to the small bend pipe, and the other end is connected to the sixth connecting part through a first mounting part, and the first mounting part is provided with a fourth cooling hole along the thickness direction of the first mounting part; the sixth connecting part is connected to the inner ring of the flame tube.

[0012] In an optional embodiment, a fourth mechanical air film ring is arranged between the inner ring of the flame tube and the small bend pipe, and the fourth mechanical air film ring includes a seventh connecting part and an eighth connecting part, and the eighth connecting part is arranged at an interval on the inward side of the seventh connecting part, and the eighth connecting part and the seventh connecting part are connected by a second mounting part, and a third gap is formed between the seventh connecting part, the second mounting part and the eighth connecting part, and the small bend pipe is arranged in the third gap and abuts against the side of the seventh connecting part facing the eighth connecting part, and the second mounting part is provided with a fifth cooling hole penetrating along the thickness direction of the second mounting part; the eighth connecting part is connected to the inner ring of the flame tube.

[0013] In an optional embodiment, a second Z-shaped air film ring is arranged between the inner ring of the flame tube and the small bend pipe, and the second Z-shaped air film ring includes a fourth part, a fifth part and a sixth part connected in sequence, and the fourth part is located on the inward side of the sixth part; the fourth part is connected to the inner ring of the flame tube, the sixth part is connected to the small bend pipe, and the fifth part is provided with a sixth cooling hole along the length direction of the sixth part.

[0014] In an optional embodiment, a turbine is arranged between one end of the small curved pipe away from the inner ring of the flame tube and one end of the large curved pipe away from the outer ring of the flame tube, a fifth mechanical air film ring is arranged between the small curved pipe and the turbine, the fifth mechanical air film ring comprises a ninth connecting portion and a tenth connecting portion, the tenth connecting portion is located on the inner side of the ninth connecting portion, a projection of the ninth connecting portion along the thickness direction of the ninth connecting portion at least partially overlaps with the tenth connecting portion, one end of the ninth connecting portion is connected to the turbine, and the other end is connected to the tenth connecting portion through a third mounting portion, the ninth connecting portion, the third mounting portion and the tenth connecting portion enclose a fourth gap, the projection of the fourth gap along the length direction of the fourth gap falls on the turbine, a seventh cooling hole is penetrated through the position of the ninth connecting portion corresponding to the fourth gap, and the tenth connecting portion is connected to the small curved pipe;

[0015] Or, a turbine is arranged between one end of the small bend pipe away from the inner ring of the flame tube and one end of the large bend pipe away from the outer ring of the flame tube, a third Z-shaped air film ring is arranged between the inner ring of the flame tube and the turbine, the third Z-shaped air film ring includes a seventh part, an eighth part and a ninth part connected in sequence, the ninth part is located on the inward side of the seventh part; the seventh part is connected to the turbine, the ninth part is connected to the small bend pipe, and the eighth part is provided with an eighth cooling hole passing through the seventh part along the length direction of the seventh part.

[0016] In an optional embodiment, a transition pipe is provided between the large bend pipe and the turbine, and a curvature radius of the transition pipe is smaller than a curvature radius of the large bend pipe.

[0017] In an optional embodiment, a fourth Z-shaped air film ring is arranged between the large bend pipe and the transition pipe, and the fourth Z-shaped air film ring includes a tenth part, an eleventh part and a twelfth part connected in sequence, and the twelfth part is located on the inward side of the tenth part; the tenth part is connected to the transition pipe, the twelfth part is connected to the large bend pipe, and the eleventh part is provided with a ninth cooling hole along the length direction of the tenth part.

[0018] In an optional embodiment, a sixth mechanical air film ring is arranged between the large bend pipe and the transition pipe, and the sixth mechanical air film ring includes an eleventh connecting part and a twelfth connecting part, the twelfth connecting part is located on the inner side of the eleventh connecting part, and the projection of the eleventh connecting part along the thickness direction of the eleventh connecting part at least partially overlaps with the twelfth connecting part, one end of the eleventh connecting part is connected to the transition pipe, and the other end is connected to the twelfth connecting part through a fourth mounting part, the fourth mounting part is penetrated by a tenth cooling hole, the projection of the tenth cooling hole along the axial direction of the tenth cooling hole falls on the inner side of the transition pipe, and the twelfth connecting part is connected to the large bend pipe.

[0019] In a second aspect, the present invention further provides a gas turbine engine, comprising the reflow combustion chamber flame tube combined cooling structure provided in the first aspect above.

[0020] Because the gas turbine engine includes a recirculation combustor flame liner combined cooling structure, which has the same beneficial effects as the recirculation combustor flame liner combined cooling structure, it will not be described in detail here. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 This is a schematic structural diagram of a reflow combustion chamber flame tube combined cooling structure of this embodiment;

[0023] Figure 2 for Figure 1 Schematic diagram of the decomposition of the structure of the middle part;

[0024] Figure 3 for Figure 2 Schematic diagram of the structure of the first Z-shaped air film ring;

[0025] Figure 4 for Figure 2 The structural diagram of the first mechanical air film ring;

[0026] Figure 5 for Figure 2 A schematic diagram of the structure of the second mechanical air film ring;

[0027] Figure 6 for Figure 2 Schematic diagram of the structure of the third mechanical air film ring;

[0028] Figure 7 for Figure 2 Schematic diagram of the structure of the fourth Z-shaped air film ring

[0029] Figure 8 It is a structural schematic diagram of a fifth mechanical air film ring in a combined cooling structure of a reflow combustion chamber flame tube of this embodiment;

[0030] Fig. 9 It is a schematic structural diagram of a third mechanical air film ring disposed between the inner ring of the flame tube and the small curved pipe in a flame tube combined cooling structure of a reflow combustion chamber of this embodiment;

[0031] Fig.10 It is a structural schematic diagram of a fourth mechanical air film ring disposed between the inner ring of the flame tube and the small curved pipe in a flame tube combined cooling structure of a reflow combustion chamber of this embodiment;

[0032] Fig.11 It is a schematic structural diagram of a second Z-shaped air film ring disposed between the inner ring of the flame tube and the small curved pipe in a flame tube combined cooling structure of a reflow combustion chamber of this embodiment;

[0033] Fig.12 It is a schematic cross-sectional structure diagram of a head ring in a combined cooling structure of a flame tube in a reflow combustion chamber of this embodiment;

[0034] Fig.13 It is a schematic cross-sectional structure diagram of a large curved pipe in a reflow combustion chamber flame tube combined cooling structure of this embodiment.

[0035] Description of reference numerals:

[0036] 100-head ring, 110-first cavity;

[0037] 200-flame tube outer ring;

[0038] 300-flame tube inner ring;

[0039] 400-large elbow, 410-second cavity;

[0040] 500- small elbow;

[0041] 610-first Z-type air film ring, 611-first part, 612-second part, 613-third part, 620-first mechanical air film ring, 621-first connecting part, 622-second connecting part, 623-first gap, 630-second mechanical air film ring, 631-third connecting part, 632-fourth connecting part, 633-second gap, 640-third mechanical air film ring, 641-fifth connecting part, 642-sixth connecting part, 643-first mounting part, 650-fourth mechanical air film ring, 660-second Z-type air film ring, 670-fifth mechanical air film ring, 671-ninth connecting part, 672-tenth connecting part, 673-third mounting part, 674-fourth gap, 675-seventh cooling hole, 680-fourth Z-type air film ring, 681-tenth part, 682-eleventh part, 683-twelfth part;

[0042] 700 - Turbine;

[0043] 800-transition pipe;

[0044] 910-main combustion zone, 920-combustion channel cavity. DETAILED DESCRIPTION

[0045] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0046] In the description of this embodiment, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing this embodiment and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting this embodiment. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0047] In the description of this embodiment, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this embodiment can be understood according to specific circumstances.

[0048] In the related technology, the flame tube used in the reflow combustion chamber usually includes a head ring, and the two ends of the head ring are respectively provided with a flame tube outer ring and a flame tube inner ring, and a large bend pipe and a small bend pipe are respectively provided at the ends of the flame tube outer ring and the flame tube inner ring away from the head ring; with the gradual increase of thermal cycle parameters of small and medium-sized aviation gas turbine engines, the average temperature of the main combustion zone gas near the flame tube head is as high as (2000-2500)K. In order to meet the use requirements of the flame tube, the full divergence cooling technology is usually used to design the flame tube with a smaller thickness (generally within 2mm) and equal wall thickness, and a plurality of divergence holes with a certain angle are arranged on the flame tube wall according to a certain pattern. The cold air in the cavity between the combustion chamber shell and the flame tube enters the high-temperature gas side of the flame tube from the divergence holes, and can flow along the high-temperature wall surface of the flame tube (i.e., the inner wall surface of the flame tube), thereby realizing cooling protection of the flame tube. However, the connection between the head ring and the outer ring of the flame tube is located near the main combustion zone and the inner side of the large bend pipe facing the main combustion zone, which makes the heat load intensity of the above-mentioned local position high. The above-mentioned full divergence cooling structure cannot meet the wall temperature control requirements, which easily causes the local flame tube (the part of the outer ring of the flame tube close to the main combustion zone and the part of the large bend pipe facing the main combustion zone) to be poorly cooled, resulting in local wall deformation or cracks; related technologies increase the number of local divergence holes to increase the amount of cold air, or design the divergence holes to have a smaller inclination angle or a tangential compound angle to improve the cooling effect, but it will cause the overall rigidity and strength of the flame tube to be relatively poor. When applied to a reflow combustion chamber with relatively large size and aerodynamic force, the flame tube is prone to deformation due to stress or difficulty in ensuring the size, affecting the reliability of the combustion chamber structure and performance. In order to solve the above-mentioned technical defects, a reflow combustion chamber flame tube combined cooling structure and a gas turbine engine according to an embodiment of the present invention are provided.

[0049] Combine the following Figures 1 to 13 , describing an embodiment of the present invention.

[0050] According to a first aspect of an embodiment of the present invention, a flame tube combined cooling structure of a reflow combustion chamber is provided, comprising a head ring 100, a flame tube outer ring 200, a flame tube inner ring 300, a large curved pipe 400 and a small curved pipe 500, wherein the flame tube inner ring 300 and the flame tube outer ring 200 are respectively arranged at two ends of the head ring 100, the large curved pipe 400 is arranged at one end of the flame tube outer ring 200 away from the head ring 100, and the small curved pipe 500 is arranged at one end of the flame tube inner ring 300 away from the head ring 100, and the reflow combustion chamber flame tube combined cooling structure also includes a first Z-shaped air film ring 610 and a first mechanical air film ring 620, wherein the first Z-shaped air film ring 610 is arranged between the flame tube outer ring 200 and the large curved pipe 400, and the first Z-shaped air film ring 610 includes a first part 611, a second part 612 and a third part 613 which are sequentially connected in a Z shape. 3. The first part 611 is connected to the outer ring 200 of the flame tube, the third part 613 is connected to the large bend pipe 400, the second part 612 is provided with a first cooling hole along the thickness direction of the second part 612, and the projection of the first cooling hole along the axial direction of the first cooling hole falls on the inner side of the large bend pipe 400; the first mechanical air film ring 620 includes a first connecting part 621 provided between the outer ring 200 of the flame tube and the head ring 100 and a second connecting part 622 provided on the inner side of the first connecting part 621, a first gap 623 is formed between the first connecting part 621 and the second connecting part 622, a second cooling hole is provided through the first connecting part 621 at a position corresponding to the first gap 623 along the thickness direction of the first connecting part 621; the projection of the first gap 623 along the length direction of the first gap 623 falls on the inner wall of the inner ring 300 of the flame tube.

[0051] The combined cooling structure of the flame tube of the reflow combustion chamber of the present embodiment is provided with a first Z-shaped air film ring 610 between the flame tube outer ring 200 and the large curved pipe 400, and a first cooling hole is provided through the second portion 612 of the first Z-shaped air film ring 610, so that the cold air can pass through the first cooling hole and flow along one end of the flame tube outer ring 200 toward the end away from the flame tube outer ring 200, close to the inner side of the large curved pipe 400, and cooperate with the original divergent holes of the large curved pipe 400 to further promote The wall-adhering effect of the divergent cooling air film of the downstream area of ​​the inner side of the large bend pipe 400 away from the outer ring 200 of the flame tube (that is, the part of the large bend pipe 400 facing the main combustion zone 910) is enhanced, so that the divergent cooling effect of this part is further enhanced, and the wall temperature gradient of the large bend pipe 400 is reduced; a first mechanical air film ring 620 is provided between the outer ring 200 of the flame tube and the head ring 100, and a second cooling hole is penetrated in the first connecting part 621 of the first mechanical air film ring 620, so that the cooling air After passing through the second cooling hole and contacting the second connecting part 622, the flow direction changes and flows along the first gap 623, and flows along the inner side surface of the flame tube outer ring 200 along the end facing the head ring 100 to the end away from the head ring 100, and cooperates with the original divergent holes of the flame tube outer ring 200 to further promote the wall-adhering effect of the divergent cooling air film in the area inside the flame tube outer ring 200 close to the main combustion zone 910, so that the divergent cooling effect of this part is further enhanced, and the wall temperature gradient of the flame tube outer ring 200 is reduced; at the same time, the first Z-shaped air film ring 610 and the first mechanical air film ring 620 respectively make the wall thickness of the connection between the flame tube outer ring 200 and the large bend pipe 400 and the connection between the flame tube outer ring 200 and the head ring 100 thicker, so as to improve the cooling effect of the local area with high thermal load intensity of the flame tube to meet the wall temperature control requirements, and improve the overall strength and rigidity of the flame tube, which is particularly suitable for reflow combustion chambers with relatively large size and aerodynamic force.

[0052] It should be noted that Figure 1 , Fig. 9 , Fig.10 , Fig.11 , Fig.12 and Fig.13 The direction indicated by the thin arrow is the direction of the cold air. Figure 1 The direction indicated by the medium thick arrow is the flow direction of the gas.

[0053] It should be noted that in this embodiment, the head ring 100, the flame tube outer ring 200, the flame tube inner ring 300, the large bend pipe 400 and the small bend pipe 500 form a combustion channel cavity 920, and the side of the components in the reflow combustion chamber flame tube combined cooling structure of this embodiment facing the combustion channel cavity 920 is the inner side.

[0054] It should be noted that a plurality of divergent holes with a certain angle are arranged according to a certain pattern on the side walls of the head ring 100, the flame tube outer ring 200, the flame tube inner ring 300, the large bend pipe 400 and the small bend pipe 500, and a first Z-shaped air film ring 610 is provided between the flame tube outer ring 200 and the large bend pipe 400, and a first mechanical air film ring 620 is provided between the flame tube outer ring 200 and the head ring 100. This improves the cooling effect of local areas with high heat load intensity of the flame tube and meets the need for good cooling in the entire range of the flame tube of the high-temperature rise recirculation combustion chamber. The flame tube is particularly suitable for recirculation combustion chambers with relatively large size and aerodynamic force. It is particularly beneficial to improve the thermal cycle parameters of a gas turbine engine equipped with the recirculation combustion chamber flame tube combined cooling structure of this embodiment.

[0055] It should be noted that a cavity is set between the outer side of the reflow combustion chamber flame tube combined cooling structure and the reflow combustion chamber shell in this embodiment, and the cavity is provided with an air inlet for conveying cold air. The cold air enters the combustion channel cavity 920 through the divergent holes and various cooling holes, and flows on the high-temperature inner wall of the flame tube to form a divergent cooling air film to achieve cooling protection for the flame tube.

[0056] Considering that the connection between the flame tube inner ring 300 and the head ring 100 is located near the main combustion zone 910, the heat load intensity of the connection between the flame tube inner ring 300 and the head ring 100 and the area near the main combustion zone 910 of the flame tube inner ring 300 is high, and the wall temperature control requirements cannot be met by simply transporting cold air through the diffuser holes; in order to solve the above problems, Figure 1 , Figure 2 and Figure 5As shown, in some embodiments, the reflow combustion chamber flame tube combined cooling structure also includes a second mechanical air film ring 630, the second mechanical air film ring 630 includes a third connecting portion 631 arranged between the flame tube inner ring 300 and the head ring 100 and a fourth connecting portion 632 arranged on the inner side of the third connecting portion 631, a second gap 633 is surrounded by the third connecting portion 631 and the fourth connecting portion 632, and a third cooling hole is penetrated through the third connecting portion 631 along the thickness direction of the third connecting portion 631 at a position corresponding to the second gap 633; ​​so that the cold air can pass through the third cooling hole and contact the fourth connecting portion 632, and then the flow direction changes and flows along the second gap 633. , and flows along the inner wall of the flame tube inner ring 300 along the end facing the head ring 100 to the end away from the head ring 100, and cooperates with the original divergent holes of the flame tube inner ring 300 to further promote the wall-adhering effect of the divergent cooling air film in the area inside the flame tube inner ring 300 close to the main combustion zone 910, so that the divergent cooling effect of this part is further enhanced, and the wall temperature gradient of the flame tube inner ring 300 is reduced; at the same time, the second mechanical air film ring 630 makes the wall thickness of the connection between the flame tube inner ring 300 and the head ring 100 thicker, so as to improve the cooling effect of the local area with high heat load intensity of the flame tube to meet the wall temperature control requirements, and improve the overall strength and rigidity of the flame tube, which is particularly suitable for reflow combustion chambers with relatively large size and aerodynamic force.

[0057] Considering that the curvature of the profile of the small curved pipe 500 is large, the airflow that enters the combustion channel cavity 920 through the divergent holes of the small curved pipe 500 and adheres to the inner side of the small curved pipe 500 is easily separated from the inner side of the small curved pipe 500, and a good cooling effect cannot be formed; in order to solve the above problem, as Figure 1 , Figure 2 , Figure 6 and Fig. 9As shown, in some embodiments, a third mechanical air film ring 640 is arranged between the flame tube inner ring 300 and the small bend pipe 500, and the third mechanical air film ring 640 includes a fifth connecting portion 641 and a sixth connecting portion 642, and the sixth connecting portion 642 is arranged at intervals on the inner side of the fifth connecting portion 641, and the projection of the fifth connecting portion 641 along the thickness direction of the fifth connecting portion 641 partially overlaps with the sixth connecting portion 642, one end of the fifth connecting portion 641 is connected to the small bend pipe 500, and the other end is connected to the sixth connecting portion 642 through a first mounting portion 643, and the first mounting portion 643 is penetrated by a fourth cooling hole along the thickness direction of the first mounting portion 643; the sixth connecting portion 642 is connected to the flame tube inner ring 300; the cold air can pass through the fourth The cooling hole enters the space enclosed by the fifth connecting part 641 and the sixth connecting part 642, and under the guidance of the space enclosed by the fifth connecting part 641 and the sixth connecting part 642, it flows along the inner side surface of the small bend pipe 500 from one end toward the inner ring 300 of the flame tube to the end away from the inner ring 300 of the flame tube, thereby increasing the wall-adhering effect of the divergent cooling air film, thereby inhibiting the separation of the divergent cooling air film from the inner side surface of the small bend pipe 500; the divergent cooling effect of this part is further enhanced, and the wall temperature gradient of the small bend pipe 500 is reduced; at the same time, the third mechanical air film ring 640 makes the wall thickness of the connection between the inner ring 300 of the flame tube and the small bend pipe 500 thicker, thereby improving the cooling effect of the key local area of ​​the flame tube to meet the wall temperature control requirements, and improving the overall strength and rigidity of the flame tube, which is particularly suitable for reflow combustion chambers with relatively large size and aerodynamic force.

[0058] As another alternative implementation of the above technical solution, Fig.10As shown, a fourth mechanical air film ring 650 is arranged between the flame tube inner ring 300 and the small bend pipe 500, and the fourth mechanical air film ring 650 includes a seventh connecting part and an eighth connecting part, and the eighth connecting part is arranged at intervals on the inner side of the seventh connecting part, and the eighth connecting part and the seventh connecting part are connected by a second mounting part, and a third gap is formed between the seventh connecting part, the second mounting part and the eighth connecting part, and one end of the small bend pipe 500 facing the flame tube inner ring 300 is arranged in the third gap and abuts against the side of the seventh connecting part facing the eighth connecting part, and the small bend pipe 500 is not in contact with the eighth connecting part, and the second mounting part is penetrated by a fifth cooling hole along the thickness direction of the second mounting part; the eighth connecting part and the flame The inner ring 300 of the flame tube is connected; the cold air can enter the space surrounded by the small bend pipe 500 and the eighth connecting part through the fifth cooling hole, and flow along the inner side of the small bend pipe 500 from one end facing the inner ring 300 of the flame tube to the end away from the inner ring 300 of the flame tube, increasing the wall-adhering effect of the divergent cooling air film on the inner side of the small bend pipe 500, thereby inhibiting the divergent cooling air film from separating from the inner side of the small bend pipe 500; further enhancing the divergent cooling effect of this part, reducing the wall temperature gradient of the small bend pipe 500; at the same time, the fourth mechanical air film ring 650 makes the wall thickness of the connection between the inner ring 300 of the flame tube and the small bend pipe 500 thicker, thereby improving the overall strength and rigidity of the flame tube on the basis of improving the cooling effect of the key local area of ​​the flame tube to meet the wall temperature control requirements, and is particularly suitable for reflow combustion chambers with relatively large size and aerodynamic force. Specifically, the projection of the fifth cooling hole along the axial direction of the fifth cooling hole is staggered with the small bend pipe 500.

[0059] As another alternative implementation of the above technical solution, Fig.11As shown, a second Z-shaped air film ring 660 is arranged between the flame tube inner ring 300 and the small bend pipe 500, and the second Z-shaped air film ring 660 includes a fourth part, a fifth part and a sixth part which are connected in sequence in a Z shape, and the fourth part is located on the inner side of the sixth part; the fourth part is connected to the flame tube inner ring 300, and the sixth part is connected to the small bend pipe 500, and the fifth part is penetrated by a sixth cooling hole along the length direction of the sixth part; cold air can pass through the sixth cooling hole and close to the inner side surface of the small bend pipe 500 along the length direction of the fourth part toward the flame tube inner ring 300. One end of the ring 300 flows, increasing the divergent cooling air film's wall-adhering effect on the inner side of the small bend pipe 500, thereby inhibiting the divergent cooling air film from separating from the inner side of the small bend pipe 500; the divergent cooling effect of this part is further enhanced, reducing the wall temperature gradient of the small bend pipe 500; at the same time, the second Z-shaped air film ring 660 makes the wall thickness of the connection between the flame tube inner ring 300 and the small bend pipe 500 thicker, thereby improving the cooling effect of the key local area of ​​the flame tube to meet the need for good cooling in the entire range of the flame tube of the high-temperature rise reflow combustion chamber, and improving the overall strength and rigidity of the flame tube. It is particularly suitable for reflow combustion chambers with relatively large size and aerodynamic force.

[0060] like Figure 1 , Figure 2 and Figure 8As shown, in some embodiments, a turbine 700 is arranged between one end of the small curved pipe 500 away from the flame tube inner ring 300 and one end of the large curved pipe 400 away from the flame tube outer ring 200, and a fifth mechanical air film ring 670 is arranged between the small curved pipe 500 and the turbine 700, and the fifth mechanical air film ring 670 includes a ninth connecting portion 671 and a tenth connecting portion 672, and the tenth connecting portion 672 is located on the inner side of the ninth connecting portion 671, and the projection of the ninth connecting portion 671 along the thickness direction of the ninth connecting portion 671 is parallel to the projection of the tenth connecting portion 672. 72 partially overlap, one end of the ninth connection part 671 is connected to the turbine 700, and the other end is connected to the tenth connection part 672 through the third mounting part 673, and a fourth gap 674 is surrounded by the ninth connection part 671, the third mounting part 673 and the tenth connection part 672, and the projection of the fourth gap 674 along the length direction of the fourth gap 674 falls on the turbine 700, and a seventh cooling hole 675 is penetrated by the position of the ninth connection part 671 corresponding to the fourth gap 674, and the tenth connection part 672 is connected to the small bend pipe 500. Because additional cooling is required for the blade roots and blade tips of the turbine 700 to meet the life requirements of the turbine 700, this embodiment provides a fifth mechanical air film ring 670 between the flame tube inner ring 300 and the turbine 700, and provides a seventh cooling hole 675 at the ninth connecting portion 671 of the fifth mechanical air film ring 670, so that the cold air can pass through the seventh cooling hole 675 and contact the tenth connecting portion 672, whereupon the flow direction changes and flows along the fourth gap 674, and flows closely to the inner side surface of the ninth connecting portion 671 and blows toward the turbine 700, thereby providing additional cooling for the blade roots and blade tips of the turbine 700, thereby enhancing the cooling effect on the blade roots and blade tips of the turbine 700 and meeting the life requirements of the turbine 700.

[0061] As another replaceable implementation of the above technical solution, a turbine 700 is arranged between one end of the small curved pipe 500 away from the flame tube inner ring 300 and one end of the large curved pipe 400 away from the flame tube outer ring 200, and a third Z-shaped air film ring is arranged between the flame tube inner ring 300 and the turbine 700, and the third Z-shaped air film ring includes a seventh part, an eighth part and a ninth part connected in sequence in a Z shape, and the ninth part is located on the inner side of the seventh part; the seventh part is connected to the turbine 700, and the ninth part is connected to the small curved pipe 500, The eighth part is penetrated by an eighth cooling hole along the length direction of the seventh part, and the projection of the eighth cooling hole along the length direction of the ninth part falls on the turbine 700; by arranging a third Z-shaped air film ring between the inner ring 300 of the flame tube and the turbine 700, and arranging an eighth cooling hole in the eighth part of the third Z-shaped air film ring, cold air can pass through the eighth cooling hole and flow closely to the inner side surface of the ninth connecting part 671 and blow toward the turbine 700, thereby performing additional cooling on the blade roots and blade tips of the turbine 700, enhancing the cooling effect on the blade roots and blade tips of the turbine 700, and meeting the life requirements of the turbine 700.

[0062] like Figure 1 , Figure 2 As shown, specifically, a transition pipe 800 is provided between the large bend pipe 400 and the turbine 700, and the curvature radius of the transition pipe 800 is smaller than the curvature radius of the large bend pipe 400; through the transition connection of the transition pipe 800, and the curvature radius of the transition pipe 800 is closer to the curvature radius of the small bend pipe 500, the turbine 700 and the rocket launcher are formed into a whole on the basis of shortening the size of the large bend pipe 400, and the size of the whole is more miniaturized, which is more conducive to application in small and medium-sized aviation gas turbine engines.

[0063] like Figure 1 , Figure 2 and Figure 7As shown, specifically, a fourth Z-shaped air film ring 680 is arranged between the large bend pipe 400 and the transition pipe 800, and the fourth Z-shaped air film ring 680 includes a tenth portion 681, an eleventh portion 682 and a twelfth portion 683 which are sequentially connected in a Z shape, and the twelfth portion 683 is located on the inner side of the tenth portion 681; the tenth portion 681 is connected to the transition pipe 800, the twelfth portion 683 is connected to the large bend pipe 400, and the eleventh portion 682 is penetrated along the length direction of the tenth portion 681. Nine cooling holes, the projection of the ninth cooling hole along the length direction of the tenth part 681 falls on the turbine 700; by arranging the fourth Z-shaped air film ring 680 between the large bend pipe 400 and the transition pipe 800, and arranging the ninth cooling hole at the eleventh part 682 of the fourth Z-shaped air film ring 680, the cold air can pass through the ninth cooling hole and flow closely along the inner side surface of the transition pipe 800 and blow toward the turbine 700, so as to perform additional cooling on the blade roots and blade tips of the turbine 700, enhance the cooling effect on the blade roots and blade tips of the turbine 700, and meet the life requirements of the turbine 700.

[0064] As another replaceable implementation of the above technical solution, a sixth mechanical air film ring is arranged between the large bend pipe 400 and the transition pipe 800, and the sixth mechanical air film ring includes an eleventh connecting part and a twelfth connecting part, and the twelfth connecting part is located on the inner side of the eleventh connecting part, and the projection of the eleventh connecting part along the thickness direction of the eleventh connecting part partially overlaps with the twelfth connecting part, one end of the eleventh connecting part is connected to the transition pipe 800, and the other end is connected to the twelfth connecting part through a fourth mounting part, and the fourth mounting part is penetrated by a tenth cooling hole, and the projection of the tenth cooling hole along the axial direction of the tenth cooling hole falls on the inner side of the transition pipe 800, and the twelfth connecting part is connected to the large bend pipe 400. By arranging the sixth mechanical air film ring between the large bend pipe 400 and the transition pipe 800, and arranging the tenth cooling hole on the fourth mounting portion of the sixth mechanical air film ring, the cold air can enter the space enclosed by the eleventh connecting portion and the twelfth connecting portion through the tenth cooling hole, and under the guidance of the space enclosed by the eleventh connecting portion and the twelfth connecting portion, the cold air flows along the inner side surface of the transition pipe 800 and blows toward the turbine 700, thereby performing additional cooling on the blade roots and blade tips of the turbine 700, thereby enhancing the cooling effect on the blade roots and blade tips of the turbine 700 and meeting the life requirements of the turbine 700.

[0065] like Fig.12 As shown, specifically, a first cavity 110 is provided in the head ring 100, so that the head ring 100 forms a double-wall structure to further optimize the cooling effect.

[0066] like Fig.13As shown, specifically, a second cavity 410 is disposed in the large curved pipe 400, so that the large curved pipe 400 forms a double-wall structure to further optimize the cooling effect.

[0067] Specifically, a third cavity is disposed in the flame tube outer ring 200 , so that the flame tube outer ring 200 forms a double-wall structure to further optimize the cooling effect.

[0068] Specifically, a fourth cavity is provided in the flame tube inner ring 300 , so that the flame tube inner ring 300 forms a double-wall structure to further optimize the cooling effect.

[0069] It should be noted that if Figure 2 As shown, in the combined cooling structure of the flame tube of the reflow combustion chamber of the present embodiment, the head ring 100, the flame tube outer ring 200, the flame tube inner ring 300, the large bend pipe 400, the small bend pipe 500, the transition pipe 800, the first Z-type air film ring 610, the fourth Z-type air film ring 680, the first mechanical air film ring 620, the second mechanical air film ring 630, the third mechanical air film ring 640 and the fifth mechanical air film ring 670 are separately arranged to form independent parts, and the head ring 100, the flame tube outer ring 200, the flame tube inner ring 300, the large bend pipe 400, the small bend pipe 500 and the transition pipe 800 can be formed by sheet metal processing, and are formed as a whole with the first Z-type air film ring 610, the fourth Z-type air film ring 680, the first mechanical air film ring 620, the second mechanical air film ring 630, the third mechanical air film ring 640 and the fifth mechanical air film ring 670 by a combined welding process, which can greatly reduce the flame tube processing cost.

[0070] According to the second aspect of the embodiment of the present invention, a gas turbine engine is also provided, comprising the recirculation combustion chamber flame tube combined cooling structure provided by the first aspect of the embodiment of the present invention. The recirculation combustion chamber flame tube combined cooling structure in the gas turbine engine of this embodiment is provided with a first Z-shaped air film ring 610 between the flame tube outer ring 200 and the large bend pipe 400, and a first cooling hole is provided through the second part 612 of the first Z-shaped air film ring 610, so that cold air can pass through the first cooling hole and flow closely along the inner side of the large bend pipe 400 along one end toward the flame tube outer ring 200 to the end away from the flame tube outer ring 200, and cooperate with the original divergent holes of the large bend pipe 400 to further promote The wall-adhering effect of the divergent cooling air film in the downstream area of ​​the inner side of the large bend pipe 400 away from the outer ring 200 of the flame tube (that is, the part of the large bend pipe 400 facing the main combustion zone 910) further enhances the divergent cooling effect of this part and reduces the wall temperature gradient of the large bend pipe 400; a first mechanical air film ring 620 is provided between the outer ring 200 of the flame tube and the head ring 100, and a second cooling hole is penetrated in the first connecting part 621 of the first mechanical air film ring 620, so that the cold air can pass through the second cooling After the hole is formed and contacts the second connecting portion 622, the flow direction changes and flows along the first gap 623, and flows along the inner side surface of the flame tube outer ring 200 along the end facing the head ring 100 to the end away from the head ring 100, and cooperates with the original divergent holes of the flame tube outer ring 200 to further promote the wall-adhering effect of the divergent cooling air film in the area inside the flame tube outer ring 200 close to the main combustion zone 910, so that the divergent cooling effect of this part is further enhanced, and the wall temperature gradient of the flame tube outer ring 200 is reduced; at the same time, the first Z-shaped air film ring 610 and the first mechanical air film ring 620 respectively make the wall thickness of the connection between the flame tube outer ring 200 and the large bend pipe 400 and the connection between the flame tube outer ring 200 and the head ring 100 thicker, so as to improve the cooling effect of the local area with high thermal load intensity of the flame tube to meet the wall temperature control requirements, thereby improving the overall strength and rigidity of the flame tube, which is particularly suitable for reflow combustion chambers with relatively large size and aerodynamic force, and is beneficial to improving the thermal cycle parameters of the gas turbine engine of this embodiment.

[0071] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A flame tube combined cooling structure for a reflow combustion chamber, comprising a head ring (100), a flame tube outer ring (200), a flame tube inner ring (300), a large curved pipe (400) and a small curved pipe (500), wherein the flame tube inner ring (300) and the flame tube outer ring (200) are respectively arranged at two ends of the head ring (100), the large curved pipe (400) is arranged at one end of the flame tube outer ring (200) away from the head ring (100), and the small curved pipe (500) is arranged at one end of the flame tube inner ring (300) away from the head ring (100), wherein: Also includes: A first Z-shaped air film ring (610) is arranged between the flame tube outer ring (200) and the large curved pipe (400), wherein the first Z-shaped air film ring (610) comprises a first portion (611), a second portion (612) and a third portion (613) connected in sequence, wherein the first portion (611) is connected to the flame tube outer ring (200), the third portion (613) is connected to the large curved pipe (400), and the second portion (612) is provided with a first cooling hole along a thickness direction of the second portion (612), and a projection of the first cooling hole along an axial direction of the first cooling hole falls on an inner side of the large curved pipe (400); The first mechanical air film ring (620) includes a first connecting portion (621) arranged between the outer ring of the flame tube (200) and the head ring (100), and a second connecting portion (622) arranged on the inner side of the first connecting portion (621), a first gap (623) is formed between the first connecting portion (621) and the second connecting portion (622), and a second cooling hole is arranged through the first connecting portion (621) at a position corresponding to the first gap (623) along the thickness direction of the first connecting portion (621).

2. A reflow combustion chamber flame tube combined cooling structure according to claim 1, characterized in that: It also includes a second mechanical air film ring (630), which includes a third connecting portion (631) arranged between the inner ring of the flame tube (300) and the head ring (100) and a fourth connecting portion (632) arranged on the inner side of the third connecting portion (631), and a second gap (633) is formed between the third connecting portion (631) and the fourth connecting portion (632), and a third cooling hole is arranged through the third connecting portion (631) along the thickness direction of the third connecting portion (631) at a position corresponding to the second gap (633).

3. The combined cooling structure of the flame tube of the reflow combustion chamber according to claim 1, characterized in that: A third mechanical air film ring (640) is arranged between the inner ring of the flame tube (300) and the small bend tube (500), and the third mechanical air film ring (640) includes a fifth connecting portion (641) and a sixth connecting portion (642), and the sixth connecting portion (642) is arranged at intervals on the inner side of the fifth connecting portion (641), and the projection of the fifth connecting portion (641) along the thickness direction of the fifth connecting portion (641) at least partially overlaps with the sixth connecting portion (642), one end of the fifth connecting portion (641) is connected to the small bend tube (500), and the other end is connected to the sixth connecting portion (642) through a first mounting portion (643), and the first mounting portion (643) is provided with a fourth cooling hole along the thickness direction of the first mounting portion (643); the sixth connecting portion (642) is connected to the inner ring (300) of the flame tube.

4. The combined cooling structure of the flame tube of the reflow combustion chamber according to claim 1, characterized in that: A fourth mechanical air film ring (650) is arranged between the inner ring of the flame tube (300) and the small bend tube (500), and the fourth mechanical air film ring (650) includes a seventh connecting part and an eighth connecting part, and the eighth connecting part is arranged at intervals on the inward side of the seventh connecting part, and the eighth connecting part and the seventh connecting part are connected by a second mounting part, and a third gap is formed between the seventh connecting part, the second mounting part and the eighth connecting part, and the small bend tube (500) is arranged in the third gap and abuts against the side of the seventh connecting part facing the eighth connecting part, and the second mounting part is provided with a fifth cooling hole penetrating along the thickness direction of the second mounting part; the eighth connecting part is connected to the inner ring of the flame tube (300).

5. The combined cooling structure of the flame tube of the reflow combustion chamber according to claim 1, characterized in that: A second Z-shaped air film ring (660) is arranged between the flame tube inner ring (300) and the small bend pipe (500), and the second Z-shaped air film ring (660) includes a fourth part, a fifth part and a sixth part connected in sequence, and the fourth part is located on the inner side of the sixth part; the fourth part is connected to the flame tube inner ring (300), the sixth part is connected to the small bend pipe (500), and the fifth part is provided with a sixth cooling hole along the length direction of the sixth part.

6. A combined cooling structure for a reflow combustion chamber flame tube according to any one of claims 1 to 5, characterized in that: A turbine (700) is arranged between one end of the small curved pipe (500) away from the inner ring (300) of the flame tube and one end of the large curved pipe (400) away from the outer ring (200) of the flame tube, and a fifth mechanical air film ring (670) is arranged between the small curved pipe (500) and the turbine (700). The fifth mechanical air film ring (670) includes a ninth connecting portion (671) and a tenth connecting portion (672). The tenth connecting portion (672) is located on the inner side of the ninth connecting portion (671). The projection of the ninth connecting portion (671) along the thickness direction of the ninth connecting portion (671) is at least partially aligned with the tenth connecting portion (672). The ninth connection part (671) overlaps the turbine (700), one end of the ninth connection part (671) is connected to the turbine (700), and the other end is connected to the tenth connection part (672) through the third mounting part (673); the ninth connection part (671), the third mounting part (673) and the tenth connection part (672) enclose a fourth gap (674); a projection of the fourth gap (674) along the length direction of the fourth gap (674) falls on the turbine (700); a seventh cooling hole (675) is provided through the ninth connection part (671) at a position corresponding to the fourth gap (674); and the tenth connection part (672) is connected to the small curved pipe (500); Alternatively, a turbine (700) is arranged between one end of the small curved pipe (500) away from the flame tube inner ring (300) and one end of the large curved pipe (400) away from the flame tube outer ring (200), and a third Z-shaped air film ring is arranged between the flame tube inner ring (300) and the turbine (700), and the third Z-shaped air film ring includes a seventh part, an eighth part and a ninth part connected in sequence, and the ninth part is located on the inner side of the seventh part; the seventh part is connected to the turbine (700), the ninth part is connected to the small curved pipe (500), and the eighth part is provided with an eighth cooling hole along the length direction of the seventh part.

7. A reflow combustion chamber flame tube combined cooling structure according to claim 6, characterized in that: A transition pipe (800) is provided between the large curved pipe (400) and the turbine (700), and the curvature radius of the transition pipe (800) is smaller than the curvature radius of the large curved pipe (400).

8. A reflow combustion chamber flame tube combined cooling structure according to claim 7, characterized in that: A fourth Z-shaped air film ring (680) is arranged between the large bend pipe (400) and the transition pipe (800), and the fourth Z-shaped air film ring (680) includes a tenth part (681), an eleventh part (682) and a twelfth part (683) which are connected in sequence, and the twelfth part (683) is located on the inner side of the tenth part (681); the tenth part (681) is connected to the transition pipe (800), the twelfth part (683) is connected to the large bend pipe (400), and the eleventh part (682) is provided with a ninth cooling hole along the length direction of the tenth part (681).

9. The combined cooling structure of the flame tube of the reflow combustion chamber according to claim 7, characterized in that: A sixth mechanical air film ring is arranged between the large bend pipe (400) and the transition pipe (800), and the sixth mechanical air film ring includes an eleventh connecting part and a twelfth connecting part, the twelfth connecting part is located on the inner side of the eleventh connecting part, and the projection of the eleventh connecting part along the thickness direction of the eleventh connecting part at least partially overlaps with the twelfth connecting part, one end of the eleventh connecting part is connected to the transition pipe (800), and the other end is connected to the twelfth connecting part through a fourth mounting part, the fourth mounting part is penetrated by a tenth cooling hole, and the projection of the tenth cooling hole along the axial direction of the tenth cooling hole falls on the inner side of the transition pipe (800), and the twelfth connecting part is connected to the large bend pipe (400).

10. A gas turbine engine, characterized in that: The invention comprises the combined cooling structure of the flame tube of the reflow combustion chamber according to any one of claims 1 to 9.

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