Impingement cooling integrated with combustion chamber flame tube cooling wall surface structure and flame tube

Abstract

The application provides a combustion chamber flame tube cooling wall surface structure and a flame tube, which are integrated by impingement cooling and mixing, and overcome the problem of uneven temperature distribution of the existing flame tube wall surface. The combustion chamber flame tube cooling wall surface structure comprises an impingement hole wall and an inner layer wall, an annular air passage is arranged between the impingement hole wall and the inner layer wall, the impingement hole wall and the inner layer wall are connected through an air film ring, an air film cooling ring slot groove is formed at the tail of the flame tube, the air film ring is provided with air film cooling holes, vertical first diameter holes are arranged on the impingement hole wall to form vertical impingement jets, the diameter of the first diameter holes is less than a first preset value, and main combustion holes and mixing holes are arranged on the inner layer wall. The application improves the traditional flame tube cooling structure, makes the air of the cooling wall surface participate in the mixing organization of the combustion chamber, and greatly reduces the amount of cooling air under the condition of ensuring the cooling effect.

Description

Technical Field

[0001] This invention belongs to the field of low-pollution combustion chamber technology for gas turbines, specifically relating to a combustion chamber flame tube cooling wall structure and flame tube that integrates impact cooling and mixing. Background Technology

[0002] In modern combustion chambers, the temperature of the gases released during combustion can exceed 2100°C, far exceeding the melting points of the combustion chamber flame tube and turbine blades. Therefore, combustion chamber design needs to consider measures to adequately cool all metal surfaces exposed to the high-temperature gases and improve structural integrity and durability. Furthermore, the amount of cooling air should be minimized to maximize the amount of air available for emission control.

[0003] Compared to many other components of an engine, the combustion chamber burner tube experiences relatively low mechanical stress. However, the burner tube is subjected to high temperatures and rapidly changing temperature gradients that threaten its structural integrity. Maintaining the temperature and temperature gradient at acceptable levels is crucial to ensuring a satisfactory burner tube lifespan. Measures must be taken to enhance heat dissipation from the burner tube, typically through radiation to the combustion chamber casing and convection with the annular air. Traditionally, this is achieved by forming a cooling film along the inner surface of the burner tube. With the improvement of turbine engine performance, the engine pressure ratio and combustion chamber temperature rise have gradually increased, placing a greater thermal load on the burner tube walls. The increased combustion air consumption coupled with a fixed intake air volume necessitates a reduction in the amount of cooling air required. Since the thermal load on the burner tube walls is also increasing, more advanced cooling methods are needed to achieve better cooling with less cooling air.

[0004] Currently, in actual gas turbine operation, the temperature distribution on the flame tube wall is often uneven, and there are even significant differences in different areas. Under such circumstances, it is difficult to select a cooling structure, and existing cooling structures are difficult to guarantee applicability to all areas. Summary of the Invention

[0005] In view of the above problems, the present invention proposes a combustion chamber flame tube cooling wall structure and flame tube that integrates impact cooling and mixing, in order to solve at least one of the above-mentioned problems existing in the prior art.

[0006] According to one aspect of the present invention, a combustion chamber flame tube cooling wall structure integrating impact cooling and mixing is provided, the combustion chamber flame tube cooling wall structure including an impact hole wall and an inner wall; an annular air channel is provided between the impact hole wall and the inner wall; the impact hole wall and the inner wall are connected by a gas film ring, forming a gas film cooling annular groove at the tail of the flame tube, the gas film ring being provided with gas film cooling holes; a vertical first diameter hole is provided on the impact hole wall to form a vertical impact jet, the diameter of the first diameter hole being smaller than a first preset value; a main combustion hole and a mixing hole are provided on the inner wall.

[0007] Furthermore, the axis of the first diameter holes distributed on the impact hole wall is perpendicular to the inner wall, and the first diameter holes are arranged in a staggered pattern.

[0008] Furthermore, the first diameter hole is a circular hole with a diameter between 0.5 and 3 mm and a hole spacing of 2 to 5 times the hole diameter.

[0009] Furthermore, the impact hole wall and the inner wall head are connected by welding, and the radial distance between the impact hole wall and the inner wall on the circumferential cross section is equal, forming an annular air channel with a radial height of 0.7 to 2 times the wall thickness.

[0010] Furthermore, the main combustion holes are circular with a diameter between 8 and 13 mm, and each combustion chamber head is provided with 4 to 6 main combustion holes.

[0011] Furthermore, the mixing holes are circular with a diameter between 7 and 12 mm, and each combustion chamber head is provided with 6 to 8 mixing holes.

[0012] Furthermore, the film cooling ring connects the impact hole wall and the inner wall by welding; the tail of the impact hole wall and the inner wall is 3-6 mm upstream of the combustion chamber turbine guide vane, and the film cooling ring is located 5-7 times the wall thickness upstream of the tail of the inner wall. The axis of the film cooling hole is parallel to the inner wall, the hole shape is circular, the hole diameter is between 0.5 and 2 mm, and the hole spacing is 2-5 times the hole diameter. After the cooling air passes through the film cooling hole, it passes through the groove of the film cooling ring to form a cooling air film at the tail of the flame tube for cooling the root of the combustion chamber turbine guide vane.

[0013] Furthermore, the combustion chamber flame tube cooling wall structure is suitable for use in an integrated combustion chamber flame tube with impact cooling; the combustion chamber flame tube includes an inner wall and an outer wall; both the inner wall and the outer wall adopt the combustion chamber flame tube cooling wall structure.

[0014] According to another aspect of the present invention, a combustion chamber flame tube with integrated impact cooling is also provided, comprising an inner wall 100 and an outer wall 200, wherein both the inner wall 100 and the outer wall 200 adopt the combustion chamber flame tube cooling wall structure as described in any one of claims 1-7; the combustion chamber flame tube with integrated impact cooling has two sets of the combustion chamber flame tube cooling wall structures; the inner wall 100 includes a first impact hole wall 120 and a first inner layer wall 130, and the first impact hole wall 120 is disposed inside the first inner layer wall 130; the outer wall 200 includes a second impact hole wall 220 and a second inner layer wall 230, and the second inner layer wall 230 is disposed inside the second impact hole wall 220; in the cross-section of the combustion chamber flame tube, the sections perpendicular to the central axis of the tube, from the inside out, are the first impact hole wall 120, the first inner layer wall 130, the second inner layer wall 230, and the second impact hole wall 220.

[0015] This invention discloses a combustion chamber flame tube cooling wall structure and flame tube integrating impact cooling and mixing. The combustion chamber flame tube cooling wall structure includes an impact hole wall, an inner wall, a film cooling ring, small-diameter holes, film cooling holes, a main combustion hole, and mixing holes. Cooling air is generated by impact cooling air on the impact wall surface to form impact cooling on the inner wall surface. The inner wall surface is cooled only by impact air. The impact cooling air converges in an annular air channel and enters the flame tube through the film cooling holes at the tail of the main combustion hole and the mixing hole, respectively. The impact cooling air used to cool the inner wall surface is reused, reducing the amount of air used for wall cooling. At the same time, a film cooling annular groove is provided at the tail of the flame tube to effectively protect the root of the combustion chamber turbine guide vanes and extend the life of the turbine guide vanes. This invention improves the traditional flame tube cooling structure by allowing the air on the cooling wall surface to participate in the mixing organization of the combustion chamber, significantly reducing the amount of cooling air while ensuring the cooling effect.

[0016] In an embodiment of the present invention, by adopting a double-wall structure, cooling air is applied to the inner wall surface through the impact cooling air on the impact wall surface to form impact cooling. The inner wall surface eliminates the film cooling structure, so the inner wall surface is cooled only by impact air. The impact cooling air converges in the annular air channel and enters the flame tube through the main combustion hole and the film cooling hole at the tail of the mixing hole, respectively. The impact cooling air used to cool the inner wall surface is reused, allowing the air used to cool the wall surface to participate in the mixing structure of the combustion chamber, reducing the amount of air used for wall cooling. At the same time, the film cooling annular groove at the tail of the flame tube is provided to effectively protect the root of the turbine guide vane in the combustion chamber and extend the life of the turbine guide vane. Attached Figure Description

[0017] Figure 1 An exemplary structural diagram of the combustion chamber flame tube cooling wall structure integrating impact cooling and mixing according to an embodiment of the present invention is shown;

[0018] Figure 2 A partial structural diagram of the tail section of the combustion chamber flame tube in an embodiment of the present invention is shown;

[0019] Figure 3 A structural diagram of the combustion chamber flame tube impact hole wall in an embodiment of the present invention is shown;

[0020] Figure 4 A diagram showing the overall structure of the flame tube wall is provided.

[0021] In the figure: 1-Connection between the impact hole wall and the inner wall; 2-Impact hole wall; 21-First diameter hole; 3-Inner wall; 4-Annular air passage; 5-Main combustion hole; 6-Mixing hole; 7-Film ring; 8-Film cooling ring groove; 9-Film cooling hole; 100-Inner wall of the flame tube; 200-Outer wall of the flame tube; 120-First impact hole wall; 130-First inner wall; 121-First impact hole; 135-First main combustion hole; 136-First mixing hole; 220-Second impact hole wall; 230-Second inner wall; 221-Second impact hole; 235-Second main combustion hole; 236-Second mixing hole. Detailed Implementation

[0022] To enable those skilled in the art to better understand the present invention, exemplary embodiments or examples of the present invention will be described below in conjunction with the accompanying drawings. All other embodiments or examples obtained by those skilled in the art based on the embodiments of the present invention without inventive effort should fall within the scope of protection of the present invention.

[0023] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections or detachable connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal connections between two components. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0024] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0025] The inventors have discovered that flame tubes are generally made of high-temperature resistant alloys. Currently, the basic cooling methods used for gas turbine flame tubes mainly include film cooling, divergent cooling, combined impact and divergent cooling, and plate cooling. The basic principle is to introduce a portion of the cold air from the outer annular cavity of the combustion chamber into the flame tube, forming a film on the inner wall of the flame tube. This cools the flame tube wall on one hand and isolates the hot combustion gas on the other.

[0026] However, as mentioned earlier, in actual gas turbine operation, the temperature distribution on the flame tube wall is often uneven, and there are even significant differences in different areas. Under such circumstances, it is quite difficult to select a cooling structure.

[0027] Therefore, a good cooling structure should be able to form a uniformly distributed gas film with low turbulence and good adhesion to the wall inside the flame tube, while avoiding excessively thick gas film accumulation that could affect the combustion structure.

[0028] Based on this, embodiments of the present invention provide a combustion chamber flame tube cooling wall structure integrating impact cooling and mixing. The combustion chamber flame tube cooling wall structure includes an impact hole wall and an inner wall. An annular air channel is provided between the impact hole wall and the inner wall. The impact hole wall and the inner wall are connected by a gas film ring, forming a gas film cooling annular groove at the tail of the flame tube. The gas film ring is provided with gas film cooling holes. A vertical first diameter hole is provided on the impact hole wall to form a vertical impact jet. The diameter of the first diameter hole is smaller than a first preset value. The inner wall is provided with a main combustion hole and a mixing hole.

[0029] Therefore, the combustion chamber flame tube cooling wall structure of the present invention can overcome the problem of uneven temperature distribution on the existing flame tube wall, that is, the problem that the existing cooling structure is difficult to guarantee applicability to all areas. In addition, it can also solve the contradiction between the increase in heat load of the advanced combustion chamber flame tube and the reduction in the amount of available cold air in the prior art.

[0030] Figure 1 A schematic diagram of an example of the combustion chamber flame tube cooling wall structure integrating impact cooling is shown below. Figures 1-3 To describe the example above.

[0031] in, Figure 2 A partial structural diagram of the tail section of the combustion chamber flame tube in an embodiment of the present invention is shown. Figure 3 A structural diagram of the combustion chamber flame tube impact hole wall in an embodiment of the present invention is shown. Furthermore, Figure 1 The combustion chamber flame tube cooling wall structure shown is an integrated impact cooling and mixing structure used in a flame tube. The resulting overall flame tube wall structure is as follows: Figure 4 As shown.

[0032] The combustion chamber flame tube cooling wall structure includes an impact hole wall 2 and an inner wall 3. The impact hole wall 2 and the inner wall 3 are, as shown in... Figure 1 The left side shown has a connection point, namely, the connection point 1 between the impact hole wall and the inner wall.

[0033] The impact hole wall 2 is, for example, a ring structure, i.e., an annular impact hole wall.

[0034] An annular air channel 4 is provided between the impact hole wall 2 and the inner wall 3. The impact hole wall 2 and the inner wall 3 are connected by a film cooling ring 7, forming a film cooling annular groove 8 at the tail of the flame tube. The film cooling ring 7 is provided with film cooling holes 9.

[0035] In addition, the impact hole wall 2 is provided with a vertical first diameter hole 21 to form a vertical impact jet, and the diameter of the first diameter hole is smaller than a first preset value; the inner wall 3 is provided with a main combustion hole 5 and a mixing hole 6.

[0036] As an example, the axis of the first diameter holes 21 distributed on the impact hole wall 2 is perpendicular to the inner wall 3, and the arrangement of the first diameter holes 21 is, for example, a cross arrangement.

[0037] As an example, the shape of the first diameter hole 21 is, for example, a circular hole. The first preset value is, for example, 1-3.5 mm.

[0038] The aperture is, for example, between 0.5 and 3 mm, and the spacing between the apertures is 2 to 5 times the aperture.

[0039] As an example, the heads of the impact hole wall 2 and the inner wall 3 are connected by welding. The radial spacing height of the impact hole wall 2 and the inner wall 3 on the circumferential section is equal, and the radial height of the formed annular air channel 4 is 0.7 to 2 times the wall thickness.

[0040] As an example, the inner wall 3 is provided with a main combustion hole 5 and a mixing hole 6.

[0041] As an example, the main combustion hole 5 is a circular hole with a diameter between 8 and 13 mm, and each combustion chamber head has 4 to 6 main combustion holes 5; the mixing hole 6 is a circular hole with a diameter between 7 and 12 mm, and each combustion chamber head has 6 to 8 mixing holes 6.

[0042] As an example, the film cooling ring 7 connects the impact hole wall 2 and the inner wall 3 by welding; the tail of the impact hole wall 2 and the inner wall 3 is 3 to 6 mm upstream of the combustion chamber turbine guide vane, and the film cooling ring 7 is located 5 to 7 times the wall thickness upstream of the tail of the inner wall 3. The axis of the film cooling hole 9 is parallel to the inner wall 3, the hole shape is a circular hole, the hole diameter is between 0.5 and 2 mm, and the hole spacing is 2 to 5 times the hole diameter. After the cooling air passes through the film cooling hole 9, it passes through the film cooling ring groove 8 to form a cooling air film at the tail of the flame tube for cooling the root of the combustion chamber turbine guide vane.

[0043] As an example, the combustion chamber flame tube cooling wall structure can be adapted for use in a combustion chamber flame tube with integrated impact cooling; the combustion chamber flame tube includes an inner wall and an outer wall; both the inner and outer walls of the flame tube adopt the combustion chamber flame tube cooling wall structure.

[0044] In a preferred embodiment of the present invention, the above-mentioned combustion chamber flame tube cooling wall structure integrating impact cooling and mixing includes an impact hole wall 2, an inner wall 3, a gas film ring 7, a small diameter hole, a gas film cooling hole 9, a main combustion hole 5, and a mixing hole 6.

[0045] The combustion chamber flame tube cooling wall structure can be used in the combustion chamber flame tube. The aforementioned wall structure consists of an impact hole wall and an inner wall, forming an annular air channel between the impact hole wall and the inner wall. The impact hole wall and the inner wall are connected by a film cooling ring, forming a film cooling annular groove at the tail of the flame tube. The film cooling ring is provided with film cooling holes. The impact hole wall is provided with vertical small-diameter holes to form a vertical impact jet. The inner wall is provided with main combustion holes and mixing holes.

[0046] The cooling air impacts the inner wall surface, providing impingement cooling. The inner wall surface is cooled solely by this impingement air, which converges within the annular air channel 4 and enters the flame tube through the main combustion port, mixing port, and tail film cooling port. This reuses the impingement air used for cooling the inner wall surface, reducing the amount of air needed for wall cooling. Simultaneously, a film cooling annular groove at the tail of the flame tube effectively protects the root of the turbine guide vanes in the combustion chamber, extending their lifespan. This invention improves upon the traditional flame tube cooling structure by integrating the air used for cooling the wall surface into the mixing mechanism of the combustion chamber, significantly reducing the amount of cooling air while maintaining effective cooling. The combustion chamber flame tube cooling wall structure consists of an impact hole wall 2 and an inner wall 3. An annular air channel 4 is formed between the impact hole wall 2 and the inner wall 3. The impact hole wall 2 and the inner wall 3 are connected by a film cooling ring 7. A film cooling annular groove 8 is formed at the tail of the flame tube. The film cooling ring is provided with film cooling holes 9. The impact hole wall 2 is provided with vertical small-diameter holes to form a vertical impact jet. The inner wall 3 is provided with main combustion holes 5 and mixing holes 6.

[0047] The small-diameter holes distributed on the impact hole wall have their axes perpendicular to the inner wall and are arranged in a staggered pattern. These small-diameter holes are circular, with diameters ranging from 0.5 to 3 mm, and the spacing between them is 2 to 5 times the hole diameter. The impact hole wall and the inner wall are connected by welding. The radial spacing between the impact hole wall and the inner wall in the circumferential section is equal, forming an annular air channel with a radial height of 0.7 to 2 times the wall thickness.

[0048] In addition, the inner wall is equipped with main combustion holes and mixing holes. The main combustion holes are circular with a diameter between 8 and 13 mm, and there are 4 to 6 holes at the head of each combustion chamber. The mixing holes are also circular with a diameter between 7 and 12 mm, and there are 6 to 8 holes at the head of each combustion chamber. The film cooling ring connects the impact hole wall and the inner wall by welding. The impact hole wall and the tail of the inner wall are located 3 to 6 mm upstream of the turbine guide vane of the combustion chamber. The film cooling ring is located 5 to 7 times the wall thickness upstream of the tail of the inner wall. The axis of the film cooling holes is parallel to the inner wall. The holes are circular with a diameter between 0.5 and 2 mm, and the spacing between the holes is 2 to 5 times the diameter. After passing through the film cooling holes, the cooling air passes through the grooves of the film cooling ring and forms a cooling air film at the tail of the flame tube to cool the root of the turbine guide vane of the combustion chamber.

[0049] Embodiments of the present invention also provide a combustion chamber flame tube with integrated impact cooling.

[0050] Below, in conjunction with Figure 4 An example of a combustion chamber flame tube that integrates the aforementioned impact cooling system.

[0051] The combustion chamber's flame tube typically consists of an inner wall and an outer wall, namely the inner wall and the outer wall of the flame tube. Figure 4 A portion of the flame tube is schematically shown. As can be seen from the figure, the inner wall 100 of the flame tube is located inside the flame tube, and the outer wall 200 of the flame tube is located outside the flame tube. That is to say, the size of the inner wall 100 of the flame tube is smaller than the size of the outer wall 200 of the flame tube, so that the flame tube can be installed.

[0052] like Figure 4 As shown, both the inner wall 100 and the outer wall 200 of the flame tube adopt the combustion chamber flame tube cooling wall structure described above. The difference is that the impact hole wall corresponding to the inner wall 100 of the flame tube is inside (closer to the center of the flame tube) and the inner layer wall is outside (farther from the center of the flame tube); while the inner layer wall corresponding to the outer wall 200 of the flame tube is inside (closer to the center of the flame tube) and the impact hole wall is outside (farther from the center of the flame tube).

[0053] The cross-section of the combustion chamber flame tube perpendicular to the central axis of the tube, from the inside out, consists of the first impact hole wall 120, the first inner wall 130, the second inner wall 230, and the second impact hole wall 220.

[0054] See Figure 4 The inner wall 100 of the flame tube includes a first impact hole wall 120 and a first inner wall 130, with the first impact hole wall 120 located inside the first inner wall 130. Thus, the first impact hole wall 120 and the first inner wall 130 constitute a set. Figure 1The impact hole wall 2 and inner wall 3 shown are illustrated. The first impact hole 121 on the first impact hole wall 120 is equivalent to the first diameter hole 21 on the impact hole wall 2. The first main combustion hole 135 and the first mixing hole 136 on the first inner wall 130 are equivalent to the main combustion hole 5 and the mixing hole 6. An annular air channel is also provided between the first impact hole wall 120 and the first inner wall 130, and the two are connected by a film cooling ring, forming a film cooling annular groove at the tail of the flame tube. The film cooling ring is provided with film cooling holes. The specific structure of the inner wall 100 of the flame tube can be adopted as described above. Figures 1-3 The combustion chamber flame tube cooling wall structure described herein, which can achieve similar effects, will not be elaborated upon here.

[0055] The outer wall 200 of the flame tube includes a second impact hole wall 220 and a second inner wall 230, with the second inner wall 230 located inside the second impact hole wall 220. Thus, the second impact hole wall 220 and the second inner wall 230 constitute another set of... Figure 1 The impact hole wall 2 and inner wall 3 are shown, but this set is different from the impact hole wall 2 and inner wall 3 shown. Figure 1 In the structure shown, the positions of the impact hole wall 2 and the inner wall 3 are exactly opposite (i.e., the positions of the impact hole wall 2 and the inner wall 3 are interchanged). The second impact hole 221 provided on the second impact hole wall 220 is equivalent to the first diameter hole 21 provided on the impact hole wall 2, and the second main combustion hole 235 and the second mixing hole 236 provided on the second inner wall 230 are equivalent to the main combustion hole 5 and the mixing hole 6. An annular air channel is also provided between the second impact hole wall 220 and the second inner wall 230, and the two are connected by a film cooling ring, forming a film cooling annular groove at the tail of the flame tube, and the film cooling ring is provided with film cooling holes. The specific structure of the outer wall 200 of the flame tube can adopt the combination of the above description. Figures 1-3 The combustion chamber flame tube cooling wall structure described herein, which can achieve similar effects, will not be elaborated upon here.

[0056] In summary, the combustion chamber flame tube cooling wall structure integrating impact cooling and mixing according to an embodiment of the present invention includes an impact hole wall, an inner wall, a film cooling ring, small-diameter holes, film cooling holes, a main combustion hole, and mixing holes. Cooling air is applied to the inner wall surface via the impact cooling air on the impact wall, resulting in impact cooling. The inner wall surface is cooled solely by the impact air. The impact cooling air converges within an annular air channel and enters the flame tube through the film cooling holes at the tail of the main combustion hole and the mixing hole, respectively. This reuses the impact cooling air used for cooling the inner wall surface, reducing the amount of air used for wall cooling. Simultaneously, a film cooling annular groove is provided at the tail of the flame tube, effectively protecting the root of the combustion chamber turbine guide vanes and extending their lifespan. This invention improves upon traditional flame tube cooling structures by integrating the air cooling the wall surface into the mixing structure of the combustion chamber, significantly reducing the amount of cooling air while maintaining cooling effectiveness.

[0057] Under the same air intake conditions, the combustion chamber flame tube cooling wall structure with integrated impact cooling and mixing according to the above-described embodiment of the present invention can, compared with the prior art, allocate more air to the head to organize combustion, realize lean combustion in the main combustion zone, and thus reduce NOx emissions. On the other hand, it can increase the amount of mixed air to improve the quality of the outlet temperature field and resolve the contradiction between cooling, outlet temperature distribution, and low emission performance.

[0058] In an embodiment of the present invention, by adopting a double-wall structure, cooling air is applied to the inner wall surface through the impact cooling air on the impact wall surface to form impact cooling. The inner wall surface eliminates the film cooling structure, so the inner wall surface is cooled only by impact air. The impact cooling air converges in the annular air channel and enters the flame tube through the main combustion hole and the film cooling hole at the tail of the mixing hole, respectively. The impact cooling air used to cool the inner wall surface is reused, allowing the air used to cool the wall surface to participate in the mixing structure of the combustion chamber, reducing the amount of air used for wall cooling. At the same time, the film cooling annular groove at the tail of the flame tube is provided to effectively protect the root of the turbine guide vane in the combustion chamber and extend the life of the turbine guide vane.

[0059] Although the invention has been described with respect to a limited number of embodiments, those skilled in the art will understand from the foregoing description that other embodiments are conceivable within the scope of the invention described herein. The disclosure of the invention is illustrative and not restrictive, and the scope of the invention is defined by the appended claims.

Claims

1. A combustor flame tube cooling wall surface structure of impingement cooling and blending integration, characterized in that, The combustion chamber flame tube cooling wall surface structure comprises an impingement hole wall (2) and an inner layer wall (3); An annular air passage (4) is arranged between the impingement hole wall (2) and the inner layer wall (3); The impingement hole wall (2) and the inner layer wall (3) are connected through a gas film ring (7), and a gas film cooling ring slot (8) is formed at the tail of the flame tube, and the gas film ring (7) is provided with gas film cooling holes (9); A vertical first diameter hole (21) is arranged on the impingement hole wall (2) to form a vertical impingement jet, and the diameter of the first diameter hole is less than a first preset value; The inner layer wall (3) is provided with a main combustion hole (5) and a mixing hole (6); The impingement hole wall (2) and the inner layer wall (3) are connected through welding by the gas film ring (7); The tail of the impingement hole wall (2) and the inner layer wall (3) is 3-6mm away from the upstream of the combustion chamber turbine guide vane, the gas film ring (7) is located at the upstream of the tail of the inner layer wall (3) and is 5-7 times the wall thickness away, the hole axis of the gas film cooling hole (9) is parallel to the inner layer wall (3), the hole shape is a circular hole, the hole diameter is between 0.5-2mm, the hole spacing is 2-5 times the hole diameter, and the cooling air passes through the gas film cooling hole (9) and then passes through the gas film cooling ring slot (8) to form a cooling air film for cooling the root of the combustion chamber turbine guide vane at the tail of the flame tube.

2. The impingement cooling and mixing integrated combustion chamber flame tube cooling wall surface structure according to claim 1, characterized in that: The hole axis of the first diameter hole (21) distributed on the impingement hole wall (2) is perpendicular to the inner layer wall (3), and the first diameter hole (21) is arranged in a staggered manner.

3. The impingement cooling blended integrated combustor flame tube wall surface structure according to claim 2, wherein, The first diameter hole (21) is a circular hole, the hole diameter is between 0.5-3mm, and the hole spacing is 2-5 times the hole diameter.

4. The impingement cooling blended integrated combustor flame tube wall surface structure according to claim 1, wherein, The head of the impingement hole wall (2) and the inner layer wall (3) is connected through welding, the radial spacing height of the impingement hole wall (2) and the inner layer wall (3) in the circumferential section is equal, and the radial height of the annular air passage (4) formed is 0.7-2 times the wall thickness.

5. The impingement cooling blended integrated combustor flame tube wall surface structure according to claim 1, wherein, The main combustion hole (5) is a circular hole, the hole diameter is between 8-13mm, and 4-6 main combustion holes (5) are arranged at each combustion chamber head.

6. The impingement cooling blended integrated combustor flame tube wall surface structure according to claim 1, wherein, The mixing hole (6) is a circular hole, the hole diameter is between 7-12mm, and 6-8 mixing holes (6) are arranged at each combustion chamber head.

7. The impingement cooling blended integral combustor flame tube wall surface structure according to any of claims 1-6, characterized by, The combustion chamber flame tube cooling wall surface structure is suitable for an impingement cooling and mixing integrated combustion chamber flame tube, the impingement cooling and mixing integrated combustion chamber flame tube has two groups of the combustion chamber flame tube cooling wall surface structure, the combustion chamber flame tube comprises a flame tube inner wall and a flame tube outer wall, and the flame tube inner wall and the flame tube outer wall both adopt the combustion chamber flame tube cooling wall surface structure.

8. An impingement cooling and mixing integrated combustion chamber flame tube, comprising a flame tube inner wall (100) and a flame tube outer wall (200), characterized in that: The flame tube inner wall (100) and the flame tube outer wall (200) both adopt the combustion chamber flame tube cooling wall surface structure according to any one of claims 1-7. The inner wall (100) of the flame tube comprises a first impact hole wall (120) and a first inner layer wall (130), and the first impact hole wall (120) is arranged at the inner side of the first inner layer wall (130); The outer wall (200) of the flame tube comprises a second impact hole wall (220) and a second inner layer wall (230), and the second inner layer wall (230) is arranged at the inner side of the second impact hole wall (220); In the cross section of the combustion chamber flame tube, which is a cross section perpendicular to the center axis of the tube, the first impact hole wall (120), the first inner layer wall (130), the second inner layer wall (230) and the second impact hole wall (220) are sequentially arranged from inside to outside.

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