Combustor flame tube and aircraft engine comprising same

Abstract

The application discloses a combustion chamber flame tube and an aero-engine comprising the same, which comprises a first section and a second section, the cross-sectional size of the first section is larger than that of the second section, and a transition section extending in the direction from the first section to the second section is further included; fluid inlets and outlets are arranged on the wall surface of the combustion chamber flame tube, one of the fluid inlets and outlets is arranged on the first section, and the other is arranged on the second section; cooling pipes communicating with the fluid inlets and the fluid outlets are arranged in the combustion chamber flame tube; the cooling pipes located in the transition section extend alternately along the circumference and the axis of the flame tube for a corresponding preset distance to connect the cooling pipes located in the first section and the second section. The cooling pipes are arranged in the combustion chamber flame tube, and fluid inlets and outlets are arranged at both ends respectively, so that the whole fluid flow direction is from front to back, the whole flame tube structure can be covered, the influence of the ablation of the flame tube on the inner and outer casings is avoided, the over-temperature phenomenon is avoided, and the normal work of the flame tube is ensured.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aero-engines, and particularly relates to a combustion chamber flame tube and an aero-engine comprising the same. BACKGROUND

[0002] At present, in the design and development process of an aero-engine, in order to obtain specific conditions such as combustion control, flame shape, fuel atomization and mixing of a combustion chamber in a working state, corresponding testing and modification are usually performed on the combustion chamber components of the aero-engine. The testing and modification of the combustion chamber flame tube structure in the aero-engine mainly includes wall temperature parameters, pulsation parameters, dynamic stress parameters and pressure parameters, etc. Meanwhile, the traditional combustion chamber test usually adopts a gas rake, a temperature rake, a thermocouple and the like for measuring gas composition, temperature, pressure and other parameters, and then the results are compared with the CFD simulation calculation results for evaluation, so as to study the combustion inside the combustion chamber.

[0003] Therefore, in order to more clearly grasp the specific combustion state, fuel atomization degree, fuel and air combination degree and other combustion conditions inside the combustion chamber of the fuel in the combustion process, a visual aero-engine combustion chamber flame tube structure needs to be designed, so that the test personnel can see the specific combustion state, fuel atomization degree, fuel and air combination degree and other conditions inside the combustion chamber flame tube through multiple window assemblies during the working process of the combustion chamber, and then the internal physical mechanism such as premixing and flame propagation inside the combustion chamber can be analyzed according to the specific combustion state. Secondly, due to the continuous high-temperature combustion of the combustion chamber, the flame tube is prone to over-temperature phenomenon, so the normal working of the test section of the flame tube cannot be guaranteed, and the cooling circuit cannot be designed inside the flame tube under the traditional system monitoring to cool the entire flame tube to guarantee the temperature bearing effect of the flame tube. SUMMARY

[0004] The present application aims to solve the technical problem of overcoming the defects of the prior art that the flame tube is prone to over-temperature phenomenon and cannot be cooled as a whole, and provides a combustion chamber flame tube and an aero-engine comprising the same.

[0005] The present application solves the above technical problems by the following technical solutions:

[0006] A combustion chamber flame tube, comprising a first section and a second section, the cross-sectional size of the first section being larger than that of the second section, and the combustion chamber flame tube further comprising a transition section extending in the direction from the first section to the second section.

[0007] The wall of the combustion chamber flame tube is provided with a fluid inlet and a fluid outlet, one of which is arranged in the first section and the other is arranged in the second section, and the cooling pipe arranged in the combustion chamber flame tube is connected with the fluid inlet and the fluid outlet;

[0008] The cooling pipe arranged in the transition section extends along the circumferential direction and the axial direction of the flame tube alternately for a corresponding preset distance to connect the cooling pipe arranged in the first section and the cooling pipe arranged in the second section.

[0009] In the technical solution, the cooling pipe is arranged in the combustion chamber flame tube, and the fluid inlet and the fluid outlet are arranged at two ends respectively, so that the whole fluid flows from front to back, and the cooling pipe is arranged in the transition section between the first section and the second section, so that the cooling position can cover the whole flame tube structure, the influence of the ablation of the flame tube on the inner and outer casings is avoided, the over-temperature phenomenon is avoided, and the normal work of the combustion chamber flame tube is ensured.

[0010] Preferably, two fluid inlets and two fluid outlets are arranged, the first cooling pipe and the second cooling pipe connected with the fluid inlets and the fluid outlets are arranged in the combustion chamber flame tube, and at least a part of the first cooling pipe and the second cooling pipe are symmetrically distributed in the combustion chamber flame tube.

[0011] In the technical solution, the fluid can enter from two pipes respectively, compared with only one pipe, the cooling fluid can pass through the whole combustion chamber flame tube to achieve the cooling effect faster, and the two pipes are symmetrically distributed at least in part in the combustion chamber flame tube, so that the machining is facilitated, and the manufacturing efficiency is improved.

[0012] Preferably, the first cooling pipe and the second cooling pipe arranged in the first section extend along the circumferential direction of the first section and rotate, one of the first cooling pipe and the second cooling pipe perpendicular to the fluid inlet direction is close to the transition section, and the other is away from the transition section.

[0013] In the technical solution, one of the first cooling pipe and the second cooling pipe perpendicular to the fluid inlet direction is arranged close to the transition section, and the other is arranged away from the transition section, which considers the related components (such as a nozzle) arranged on the outer wall of the combustion chamber flame tube, and avoids interference with the components; in addition, the first cooling pipe and the second cooling pipe extend along the circumferential direction and rotate, which on one hand increases the cooling area in the combustion chamber flame tube, and on the other hand considers the interference with the wall of the flame tube or other components in the flame tube, so that the path is avoided.

[0014] Preferably, the first cooling pipe and the second cooling pipe of the second section are symmetrically distributed in the combustion chamber flame sleeve and extend along the circumferential direction of the second section and turn back.

[0015] In the technical solution, the symmetrical arrangement of the first cooling pipe and the second cooling pipe of the second section facilitates the machining thereof and improves the machining efficiency; and the extension and turning back of the first cooling pipe and the second cooling pipe along the circumferential direction can increase the cooling area inside the combustion chamber flame sleeve.

[0016] Preferably, the cross section of the combustion chamber flame sleeve is rectangular, and the first cooling pipe and the second cooling pipe both pass through three adjacent side walls of the flame sleeve.

[0017] In the technical solution, the first cooling pipe and the second cooling pipe can pass through three adjacent side walls, so that more side wall area can be covered by one pipe as much as possible, and the first cooling pipe and the second cooling pipe as a whole can cover the side walls of the combustion chamber flame sleeve with a rectangular cross section, so that the cooling position covers the entire combustion chamber flame sleeve structure, ensuring that the combustion chamber flame sleeve can work normally and avoiding the influence of the ablation of the flame sleeve on the inner and outer casings.

[0018] Preferably, the combustion chamber flame sleeve comprises a first side wall, a second side wall and a third side wall; the first cooling pipe or the second cooling pipe extends twice in the first side wall, passes through the second side wall along the circumferential direction and enters the third side wall, extends twice in the third side wall, passes through the second side wall again along the circumferential direction and enters the first side wall again, extends along the circumferential direction after extending in the first side wall, and passes through the first side wall, the second side wall and the third side wall in turn and forms the fluid inlet or the fluid outlet on the third side wall.

[0019] In the technical solution, the extension and bending of the first cooling pipe and the second cooling pipe on the three walls make the connection between each wall, thereby increasing the cooling area and achieving the effect of uniform cooling inside the combustion chamber flame sleeve.

[0020] Preferably, a plurality of window assemblies are arranged on the wall of the combustion chamber flame sleeve, the plurality of window assemblies are distributed along the circumferential direction of the combustion chamber flame sleeve, and the cooling pipes are distributed in the combustion chamber flame sleeve around the window assemblies.

[0021] In the technical solution, the four sides of the combustion chamber flame tube are made visible by arranging the window assembly along the circumference of the combustion chamber test section 2, so that the fuel nozzle injection and atomization, fuel gas mixing combustion, combustion chamber internal stage combustion and premixed flame propagation process can be clearly observed from the window assembly during the test process, thereby mining the internal physical mechanisms such as flow field, temperature field and component field.

[0022] Preferably, a plurality of cooling holes are arranged on the wall surface of the combustion chamber flame tube, and the plurality of cooling holes are arranged on the outer periphery of the window assembly.

[0023] Preferably, the window assembly comprises a first window and a second window, and the first window and the second window are arranged at intervals along the axial direction of the wall surface of the combustion chamber flame tube.

[0024] In the technical solution, the traditional flame tube has small holes on the inner and outer ring structures for air cooling, and the cooling air quantity is strictly required to ensure the cooling effect, which leads to high machining precision requirement of the small holes, while the internal structure of the overall flame tube in the present application is designed with corresponding cooling water channels to cool the entire flame tube to withstand high-temperature gas, and the machining precision requirement is low by controlling the flow rate and detecting the inlet water temperature to ensure the temperature bearing effect of the overall flame tube. In addition, the window assembly is arranged at intervals to facilitate the experimental personnel to observe the internal combustion of the different segmented flame tubes.

[0025] Preferably, the overall combustion chamber flame tube is made of 3D printing, the material used in the 3D printing is a high-temperature resistant alloy material, and the cooling pipeline is distributed along the inner wall of the combustion chamber flame tube.

[0026] In the technical solution, the overall structure is processed by 3D printing technology, which is different from the traditional flame tube which is processed by inner and outer ring split and bolted connection, and the flame tube is directly integrated and 3D printed, which is convenient to process and reliable to disassemble and assemble.

[0027] Preferably, the combustion chamber flame tube comprises a first connecting assembly and a second connecting assembly, and the first end and the second end of the combustion chamber flame tube are connected with the combustion chamber casing through the first connecting assembly and the second connecting assembly, respectively.

[0028] In the technical solution, the two ends of the combustion chamber flame tube are connected with the combustion chamber casing through the connecting assembly, and the front and rear positioning structures ensure that the visualization window around the flame tube structure can be consistent with the axial position of the window on the casing, which is convenient for connection.

[0029] Preferably, the first connecting assembly comprises a centering stop and a gasket, and the first end of the combustion chamber flame tube is connected with the combustion chamber casing through the centering stop and the gasket in sequence.

[0030] Preferably, the second connecting assembly comprises a bolt and a fixing plate, the second end of the combustion chamber flame tube is provided with a plurality of first mounting holes, the fixing plate is provided with a second mounting hole matched with the second end, and the fixing plate is further provided with a third mounting hole in the circumferential direction, the bolt connects the fixing plate with the combustion chamber flame tube through the first mounting hole and the second mounting hole, and the bolt connects the fixing plate with the combustion chamber casing through the third mounting hole.

[0031] In the technical solution, the combustion chamber flame tube is connected with the combustion chamber casing through the front end stop, and the front and rear end positioning structures ensure that the visual windows around the flame tube structure can be consistent with the axial positions of the windows on the casing, thereby facilitating connection; in order to avoid thermal stress caused by expansion and contraction of the combustion chamber flame tube due to cold and hot impact, axial free stretching of the flame tube during operation needs to be ensured, and therefore a gasket is added at the front end positioning structure to form a mixed positioning mode of rear end positioning and auxiliary positioning of the front end stop + gasket.

[0032] The application further provides an aero-engine comprising the combustion chamber flame tube according to any one of the preceding items.

[0033] In the technical solution, the aero-engine using the combustion chamber flame tube has the following effects: the cooling pipeline is arranged in the combustion chamber flame tube, fluid inlets and fluid outlets are arranged at two ends respectively, the entire fluid flow direction is from front to back, the cooling position can cover the entire flame tube structure, the influence of ablation of the flame tube on the inner and outer casings is avoided, over-temperature phenomenon is avoided, and normal operation of the combustion chamber flame tube is ensured.

[0034] The positive progress effect of the application is that the cooling pipeline is arranged in the combustion chamber flame tube, fluid inlets and fluid outlets are arranged at two ends respectively, the entire fluid flow direction is from front to back, the cooling position can cover the entire flame tube structure, the influence of ablation of the flame tube on the inner and outer casings is avoided, over-temperature phenomenon is avoided, and normal operation of the combustion chamber flame tube is ensured. BRIEF DESCRIPTION OF DRAWINGS

[0035] Figure 1 FIG. 1 is a perspective view of an aero-engine combustion chamber flame tube assembly according to an embodiment of the application;

[0036] Figure 2 FIG. 2 is a perspective view of an aero-engine combustion chamber flame tube according to an embodiment of the application;

[0037] Figure 3A side view of a combustion chamber flame tube of an aero-engine according to an embodiment of the present application;

[0038] Figure 4 A view of the cooling ducts inside a combustion chamber flame tube of an aero-engine according to an embodiment of the present application;

[0039] Figure 5 A view of the cooling ducts inside a combustion chamber flame tube of an aero-engine according to an embodiment of the present application;

[0040] Figure 6 A cross-sectional view of a combustion chamber flame tube of an aero-engine according to an embodiment of the present application.

[0041] Reference sign explanation:

[0042] Combustion chamber flame tube 100

[0043] First section 101

[0044] Second section 102

[0045] Transition section 103

[0046] First side wall 1001

[0047] Second side wall 1002

[0048] Third side wall 1003

[0049] Fluid inlet 21

[0050] Fluid outlet 22

[0051] First cooling duct 31

[0052] Second cooling duct 32

[0053] Window position 4

[0054] First window 41

[0055] Second window 42

[0056] Cooling hole 5

[0057] Centering stop 61

[0058] Bolt 62

[0059] Fixing plate 63

[0060] First mounting hole 601

[0061] Second mounting hole 602

[0062] Third mounting hole 603

[0063] bend 7 DETAILED DESCRIPTION

[0064] The present application will be further described by way of examples without thereby limiting the present application to the examples described.

[0065] As Figures 1 to 4 shown, the present embodiment provides a combustion chamber flame tube 100, which comprises a first section 101 and a second section 102, the cross-sectional size of the first section 101 is larger than that of the second section 102, and the combustion chamber flame tube 100 further comprises a transition section 103 extending in the direction from the first section 101 to the second section 102.

[0066] The combustion chamber flame tube 100 is provided with a fluid inlet 21 and a fluid outlet 22 on the wall surface thereof, in the present embodiment, one of the fluid inlet 21 and the fluid outlet 22 is arranged on the first section 101, and the other is arranged on the second section 102, and the combustion chamber flame tube 100 is arranged with cooling ducts communicating with the fluid inlet 21 and the fluid outlet 22.

[0067] The cooling ducts located in the transition section 103 extend alternately along the circumferential direction and the axial direction of the flame tube for a corresponding preset distance, so as to connect the cooling ducts located in the first section 101 and the cooling ducts located in the second section 102.

[0068] The combustion chamber flame tube 100 is arranged with cooling ducts inside, and is respectively provided with a fluid inlet 21 and a fluid outlet 22 at both ends, so that the entire fluid flow direction is from front to back, and the transition section between the first section and the second section is provided with a meandering cooling duct, the cooling position can cover the entire flame tube structure, avoiding the influence on the inner and outer casings after the ablation of the flame tube, avoiding the occurrence of over-temperature phenomenon, and ensuring the normal work of the combustion chamber flame tube 100. In the specific implementation, the fluid inlet 21 is arranged on the side wall of the first section 101, and the fluid outlet 22 is arranged on the side wall of the second section 102. In use, the flame temperature in the first section 101 is higher than that in the second section 102, the fluid inlet 21 is arranged on the first section 101, and the cooling medium can first cool the first section 101, and when passing through the transition section 103 into the second section 102, the cooling duct with larger sealing and larger cooling area can be configured on the second section 102, so that the overall cooling of the flame tube 100 is balanced.

[0069] In the present embodiment, water is used as the cooling medium to flow in the cooling duct inside the combustion chamber flame tube 100 to achieve the cooling effect.

[0070] It should be noted that in other alternative embodiments, a fluid such as a gas can also be used as the cooling medium, and adaptive adjustments can be made according to actual needs as long as the interior of the combustion chamber flame tube 100 can be cooled, which is not specifically limited here.

[0071] In this embodiment, the entire combustion chamber flame tube 100 is made by 3D printing, and the material used for 3D printing is a high-temperature-resistant alloy material. The entire structure is processed by 3D printing technology, which is different from the traditional inner and outer ring split processing and bolt 62 connection. This flame tube is directly integrated and 3D printed, which is convenient to process and reliable to disassemble and assemble.

[0072] It should be noted that in other alternative embodiments, other processes can also be used to process and form the combustion chamber flame tube 100, as long as the combustion chamber flame tube 100 is a whole and does not affect the formation of the cooling pipe inside it, which is not specifically limited here.

[0073] In this embodiment, the fluid inlet 21 and the fluid outlet 22 are both provided with two, and the fluid can enter from two pipes respectively. Compared with only one pipe, the cooling fluid can pass through the entire combustion chamber flame tube 100 to achieve the cooling effect faster. It should be noted that in other alternative embodiments, the diameter of the cooling pipe can be reduced, and multiple cooling pipes can be added to further expand the cooling area inside the combustion chamber flame tube 100, as long as the minimum printable wall thickness of 3D printing can be met. The number and shape of the cooling pipe are not specifically limited here.

[0074] Specifically, the first cooling pipe 31 and the second cooling pipe 32 located in the first section 101 both extend and rotate along the circumferential direction of the first section 101, wherein, as shown in Figure 4 one of the first cooling pipe 31 and the second cooling pipe 32 perpendicular to the fluid inlet direction is close to the transition section 103, and the other is away from the transition section 103.

[0075] One of the first cooling pipe 31 and the second cooling pipe 32 perpendicular to the fluid inlet direction is close to the transition section 103, and the other is away from the transition section 103. This setting considers the related components (such as nozzles, mounting seats, etc.) arranged on the outer wall of the combustion chamber flame tube 100, to avoid interference with them; in addition, the first cooling pipe 31 and the second cooling pipe 32 extend and rotate along the circumferential direction, which on the one hand increases the cooling area inside the combustion chamber flame tube 100, and also considers the interference with the wall of the flame tube or other components inside the flame tube, so the path is avoided.

[0076] It should be noted that in other alternative embodiments, other arrangements can also be provided, for example, the first cooling pipe and the second cooling pipe perpendicular to the fluid inlet direction are simultaneously close to the transition section 103, or simultaneously away from the transition section 103, or are both arranged in the middle of the first section 101, which can be adapted according to actual needs and the structure of the external and internal parts of the flame tube, which is not specifically limited here.

[0077] The first cooling pipe 31 and the second cooling pipe 32 located in the second section 102 are symmetrically distributed in the combustion chamber flame tube 100 and extend and revolve along the circumferential direction of the second section 102. The symmetrical arrangement of the first cooling pipe 31 and the second cooling pipe 32 of the second section 102 facilitates processing, improves processing efficiency; and the extension and revolution of the first cooling pipe 31 and the second cooling pipe 32 along the circumferential direction can increase the cooling area inside the combustion chamber flame tube 100.

[0078] In the present embodiment, the cross section of the combustion chamber flame tube 100 is rectangular, and the first cooling pipe 31 and the second cooling pipe 32 both pass through three adjacent side walls of the flame tube. The first cooling pipe 31 and the second cooling pipe 32 can pass through three adjacent side walls, so that more side wall area can be covered by one pipe as much as possible, so that the first cooling pipe 31 and the second cooling pipe 32 cover the side walls of the combustion chamber flame tube 100 with a rectangular cross section as a whole, so that the cooling position covers the entire combustion chamber flame tube structure, so as to achieve the effect of uniform cooling inside the combustion chamber flame tube 100.

[0079] Specifically, as shown in Figure 1 The combustion chamber flame tube 100 includes a first side wall 1001, a second side wall 1002 and a third side wall 1003; in combination with Figure 4 It can be seen that the fluid inlet 21 is arranged on the first side wall 1001, and the fluid outlet 22 is arranged on the second side wall 1002;

[0080] Taking the first cooling pipe 31 as an example, first, the pipe running of the first cooling pipe 31 in the first section is described: the first cooling pipe 31 extends twice in the first side wall 1001, then passes through the second side wall 1002 and enters the third side wall 1003 along the axial direction, and then extends twice in the third side wall 1003, and then passes through the second side wall 1002 again along the axial direction, and then enters the transition section. In combination with Figure 4 and Figure 5 It can be seen that in the first section 101, the first cooling pipe 31 has two bending portions 7 in the first side wall 1001, three bending portions 7 in the second side wall 1002, and two bending portions 7 in the third side wall 1003.

[0081] Secondly, the pipeline layout of the first cooling pipe 31 in the second section 102 is described: after bending twice in the first side wall 1001, it passes through the second side wall 1002 and enters the third side wall 1003 along the circumference, after bending twice in the third side wall 1003, it passes through the second side wall 1002 again and enters the first side wall 1001 again along the circumference, after bending in the first side wall 1001, it extends along the circumferential direction and passes through the first side wall 1001, the second side wall 1002 and the third side wall 1003 in turn, and forms the fluid outlet 22 on the third side wall 1003. In combination with Figure 4 and Figure 5 It can be seen that in the second section 102, the first cooling pipe 31 has three bending portions 7 in the first side wall 1001, five bending portions 7 in the second side wall 1002, and three bending portions 7 in the third side wall 1003.

[0082] It should be noted that in other alternative embodiments, the cross section of the combustion chamber flame tube 100 can also be circular, and the extension and bending times of the cooling pipe can be 1, 2, 3 or more, which can be adjusted according to actual needs, as long as the cooling effect of the whole flame tube is achieved while avoiding the cooling pipe located in the wall surface and internal structure of the combustion chamber flame tube 100, which is not limited here.

[0083] It should be noted that since the first section 101 is a flame concentration combustion area, the temperature is higher than that of the combustion area of the second section 102, so the curvature of the bending portion 7 of the cooling pipe located in the first section 101 is smaller than that of the cooling pipe located in the second section 102, so that the cooling area is more concentrated.

[0084] In this embodiment, the bending portion 7 of the cooling pipe adopts smooth transition, and through the water cooling structure of entering from below and exiting from above, no flow dead zone can be formed in the whole cooling water flow process, so that the flow channel is smooth. According to the analysis, the pressure drop of the fluid inlet 21 and the fluid outlet 22 is 0.25 MPa, the cooling water flow rate of the two inlets is 0.5 kg / s, the temperature is 293 K, and the cooling water passes through the cooling pipe and withstands high temperature gas in the whole flame tube working process. The outlet temperature of the cooling water under each working condition is less than 340 K, and the wall surface temperature of the combustion chamber flame tube 100 is as high as 1100 K, which can meet the use conditions.

[0085] In this embodiment, as Figure 6As shown, the wall surface of the combustion chamber flame tube 100 is reserved with window positions 4 for a plurality of window assemblies, and the plurality of window assemblies are distributed along the circumference of the combustion chamber flame tube 100, and the cooling channels are distributed around the window assemblies in the combustion chamber flame tube 100. Each window assembly allows the inside of the combustion chamber flame tube 100 to be visible, that is, the observer can see the combustion process and fuel atomization inside the combustion chamber test section through the window assembly during the test process. A plurality of window assemblies are arranged along the circumference of the combustion chamber flame tube 100 to allow the test personnel to observe the inside of the combustion chamber flame tube 100 from multiple angles.

[0086] By arranging the window assemblies along the circumference of the combustion chamber flame tube 100, the inside of the combustion chamber flame tube 100 can be visualized on the four surfaces of the combustion chamber flame tube 100, and through the full-visualization window assembly, the fuel nozzle injection and atomization, fuel-gas mixed combustion, combustion chamber internal stage combustion, and premixed flame propagation process can be clearly observed from the window assembly during the test process. Thus, the internal physical mechanisms such as flow field, temperature field, and component field can be explored.

[0087] At the same time, through the visualized test process, the actual flame shape, temperature field distribution, and flow field shape of each combustion chamber head scheme can be easily obtained, and the oscillation combustion characteristics of the combustion chamber head can be explored through the pulsation pressure measuring point, so that the visualized analysis of the failure problems occurring in the test run and test can be performed.

[0088] Further, the flame shape, temperature field, flow field, and the like obtained through the visualized test process can be directly used to check the CFD and other combustion chamber numerical simulation software, thereby providing a basis for continuously improving the maturity, reliability, and engineering applicability of the software, better guiding the combustion chamber design, further reducing the test cost, and improving the design iteration efficiency.

[0089] In the embodiment, the window assembly includes a first window 41 and a second window 42, the area of the first window 41 is greater than the area of the second window 42, specifically, the first window 41 is located at the first section 101 of the combustion chamber flame tube 100 and is arranged on the second side wall 1002 of the combustion chamber flame tube 100, and the second window 42 is located at the second section 102 of the combustion chamber flame tube 100 and is distributed on the first wall surface, the second wall surface, and the third wall surface, that is, the second window 42 is provided with one second window 42 in the circumferential direction of the second section 102 of the combustion chamber flame tube 100; for the second side wall 1002, the first window 41 and the second window 42 are arranged in the axial direction of the wall surface of the combustion chamber flame tube 100, which facilitates the experimental personnel to view the internal combustion of the flame tube in different sections.

[0090] It should be noted that in other alternative embodiments, two or even more windows can be provided for different wall surfaces, and the number and distribution of the window assemblies are not specifically limited here and can be adjusted as needed.

[0091] In addition, according to the foregoing description, whether the cooling pipe located in the first section 101 or the cooling pipe located in the second section 102 is extended along the wall surface and bent, and the wall surface of the combustion chamber flame tube 100 is provided with a window assembly, so as not to affect the observation of the internal combustion condition by the experimenters, therefore, in combination with the Figure 4 It can be seen that the cooling pipes in the embodiment all reserve the positions of the windows, i.e., are arranged around the first window 41 and the second window 42.

[0092] In the embodiment, the first window 41 and the second window 42 are both configured as high-temperature-resistant and high-pressure-resistant glass. Since there is high temperature inside the combustion chamber flame tube 100 during the test, the temperature-resistant glass is directly impacted by the high temperature, but does not bear high pressure. The high-temperature-resistant glass is also called high-temperature glass, which can reach or bear the corresponding temperature under certain temperature conditions, and still maintains the original permeability and transparency of the glass under high-temperature environment. The high-temperature-resistant glass referred to in this paper refers to the glass that can bear more than 700K (Kelvin). The high-pressure-resistant glass refers to the glass that still ensures the integrity of the overall structure without breaking under the impact of a certain pressure. The high-pressure-resistant glass referred to in this paper refers to the glass that can bear more than 1Mpa pressure.

[0093] Specifically, the first window 41 and the second window 42 both use quartz glass, which can bear high temperature, and by increasing the thickness of the quartz glass, it can bear a certain high pressure, meeting the design requirements of bearing both high temperature and high pressure.

[0094] It should be noted that in other alternative embodiments, the window can also use glass of other materials, as long as it can achieve high-temperature resistance and high-pressure resistance, and can be adjusted as needed according to actual conditions, which is not specifically limited here.

[0095] In the embodiment, a plurality of cooling holes 5 are provided on the wall surface of the combustion chamber flame tube 100, and the plurality of cooling holes 5 are arranged on the outer periphery of the window assembly. Since the traditional flame tube is provided with small holes on the inner and outer ring structures for cooling by air, the first end and the second end are connected with the combustion chamber casing through the first connecting assembly and the second connecting assembly, respectively.

[0096] Specifically, the first connecting assembly includes a centering stop 61 and a gasket (not shown in the figure), and the first end of the combustion chamber flame tube 100 is connected with the combustion chamber casing through the centering stop 61 and the gasket in sequence;

[0097] The second connecting assembly comprises a bolt 62 and a fixing plate 63, the second end of the combustion chamber flame tube 100 is provided with a plurality of first mounting holes, the fixing plate 63 is provided with a second mounting hole 602 matched with the second end, and a third mounting hole is further provided in the circumference of the fixing plate 63, the bolt 62 connects the fixing plate 63 with the combustion chamber flame tube 100 through the first mounting hole 601 and the second mounting hole 602, and the bolt 62 connects the fixing plate 63 with the combustion chamber casing through the third mounting hole 603.

[0098] The combustion chamber flame tube 100 is connected with the combustion chamber casing through the front end stopper positioning, and the front and rear end positioning structures ensure that the visual window assembly around the flame tube structure can be consistent with the axial position of the window on the casing, thereby facilitating connection; meanwhile, in order to avoid thermal stress caused by expansion and contraction of the combustion chamber flame tube 100 due to cold and hot impact, the axial free stretching of the flame tube during operation needs to be ensured, and therefore a gasket is added at the front end positioning structure to form a mixed positioning mode of rear end positioning and front end stopper + gasket auxiliary positioning.

[0099] It should be noted that in other alternative embodiments, other connection modes can also be adopted as long as the axial position of the window assembly on the window on the casing can be consistent and the flame tube can freely stretch in the axial direction during thermal expansion and contraction, which is not limited here.

[0100] The application further provides an aero-engine comprising the combustion chamber flame tube 100 according to any one of the above.

[0101] The aero-engine adopting the combustion chamber flame tube 100 has the following effects: the cooling pipeline is arranged inside the combustion chamber flame tube 100, and fluid inlets 21 and fluid outlets 22 are respectively arranged at two ends, so that the entire fluid flow direction is from front to back, the cooling position can cover the entire flame tube structure, the influence of flame tube ablation on the inner and outer casings is avoided, the over-temperature phenomenon is avoided, and the normal work of the combustion chamber flame tube 100 is ensured.

[0102] In summary, the combustion chamber flame tube 100 and the aero-engine comprising the same provided in the embodiment have the following advantages:

[0103] 1. The cooling pipeline is arranged inside the combustion chamber flame tube 100, and fluid inlets 21 and fluid outlets 22 are respectively arranged at two ends, so that the entire fluid flow direction is from front to back, the cooling position can cover the entire flame tube structure, the influence of flame tube ablation on the inner and outer casings is avoided, the over-temperature phenomenon is avoided, and the normal work of the combustion chamber flame tube 100 is ensured.

[0104] 2、The flame tube for the aero-engine combustion chamber test device provided by the application is directly integrally 3D printed, is convenient to process, and is reliable to disassemble and assemble, which is different from the traditional flame tube that is split processed and connected by bolts.

[0105] 3、The flame tube for the aero-engine combustion chamber test device provided by the application is directly integrally 3D printed, is convenient to process, and is reliable to disassemble and assemble, which is different from the traditional flame tube that is split processed and connected by bolts.

[0106] 4、The flame tube for the aero-engine combustion chamber test device provided by the application is directly integrally 3D printed, is convenient to process, and is reliable to disassemble and assemble, which is different from the traditional flame tube that is split processed and connected by bolts.

[0107] Although the specific embodiments of the present application are described above, those skilled in the art should understand that this is only an example, and the protection scope of the present application is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present application, and such changes and modifications all fall within the protection scope of the present application.

Claims

1. A combustion chamber flame channel, characterized by, The combustion chamber flame tube comprises a first section and a second section, the cross-sectional size of the first section is larger than that of the second section, and the combustion chamber flame tube further comprises a transition section extending from the first section to the second section; The wall surface of the combustion chamber flame tube is provided with a fluid inlet and a fluid outlet, one of the fluid inlet and the fluid outlet is arranged on the first section, and the other is arranged on the second section, and the combustion chamber flame tube is arranged with a cooling pipe communicating with the fluid inlet and the fluid outlet; The cooling pipe in the transition section extends along the circumferential direction and the axial direction of the flame tube for a corresponding preset distance to connect the cooling pipe in the first section and the cooling pipe in the second section. The fluid inlet and the fluid outlet are provided with two, and the combustion chamber flame tube is arranged with a first cooling pipe and a second cooling pipe communicating with the fluid inlet and the fluid outlet, and at least a part of the first cooling pipe and the second cooling pipe is symmetrically distributed in the combustion chamber flame tube. The first cooling pipe and the second cooling pipe in the first section extend and turn along the circumferential direction of the first section, wherein one of the first cooling pipe and the second cooling pipe perpendicular to the fluid inlet direction is close to the transition section, and the other is away from the transition section.

2. The combustor flame tube of claim 1, wherein, The first cooling pipe and the second cooling pipe in the second section are symmetrically distributed in the combustion chamber flame tube and extend and turn along the circumferential direction of the second section.

3. The combustion chamber flame channel of claim 1 or 2, wherein The cross section of the combustion chamber flame tube is rectangular, and the first cooling pipe and the second cooling pipe pass through three adjacent side walls of the flame tube.

4. The combustor flame tube of claim 3, wherein, The combustion chamber flame tube comprises a first side wall, a second side wall and a third side wall; The first cooling pipe or the second cooling pipe extends twice in the first side wall, then passes through the second side wall along the circumferential direction and enters the third side wall, then passes through the second side wall again along the circumferential direction and enters the first side wall again, then extends along the circumferential direction and passes through the first side wall, the second side wall and the third side wall in turn, and forms the fluid inlet or the fluid outlet on the third side wall.

5. The combustor flame tube of claim 1, wherein The wall surface of the combustion chamber flame tube is provided with a plurality of window assemblies, and the plurality of window assemblies are distributed along the circumferential direction of the combustion chamber flame tube, and the cooling pipe is distributed in the combustion chamber flame tube around the window assembly.

6. The combustor flame tube of claim 5, wherein, The wall surface of the combustion chamber flame tube is provided with a plurality of cooling holes, and the plurality of cooling holes are arranged on the outer periphery of the window assembly. And / or, the window assembly comprises a first window and a second window, and the first window and the second window are arranged at intervals along the axial direction of the wall surface of the combustion chamber flame tube.

7. The combustor flame tube of claim 1, wherein The whole combustion chamber flame tube is made of 3D printing, the material used in the 3D printing is high-temperature resistant alloy material, and the cooling pipe is distributed along the inner wall of the combustion chamber flame tube.

8. The combustor flame tube of claim 1, wherein, The combustion chamber flame tube comprises a first connecting assembly and a second connecting assembly, and opposite first and second ends of the combustion chamber flame tube are connected with a combustion chamber casing through the first and second connecting assemblies respectively.

9. The combustor flame tube of claim 8, wherein, The first connecting assembly comprises a centering stop and a gasket, and the first end of the combustion chamber flame tube is connected with the combustion chamber casing through the centering stop and the gasket in sequence. And / or the second connecting assembly comprises a bolt and a fixing plate, the second end of the combustion chamber flame tube is provided with a plurality of first mounting holes, the fixing plate is provided with a second mounting hole matched with the second end, and the fixing plate is further provided with a third mounting hole in the circumferential direction, the bolt connects the fixing plate with the combustion chamber flame tube through the first and second mounting holes, and the bolt connects the fixing plate with the combustion chamber casing through the third mounting hole.

10. An aeroengine characterised in that, The combustion chamber flame tube comprises the combustion chamber flame tube according to any one of claims 1-9.

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