Combustion chamber, gas turbine engine, combustion organization method

Abstract

The invention provides a combustion chamber, a gas turbine engine, and a combustion organization method. Wherein the combustion chamber comprises a combustion chamber casing, a combustion chamber outer casing and a combustion chamber inner casing; the flame tube is arranged between the combustion chamber outer casing and the combustion chamber inner casing and comprises a tube wall, and an inner cavity used for fuel combustion is formed by the tube wall; wherein the cylinder wall is provided with a plurality of cooling holes communicated with the inner cavity and the outer side of the flame cylinder, the cooling holes are used for introducing cooling gas into the inner cavity to cool the cylinder wall when fuel is combusted, and at least one partition plate is arranged between the cylinder wall and the combustion chamber casing; in the radial direction of the flame tube, one end of the partition plate makes contact with the combustion chamber casing, and a gap is formed between the other end of the partition plate and the tube wall and ranges from 0.2 mm to 2 mm.

Description

Technical Field

[0001] The present invention relates to the field of combustion chambers, and in particular to a combustion chamber, a gas turbine engine, and a combustion organization method. Background Art

[0002] As a power device, aircraft engines are widely used in aviation power, electricity, industry, ships, and defense land use. Among the technical difficulties in the field of power devices, oscillating combustion is a key technical challenge. During the operation of aircraft engines, the combustion chamber of aircraft engines sometimes has unstable combustion phenomena with large pressure pulsations. For example, in some aircraft engines that use lean premixed preevaporation combustion technology to reduce the emission of pollutants mainly composed of nitrogen oxides (NOx), the flame in the combustion chamber often works in a near-extinguishing working condition during combustion, which is easily disturbed by the outside world. When thermal-acoustic coupling occurs, it is easy to cause oscillating combustion, which will affect the stable combustion working range of the power device combustion at the least, and cause hardware ablation of the hot end components of the power device combustion chamber or damage to the hardware of other components at the worst. In severe cases, it will threaten the operation safety of the entire power device. The unstable combustion phenomenon caused by oscillating combustion can easily lead to engine vibration, increased pollutant emissions, nozzle ablation, etc. Therefore, oscillating combustion is a problem that must be avoided as much as possible in the combustion chamber of aircraft engines.

[0003] In order to solve the oscillating combustion problem in aircraft engines, existing solutions include using active actuators to monitor the pulsating pressure or other aerodynamic parameter signals in the combustion device in real time, and actively increase the corresponding anti-phase excitation to the inlet gas path or fuel supply through the external excitation of the control system according to the oscillation frequency of the monitored pulsating pressure, so as to reduce the pulsating pressure in the combustion device and suppress or eliminate thermal-acoustic coupling. However, this method requires the addition of additional control systems and actuators, as well as more complex control systems, which results in additional technical difficulty and increased costs.

[0004] In the Chinese invention patent application filed by the applicant with publication number CN116951475A and titled “Combustion chamber of aircraft engine and aircraft engine”, it is proposed that a partition be provided between the barrel wall of the flame tube and the combustion chamber casing, and the partition cover at least part of the cooling holes along the axial direction of the flame tube. When thermoacoustic coupling oscillation occurs during combustion in the combustion chamber, the partition can change the waveform of the sound wave located between the barrel wall and the combustion chamber casing near the covered cooling hole, so that the waveform of the sound wave in the flame tube and the waveform near the cooling hole change from the same direction to the opposite direction, thereby increasing the pulsating pressure difference of the sound wave inside and outside the flame tube, thereby increasing the dissipation of the sound energy of the flame tube through the cooling hole, further weakening the oscillating combustion, and improving the combustion stability of the combustion chamber.

[0005] However, the inventors found in subsequent studies that the above solution has the risk of ablation of the flame tube wall. Summary of the invention

[0006] The present invention provides a combustion chamber, a gas turbine engine and a combustion organization method, which avoid the risk of ablation of the cylinder wall of the flame tube while retaining the effect of suppressing oscillating combustion by setting a baffle.

[0007] An object of the present invention is to provide a combustion chamber.

[0008] An object of the present invention is to provide a gas turbine engine.

[0009] An object of the present invention is to provide a method for burning tissue.

[0010] The first aspect of the present invention discloses a combustion chamber of an aircraft engine, comprising:

[0011] A combustion chamber casing, comprising an outer combustion chamber casing and an inner combustion chamber casing;

[0012] A flame tube is disposed between the outer casing of the combustion chamber and the inner casing of the combustion chamber, and comprises a tube wall, wherein the tube wall forms an inner cavity for fuel combustion;

[0013] The cylinder wall is provided with a plurality of cooling holes connecting the inner cavity and the outer side of the flame tube, and the cooling holes are used to introduce cooling gas into the inner cavity to cool the cylinder wall when the fuel is burning. At least one partition is provided between the cylinder wall and the combustion chamber casing; wherein, along the radial direction of the flame tube, one end of the partition is in contact with the combustion chamber casing, and the other end has a gap with the cylinder wall, and the gap is 0.2mm to 2mm.

[0014] In some embodiments, the partition is provided with at least one through hole, and the through hole can connect adjacent spaces separated by the partition.

[0015] In some embodiments, the shape of the through hole includes a circular hole, a rectangular hole, a diamond hole, a polygonal hole, or an irregular shape.

[0016] In some embodiments, the baffle extends along an extension direction of an axis of the flame tube.

[0017] In some embodiments, a folding ear with a connecting hole is provided on the side of the partition that contacts the casing.

[0018] In some embodiments, the folded ears of the partition are in contact with the inner wall of the casing and are fixed to the casing via a threaded connection structure.

[0019] In some embodiments, the combustion chamber of the aircraft engine is an annular combustion chamber, and the cylinder wall includes an outer cylinder wall that is coaxial with the combustion chamber outer casing and the combustion chamber inner casing and closer to the combustion chamber outer casing relative to the combustion chamber inner casing, and an inner cylinder wall that is coaxial with the outer cylinder wall and closer to the combustion chamber inner casing relative to the combustion chamber outer casing, and a plurality of cooling holes are provided on the outer cylinder wall and the inner cylinder wall, and at least one partition is provided between the outer cylinder wall and the combustion chamber outer casing and / or between the inner cylinder wall and the combustion chamber inner casing.

[0020] In some embodiments, a plurality of the partitions are provided between the outer cylinder wall and the outer casing of the combustion chamber, and the plurality of partitions are arranged uniformly or unevenly along the circumference of the flame cylinder; and / or, a plurality of the partitions are provided between the inner cylinder wall and the outer casing of the combustion chamber, and the plurality of partitions are arranged uniformly or unevenly along the circumference of the flame cylinder.

[0021] In some embodiments, the combustion chamber further comprises:

[0022] A front diffuser is arranged upstream of the flame tube along the air intake direction, and is used to expand the pressure and reduce the speed of the gas flowing into the flame tube;

[0023] A plurality of combustion assemblies are arranged at the flame tube inlet along the circumference of the flame tube, and the combustion assemblies include a pre-combustion stage fuel nozzle nozzle located in the middle, a main combustion stage fuel nozzle nozzle surrounding the central fuel nozzle nozzle, a first swirler and a second swirler located radially inside the main combustion stage fuel nozzle nozzle and arranged around the pre-combustion stage fuel nozzle nozzle, a third swirler located between the main combustion stage fuel nozzle nozzle and the second swirler, and a fourth swirler surrounding the main combustion stage fuel nozzle nozzle.

[0024] In some embodiments, the first swirler and the second swirler are radial swirlers, the third swirler is an axial swirler, and the fourth swirler is a radial swirler.

[0025] Based on the combustion chamber introduced in the above embodiment, a partition is arranged between the cylinder wall of the flame tube and the combustion chamber casing, and the partition is distributed in a certain regular pattern along the circumference of the flame tube. When thermal-acoustic coupling oscillation occurs during combustion in the combustion chamber, the partition can change the waveform of the sound wave between the cylinder wall and the combustion chamber casing, so that the sound wave between the cylinder wall and the combustion chamber casing is converted from a traveling wave that is approximately in phase with the sound wave in the flame tube to a standing wave or a slowly rotating standing wave, thereby increasing the rotational interaction between the sound wave in the flame tube and the sound wave in the cavity outside the flame tube, that is, the number of rotations of one wave around another wave in a certain period of time, thereby increasing the dissipation of sound energy through the cooling holes on the flame tube, further weakening the oscillating combustion, and improving the combustion stability of the combustion chamber.

[0026] A second aspect of the present invention discloses a gas turbine engine comprising the combustion chamber described above.

[0027] The third aspect of the present invention discloses a method for organizing combustion, in which a partition is arranged between the cylinder wall of the flame tube and the combustion chamber casing, and the partition is distributed along the circumference of the flame tube. When thermal-acoustic coupling oscillation occurs during combustion in the combustion chamber, the waveform of the sound wave between the cylinder wall and the combustion chamber casing is changed by the partition, so that the sound wave between the cylinder wall and the combustion chamber casing is converted from a traveling wave that is approximately in phase with the sound wave in the flame tube to a standing wave or a slowly rotating standing wave; wherein, along the radial direction of the flame tube, the partition is arranged so that one end of the partition is in contact with the combustion chamber casing, and the other end has a gap with the cylinder wall, and the gap is 0.2mm to 2mm; so that the partition and the cylinder wall remain non-contact during the combustion process. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments. In the accompanying drawings, the same reference numerals always represent the same features. It should be noted that these drawings are only examples and are not drawn according to the conditions of equal scale, and should not be used as a limitation on the actual scope of protection required by the present invention, wherein:

[0029] Figure 1 A schematic structural diagram of a combustion chamber of a gas turbine engine according to an embodiment;

[0030] Figure 2 It is a partial enlarged structural schematic diagram of a combustion assembly of a combustion chamber of an embodiment;

[0031] Figure 3 It is a partial cross-sectional structural schematic diagram of a combustion chamber of an embodiment;

[0032] Figures 4a to 4d For multiple embodiments corresponding to Figure 3 The schematic diagram of the AA-direction cross-sectional structure shown;

[0033] Figure 5 It is a schematic structural diagram of a partition plate between the outer tube wall of a flame tube of a combustion chamber and an outer casing in one embodiment;

[0034] Figure 6 It is a schematic structural diagram of a partition plate between the inner cylinder wall of the flame tube and the inner casing of a combustion chamber in one embodiment;

[0035] Figure 7a , Figure 7b They are respectively Figure 4d Numerical simulation diagram of the distribution of acoustic pressure modulus values ​​in the flame tube cavity, the first cavity and the second cavity before and after the baffle structure of the embodiment shown;

[0036] Figure 8a , Figure 8b They are respectively Figure 4d Numerical simulation diagram of the sound pressure phase distribution in the flame tube cavity, the first cavity and the second cavity before and after the partition structure of the illustrated embodiment. DETAILED DESCRIPTION

[0037] Reference will now be made in detail to various embodiments of the present invention, examples of which are shown in the accompanying drawings and described below. Although the present invention will be described in conjunction with the exemplary embodiments, it should be appreciated that this specification is not intended to limit the present invention to those exemplary embodiments. On the contrary, the present invention is intended to cover not only these exemplary embodiments, but also various alternative forms, modifications, equivalent forms and other embodiments that may be included within the spirit and scope of the present invention as defined by the appended claims.

[0038] In the following description, the directions or positional relationships indicated by "axial", "radial", "circumferential", "upstream", "downstream", "inner", "outer" or other directional terms are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, "upstream" and "downstream" are divided according to the direction of airflow, for example, air flows from "upstream" to "downstream".

[0039] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment" and / or "an embodiment" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0040] The combustion chamber introduced below is applicable to gas turbine engines, taking aircraft engines as an example, but is not limited to this. For example, it can also be applicable to ship gas turbines, ground gas turbines and other scenarios.

[0041] like Figures 1 to 6 As shown, in a gas turbine engine, taking an aircraft engine as an example, the combustion chamber may include a combustion chamber casing and a flame tube.

[0042] The combustion chamber casing comprises an outer combustion chamber casing 11 and an inner combustion chamber casing 12. Relative to the axis of the aircraft engine, the outer combustion chamber casing 11 is the part of the combustion chamber casing located radially outward, and the inner combustion chamber casing 12 is the part of the combustion chamber casing located radially inward.

[0043] The flame tube is arranged between the outer casing 11 of the combustion chamber and the inner casing 12 of the combustion chamber, and the flame tube includes a tube wall, and the tube wall forms an inner cavity 23 for fuel combustion. Figures 1 to 4d The annular combustion chamber is shown. At this time, relative to the axis of the aircraft engine, the cylinder wall includes an outer cylinder wall 21 located on the radial outside and an inner cylinder wall 22 located on the radial inside. The combustion chamber casing 11, the combustion chamber casing 12, the outer cylinder wall 21 and the inner cylinder wall 22 are all coaxial annular structures, and the cylinder wall is a double annular structure including an annular inner cylinder wall 22 and an annular outer cylinder wall 21. In some embodiments not shown in the figure, the combustion chamber can also be a single-tube combustion chamber, in which case the cylinder wall of the flame tube is an overall cylindrical structure. In some embodiments, the combustion chamber can also be an annular tube combustion chamber.

[0044] There are multiple cooling holes 212 on the cylinder wall that connect the inner cavity 23 and the outer side of the flame tube. The cooling holes 212 are through-hole structures. The cooling holes 212 are used to pass cooling gas into the inner cavity 23 to cool the cylinder wall when the fuel is burned, so as to perform air film cooling on the cylinder wall. At least one partition 6 is provided between the cylinder wall and the combustion chamber casing. On the axis of the flame tube, the projection of the partition 6 covers the projection of at least one cooling hole 212.

[0045] A cavity is formed between the cylinder wall and the combustion chamber casing, a first cavity 121 is formed between the cylinder wall and the combustion chamber outer casing 11, and a second cavity 122 is formed between the cylinder wall and the combustion chamber casing 12. In the embodiment where the combustion chamber is an annular combustion chamber, the first cavity 121 and the second cavity 122 are both full annular cavities. In a single-tube combustion chamber, the first cavity 121 and the second cavity 122 are both semi-annular cavities, which are interconnected to form a full annular cavity.

[0046] A partition is provided in the first cavity 121 or the second cavity 122. On the axis of the flame tube, the projection of the partition 6 covers the projections of at least several cooling holes 212, that is, along the axial direction of the flame tube, the axial position of the partition covers the axial position of at least several cooling holes 212, that is, if the three-dimensional coordinate is established with the axis of the flame tube as the x-axis, the coordinate range of at least one cooling hole on the x-axis is within the coordinate range of the partition on the x-axis. When the combustion chamber is an annular combustion chamber, the axis of the flame tube is collinear with the axis of the aircraft engine. When the combustion chamber is a single-tube combustion chamber or an annular tube combustion chamber, the axis of the flame tube is not collinear with the axis of the aircraft engine.

[0047] The above Figures 1 to 3 The structure is similar to the case previously applied for by the applicant (Chinese invention patent application with publication number CN116951475A and title “Combustion chamber of aircraft engine and aircraft engine”). The above introduction is made to illustrate the completeness of the solution.

[0048] In some embodiments, Figure 3 and Figures 4a to 4d As shown, the combustion chamber of the aircraft engine is an annular combustion chamber, and the cylinder wall includes an outer cylinder wall 21 coaxial with the combustion chamber outer casing 11 and the combustion chamber outer casing 12 and closer to the combustion chamber outer casing 11 relative to the combustion chamber inner casing 12, and an inner cylinder wall 22 coaxial with the outer cylinder wall 21 and closer to the combustion chamber inner casing 12 relative to the combustion chamber outer casing 11. A plurality of cooling holes 212 are provided on the outer cylinder wall 21 and the inner cylinder wall 22, and at least one partition 6 is provided between the outer cylinder wall 21 and the combustion chamber outer casing 11 and between the inner cylinder wall 22 and the combustion chamber inner casing 12. In the annular combustion chamber, it has been experimentally verified that the effect of setting a partition to reduce oscillating combustion is obvious.

[0049] Regarding the structure of setting a baffle, the inventors found in practice that although it can achieve the effect of reducing oscillating combustion and improving the combustion stability of the combustion chamber, long-term research has found that the wall of the flame tube of the combustion chamber using a baffle structure is more prone to ablation, especially after the combustion chamber has been running for a long time.

[0050] After in-depth research, the inventors found that the reason why the wall of the flame tube is burned is that the temperature of the flame tube is relatively high during operation (the flame tube contains high-temperature combustion gas, and the chamber between the flame tube and the inner casing or outer casing of the combustion chamber is filled with air). Therefore, during the operation of the combustion chamber, the flame tube contacts the partition after expansion, and the temperature of the end of the partition that contacts the wall of the flame tube is also higher, causing the part of the partition at this end to expand. As a result, the partition will block at least part of the flow area of ​​the cooling hole 212, resulting in the risk of burning of the wall of the flame tube.

[0051] In some embodiments, Figure 3 and Figures 4a to 4d As shown, at least one partition plate 6 is provided between the outer cylinder wall 21 and the combustion chamber casing 11 and between the inner cylinder wall 22 and the combustion chamber casing 12, and the number of partition plates 6 may be one or more. Figures 4a to 4d In each of the embodiments shown, along the radial direction of the flame tube, the two ends of the partition 6 extend to the combustion chamber casing and the tube wall respectively, one end of the partition 6 is directly in contact with the combustion chamber casing 11 or the combustion chamber casing 12, and the other end of the partition 6 has a gap G of 0.2mm to 2mm with the tube wall. Figure 4a As shown, a partition 6a is provided between the outer cylinder wall 21 and the combustion chamber casing 11, and a partition 6b is provided between the inner cylinder wall 22 and the combustion chamber casing 12. Figure 4b to Figure 4dAs shown, a plurality of baffles 6a are provided between the outer cylinder wall 21 and the outer casing 11 of the combustion chamber, and the plurality of baffles 6a are arranged uniformly or non-uniformly along the circumference of the flame tube; and / or a plurality of baffles 6b are provided between the inner cylinder wall 22 and the outer casing 11 of the combustion chamber, and the plurality of baffles 6b are arranged uniformly or non-uniformly along the circumference of the flame tube. Figure 4b In the embodiment shown, two baffles 6a are provided between the outer cylinder wall 21 and the combustion chamber outer casing 11, and the two baffles 6a are arranged non-uniformly along the circumference of the flame tube, and two baffles 6b are provided between the inner cylinder wall 22 and the combustion chamber outer casing 11, and the two baffles 6b are arranged non-uniformly along the circumference of the flame tube. Figure 4c In the embodiment shown, three baffles 6a are provided in the first chamber 121 between the outer cylinder wall 21 and the combustion chamber outer casing 11, and the three baffles 6 are evenly arranged along the circumferential direction (i.e., the three baffles are arranged at intervals of 120°), and three baffles 6b are provided in the second chamber 122 between the inner cylinder wall 22 and the combustion chamber casing 12, and the three baffles 6b are evenly arranged along the circumferential direction (i.e., the three baffles are arranged at intervals of 120°). Figure 4d In the illustrated embodiment, two baffles 6a are provided between the outer cylinder wall 21 and the combustion chamber outer casing 11, and the two baffles 6a are evenly arranged along the circumference of the flame tube (i.e., the two are arranged at an interval of 180°), and two baffles 6b are provided between the inner cylinder wall 22 and the combustion chamber outer casing 11, and the two baffles 6b are evenly arranged along the circumference of the flame tube (i.e., the two are arranged at an interval of 180°). The inventors have found that providing multiple baffles can further improve the acoustic energy dissipation effect of the cooling holes 212.

[0052] The following combination Figure 7a , Figure 7b as well as Figure 8a , Figure 8b The principle by which the combustion chamber structure introduced above reduces the effect of oscillating combustion is explained in detail.

[0053] like Figure 7a as well as Figure 8a As shown, when the combustion chamber undergoes oscillatory combustion and the oscillation amplitude is high, the sound waves generated in the inner cavity of the flame tube are mostly circumferential traveling waves. By arranging a partition 6 between the tube wall of the flame tube and the combustion chamber casing, and the partition 6 extends along the axial direction of the flame tube, when the combustion chamber undergoes thermal-acoustic coupling oscillation, the sound waves generated in the inner cavity 23 are transmitted to the chamber between the tube wall and the combustion chamber casing through the upstream end of the flame tube and the cooling hole 212, as shown in FIG. Figure 7b as well as Figure 8bAs shown, after the partition 6 is provided, the partition 6 can change the waveform of the sound waves in the first cavity 121 and the second cavity 122, so that the sound waves in the first cavity 121 and the second cavity 122 are transformed from traveling waves that are approximately in phase with the sound waves in the flame tube cavity 23 to standing waves or slowly rotating standing waves, thereby increasing the rotational interaction between the sound waves in the flame tube cavity 23 and the sound waves in the first cavity 121 and the second cavity 122, that is, the number of circles that one wave rotates around another wave in a certain period of time, thereby enhancing the dissipation of sound energy through the cooling holes 212 on the flame tube wall, further weakening the oscillating combustion, and improving the combustion stability of the combustion chamber. Figure 7a as well as Figure 8a As shown, before the partitions are arranged in the inner and outer annular cavities of the combustion chamber, the sound waves in the flame tube cavity 23, the first cavity 121, and the second cavity 122 are all traveling waves, which basically keep the same phase and rotate at the same speed. The sound waves in the three cavities are relatively static, and the sound energy dissipation through the cooling holes 212 on the flame tube wall is small; Figure 7b as well as Figure 8b As shown, the inner and outer ring cavities in the combustion chamber are arranged as follows Figure 4d After the baffle structure of the embodiment shown, the sound waves in the flame tube inner cavity 23 and the first cavity 121 are transformed from traveling waves to rotating standing waves, and the sound waves in the second cavity are transformed from traveling waves to standing waves. Due to the different rotation speeds and phases of the sound waves in the three cavities, the sound energy dissipation through the cooling holes 212 on the flame tube wall is enhanced, so that the energy maintaining the combustion oscillation in the inner cavity 23 is reduced and the combustion oscillation amplitude is attenuated.

[0054] The inventors found that the beneficial effect of setting a gap G of 0.2mm-2mm is that when the gap is greater than 2mm, the effect of suppressing combustion decreases significantly. The reason may be that when the gap is greater than 2mm, the effect of converting the sound wave from a traveling wave to a standing wave due to the blocking effect of the partition is significantly reduced. When the gap is less than 0.2mm, the influence caused by thermal expansion cannot be completely eliminated.

[0055] Preferably, if Figure 5 as well as Figure 6 As shown, at least one through hole 602 may be provided on the partition 6a and the partition 6b respectively. The through hole 602 may be located in the middle area of ​​the partition 6 as much as possible, rather than at both ends. The through hole 602 may connect the adjacent spaces separated by the partition. The inventors have found that this can make the oscillation combustion weakening effect more uniform and effective. The principle may be that the through hole 602 is provided so that the chamber separated by the partition forms a Helmholtz resonator, which further increases the effect of acoustic energy dissipation.

[0056] It can be understood that the shape of the through hole 602 can be a circular hole, a rectangular hole, a diamond hole, a polygonal hole (i.e. a polygon larger than a quadrilateral, such as a pentagon or a hexagon), or an irregularly shaped hole (e.g. a combination of the above shapes, such as a combination of a circular hole and a rectangular hole, or an irregular shape such as a star). Figure 5 and Figure 6 In the illustrated embodiment, a circular through hole 602 is respectively provided on the partition 6a and the partition 6b, and the diameter of the hole is between 1 mm and 5 mm, so as to further optimize the effect of suppressing oscillating combustion by forming a Helmholtz resonator.

[0057] In some embodiments, along the radial direction of the flame tube, the two ends of the partition 6 extend to the combustion chamber casing and the cylinder wall respectively, with a gap of 0.2 to 2 cm between the cylinder wall and the casing in direct contact. Figure 5 and Figure 6 As shown, the structure in which the partition 6 is fixed to the casing can be that the partition 6 is provided with a plurality of folding ears with connection holes 603 on one side, and is fixed to the casing by bolts. It can be understood that other threaded connection structures can also be used, and the bolt structure is not limited. Figure 5 In the embodiment shown, two folding ears 601 with connection holes are provided on the side of the partition 6a in contact with the outer casing 11. The folding ears extend in the lateral direction, contact the inner wall of the outer casing 11, and are fixed to the outer casing by bolts. Figure 6 In the illustrated embodiment, two folding ears 601 with connecting holes 603 are provided on the side of the partition 6b in contact with the inner casing 12, one folding ear extends in the lateral direction, contacts the inner wall of the inner casing, and is fixed to the inner casing by bolts, and the other folding ear extends in the radial direction, contacts the inner side of the inner casing end wall, and is fixed to the inner casing end wall by bolts.

[0058] In some embodiments, Figures 1 to 4a to Figure 4d As shown, the combustion chamber of the aircraft engine also includes a pre-diffuser 3 and a plurality of combustion components.

[0059] The pre-diffuser 3 is arranged upstream of the flame tube along the air intake direction. The pre-diffuser 3 is used to expand and reduce the speed of the gas flowing into the flame tube. When the aircraft engine is working, the compressed air from the high-pressure compressor flows toward the flame tube after the expansion and speed reduction effect of the pre-diffuser 3.

[0060] A plurality of combustion assemblies are arranged at the entrance of the flame tube along the circumference of the flame tube, and the combustion assemblies include a pre-combustion stage fuel nozzle nozzle 50 located in the middle, a main combustion stage fuel nozzle nozzle 55 surrounding the central fuel nozzle nozzle, a first swirler 51 and a second swirler 52 located radially inside the main combustion stage fuel nozzle nozzle 55 and arranged around the pre-combustion stage fuel nozzle nozzle 50, a third swirler 53 located between the main combustion stage fuel nozzle nozzle 55 and the second swirler 52, and a fourth swirler 54 surrounding the main combustion stage fuel nozzle nozzle 55. In this embodiment, as shown in FIG. Figure 2 The air flow path shown by the middle dotted line, when the aircraft engine is working, a stream of compressed air passes through the first swirler 51, and another stream of compressed air passes through the second swirler 52 and then mixes with the fuel passing through the pre-combustion stage fuel nozzle nozzle 50, a stream of compressed air passes through the third swirler 53, and another stream of compressed air passes through the fourth swirler 54 and then mixes with the fuel passing through the main combustion stage fuel nozzle nozzle 50, and finally all the oil-gas mixed gases intersect and mix in the flame tube cavity. The combustion assembly of this embodiment can realize lean premixed preevaporation combustion, which can effectively reduce nitrogen oxides, but it is more likely to produce oscillating combustion. With the setting of the baffle, this embodiment can effectively reduce nitrogen oxides while making the combustion more stable.

[0061] In some embodiments, the first swirler 51 and the second swirler 52 are radial swirlers, the third swirler 53 is an axial swirler, and the fourth swirler 54 is a radial swirler. This arrangement can improve the combustion effect of lean premixed preevaporation combustion.

[0062] As described above, the present application further discloses a gas turbine engine, which includes a combustion chamber described in any of the above-mentioned embodiments.

[0063] As introduced above, the present application also discloses a combustion organization method, wherein a partition is arranged between the cylinder wall of the flame tube and the combustion chamber casing, and the partition is distributed along the circumference of the flame tube. When thermal-acoustic coupling oscillation occurs during combustion in the combustion chamber, the waveform of the sound wave between the cylinder wall and the combustion chamber casing is changed by the partition, so that the sound wave between the cylinder wall and the combustion chamber casing is converted from a traveling wave that is approximately in phase with the sound wave in the flame tube to a standing wave or a slowly rotating standing wave; wherein, along the radial direction of the flame tube, the partition is arranged so that one end of the partition is in contact with the combustion chamber casing, and the other end has a gap with the cylinder wall, and the gap is 0.2mm to 2mm, so that the partition and the cylinder wall remain non-contact during the combustion process.

[0064] In summary, the beneficial effects of the combustion chamber, gas turbine engine and combustion organization method introduced in the above embodiments include but are not limited to: by setting a radial gap of 0.2mm to 2mm between the partition and the wall of the flame tube, the expansion of the wall of the flame tube during the operation of the combustion chamber, which causes it to contact with the partition and block at least part of the flow area of ​​the cooling hole, thereby avoiding burning of the flame tube, and the radial gap of 0.2mm to 2mm also ensures that the oscillation combustion suppression effect of the partition itself is not affected, thereby achieving the risk of burning of the flame tube wall while retaining the effect of suppressing oscillation combustion by setting the partition.

[0065] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A combustion chamber, characterized in that: include: A combustion chamber casing, comprising an outer combustion chamber casing and an inner combustion chamber casing; A flame tube is disposed between the outer casing of the combustion chamber and the inner casing of the combustion chamber, and comprises a tube wall, wherein the tube wall forms an inner cavity for fuel combustion; The cylinder wall is provided with a plurality of cooling holes communicating with the inner cavity and the outer side of the flame tube, the cooling holes are used to pass cooling gas into the inner cavity to cool the cylinder wall when the fuel is burning, and at least one partition is provided between the cylinder wall and the combustion chamber casing; Among them, along the radial direction of the flame tube, one end of the partition is in contact with the combustion chamber casing, and the other end has a gap with the tube wall, and the gap is 0.2mm to 2mm.

2. The combustion chamber according to claim 1, characterized in that The partition is provided with at least one through hole, and the through hole can communicate with adjacent spaces separated by the partition.

3. The combustion chamber according to claim 2, characterized in that The shape of the through hole includes a circular hole, a rectangular hole, a diamond hole, a polygonal hole, or an irregular shape.

4. The combustion chamber according to claim 1, characterized in that The partition plate extends along an extending direction of an axis of the flame tube.

5. The combustion chamber according to claim 1, characterized in that A folding ear with a connecting hole is arranged on the side of the partition plate in contact with the casing.

6. The combustion chamber according to claim 1, characterized in that The folded ears of the partition are fitted with the inner wall of the casing and are fixed to the casing through a threaded connection structure.

7. The combustion chamber according to claim 1, characterized in that The combustion chamber of the aircraft engine is an annular combustion chamber, and the cylinder wall includes an outer cylinder wall that is coaxial with the combustion chamber outer casing and the combustion chamber inner casing and is closer to the combustion chamber outer casing relative to the combustion chamber inner casing, and an inner cylinder wall that is coaxial with the outer cylinder wall and is closer to the combustion chamber inner casing relative to the combustion chamber outer casing, a plurality of cooling holes are provided on the outer cylinder wall and the inner cylinder wall, and at least one partition is provided between the outer cylinder wall and the combustion chamber outer casing and / or between the inner cylinder wall and the combustion chamber inner casing.

8. The combustion chamber according to claim 1, characterized in that A plurality of partitions are provided between the outer cylinder wall and the outer casing of the combustion chamber, and the plurality of partitions are evenly or unevenly arranged along the circumference of the flame cylinder; and / or a plurality of partitions are provided between the inner cylinder wall and the outer casing of the combustion chamber, and the plurality of partitions are evenly or unevenly arranged along the circumference of the flame cylinder.

9. The combustion chamber according to claim 1, characterized in that Also includes: A front diffuser is arranged upstream of the flame tube along the air intake direction, and is used to expand the pressure and reduce the speed of the gas flowing into the flame tube; A plurality of combustion assemblies are arranged at the flame tube inlet along the circumference of the flame tube, and the combustion assemblies include a pre-combustion stage fuel nozzle nozzle located in the middle, a main combustion stage fuel nozzle nozzle surrounding the central fuel nozzle nozzle, a first swirler and a second swirler located radially inside the main combustion stage fuel nozzle nozzle and arranged around the pre-combustion stage fuel nozzle nozzle, a third swirler located between the main combustion stage fuel nozzle nozzle and the second swirler, and a fourth swirler surrounding the main combustion stage fuel nozzle nozzle.

10. The combustion chamber according to claim 1, characterized in that The first swirler and the second swirler are radial swirlers, the third swirler is an axial swirler, and the fourth swirler is a radial swirler.

11. A gas turbine engine, characterized in that: Comprising a combustion chamber as described in any one of claims 1-10.

12. A method for organizing combustion, characterized in that: include: A partition is arranged between the cylinder wall of the flame tube and the combustion chamber casing, and the partition is distributed along the circumference of the flame tube. When thermal-acoustic coupling oscillation occurs during combustion in the combustion chamber, the waveform of the sound wave between the cylinder wall and the combustion chamber casing is changed by the partition, so that the sound wave between the cylinder wall and the combustion chamber casing is converted from a traveling wave that is approximately in phase with the sound wave in the flame tube to a standing wave or a slowly rotating standing wave; wherein, along the radial direction of the flame tube, the partition is arranged so that one end of the partition is in contact with the combustion chamber casing, and the other end has a gap with the cylinder wall, and the gap is 0.2mm to 2mm, so that the partition and the cylinder wall remain non-contact during the combustion process.

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