A high temperature rise combustion chamber for a high speed turbine engine

Abstract

The application discloses a high-temperature-rise combustion chamber for a high-speed turbine engine, belonging to the technical field of small turbine engines for high-speed unmanned aerial vehicles.The high-temperature-rise combustion chamber comprises a casing, wherein a sudden expansion diffuser is arranged on the casing, the sudden expansion diffuser is in communication with the inside of the casing and the outside of the casing, a flame tube assembly is further arranged in the casing, one end of the flame tube assembly is directed to the sudden expansion diffuser, and the other end of the flame tube assembly extends to the outside of the casing; a fuel atomization device capable of grading fuel supply is arranged on the flame tube assembly, the fuel atomization device is located between the flame tube assembly and the sudden expansion diffuser and is inserted into the flame tube assembly. The application improves the fuel atomization form by grading fuel supply, thereby improving the combustion stability under low working conditions, reducing the lean blowout fuel gas ratio, realizing high-efficiency combustion under high working conditions, improving the temperature distribution quality at the outlet of the combustion chamber, improving the fuel regulation range and guaranteeing the fuel atomization quality under the condition of high fuel gas ratio.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of small turbojet engine for high-speed unmanned aerial vehicle, in particular to a high-temperature-rise combustion chamber for high-speed turbojet engine. BACKGROUND

[0002] Fighter aircraft is developing towards super maneuverability, supersonic cruise and high stealth, which puts forward higher design requirements for aero-engine, especially the requirements of increasing engine thrust-to-weight ratio and maintaining supersonic cruise. From the analysis of engine thermodynamic cycle parameters, compared with increasing the pressure ratio of the compressor, increasing the temperature before the turbine is the most effective measure to improve the thrust-to-weight ratio, which means that the temperature rise of the combustion chamber needs to be continuously improved.

[0003] At present, the turbine inlet temperature of the engine of an advanced large fighter aircraft has reached 2000K, the temperature rise of the combustion chamber has been increased to 1350K, and the oil-gas ratio is as high as 0.05 or even higher. This means that under the same air flow conditions, the fuel device needs to adjust a wider range of fuel flow, and under the limitation of oil pump oil supply pressure, more fuel needs to be fully atomized and uniformly distributed; more air needs to participate in combustion, and less air needs to be used for cooling and mixing in the air entering the flame tube of the combustion chamber, and the service life and outlet temperature distribution quality of the combustion chamber need to be met. The turbine inlet temperature of the small missile turbojet engine F107 has reached 1500K, and the turbine inlet temperature of the small turbo-shaft and turbo-prop engine has reached 1600K, and is developing towards higher temperature.

[0004] The high-temperature-rise combustion chamber for small high-speed turbojet engine has the problems of small radial size, low oil supply pressure and poor outlet temperature quality, and the traditional centrifugal nozzle combined with double-stage swirler or double-stage swirler air atomizing nozzle mode is difficult to meet the requirements of wide range fuel adjustment and atomization quality under high oil-gas ratio conditions. The combination scheme of centrifugal nozzle combined with double-stage swirler is difficult to meet the requirements of outlet temperature distribution quality of high-temperature-rise combustion chamber under high working condition, and the double-swirl air atomizing nozzle scheme is prone to lean blowout or unstable combustion under low engine working condition. SUMMARY

[0005] The present application aims to overcome the deficiencies of the prior art that the high-temperature-rise combustion chamber for small high-speed turbojet engine has the problems of small radial size, low oil supply pressure and poor outlet temperature quality, which makes it difficult for small turbojet engine to achieve wide range fuel adjustment and meet the requirements of fuel atomization quality under high oil-gas ratio conditions, and provides a high-temperature-rise combustion chamber for high-speed turbojet engine, which improves the fuel atomization form by means of staged oil supply, thereby improving the combustion stability under low working condition and reducing the lean blowout oil-gas ratio, and at the same time realizing high-efficiency combustion under high working condition and improving the outlet temperature distribution quality of the combustion chamber, so as to improve the fuel adjustment range and guarantee the fuel atomization quality under high oil-gas ratio conditions.

[0006] The present application is achieved mainly by the following technical solutions.

[0007] A high-temperature-rise combustion chamber for high-speed turbine engine, comprising a casing, wherein a sudden expansion diffuser is arranged on the casing, the sudden expansion diffuser is communicated with the inside of the casing and the outside of the casing, and a flame tube assembly is further arranged in the casing, one end of the flame tube assembly is directed to the sudden expansion diffuser, and the other end of the flame tube assembly extends to the outside of the casing.

[0008] A fuel atomizing device capable of grading fuel supply is arranged on the flame tube assembly, the fuel atomizing device is located between the flame tube assembly and the sudden expansion diffuser and is inserted into the flame tube assembly.

[0009] Further, the flame tube assembly comprises a flame tube outer ring and a flame tube inner ring, and the flame tube outer ring and the flame tube inner ring are coaxially arranged.

[0010] Further, a flame tube front wall is arranged, and the end face of the flame tube outer ring and the end face of the flame tube inner ring are fixed with the flame tube front wall.

[0011] Further, a plurality of oval flange holes and a plurality of circular flange holes are arranged on the flame tube outer ring, and the oval flange holes and the circular flange holes are staggered.

[0012] Further, a double-stage cyclone is arranged on the fuel atomizing device, the fuel atomizing device comprises a first fuel channel, a second fuel channel and a third fuel channel, the first fuel channel, the second fuel channel and the third fuel channel are coaxially arranged, the second fuel channel is sleeved outside the first fuel channel, and the third fuel channel is sleeved outside the second fuel channel.

[0013] The first fuel channel, the second fuel channel, the third fuel channel and the double-stage cyclone are coaxially arranged.

[0014] The end of the first fuel channel, the end of the second fuel channel and the end of the third fuel channel are communicated with the double-stage cyclone.

[0015] Further, the double-stage cyclone comprises a primary cyclone and a secondary cyclone, the primary cyclone and the secondary cyclone are coaxially arranged, and the secondary cyclone is sleeved outside the primary cyclone.

[0016] Further, the first fuel channel comprises a centrifugal nozzle, the end of the centrifugal nozzle is communicated with the primary cyclone, and the gas in the primary cyclone is mixed with the fuel sprayed by the centrifugal nozzle and then enters the flame tube assembly.

[0017] Further, a gap exists between the primary cyclone and the secondary cyclone, the second fuel channel is located in the gap, the gap forms an annular cavity, and the annular cavity is sleeved outside the first fuel channel.

[0018] Further, a plurality of fuel flow uniformizing pieces are arranged in the second fuel channel, and the fuel flow uniformizing pieces are uniformly distributed in the circumferential direction.

[0019] Further, the secondary cyclone comprises a cyclone outer wall, a cyclone vane is arranged in the secondary cyclone, a first cavity is arranged in the cyclone vane, a second cavity is arranged in the cyclone outer wall, the third fuel channel comprises the first cavity and the second cavity, and the first cavity and the second cavity are communicated.

[0020] An oil injection hole is arranged on the cyclone vane, and the oil injection hole is located in the third fuel channel.

[0021] Compared with the prior art, the present application has the following beneficial effects:

[0022] In the present application, the fuel atomization device capable of staged fuel supply is used to realize the staged fuel supply in the flame tube assembly, so that the wide range fuel regulation is realized, and the atomization quality requirement under the condition of high oil-gas ratio is achieved. The sudden expansion diffuser in the embodiment is used to form an air vortex, the casing is used to accommodate the flame tube assembly, the flame tube assembly is used to accommodate fuel combustion, and the fuel atomization device is used to atomize fuel and uniformly diffuse into the flame tube assembly. The staged combustion form can effectively match the air flow and the fuel spray amount, so that uniform mixing is formed, and on the basis of adjusting the combustion condition, each combustion condition can achieve the purpose of sufficient combustion.

[0023] On this basis, the double-stage cyclone can mix air and fuel by the way of cyclone, and the atomized fuel can assist the fuel to diffuse uniformly, in the embodiment, the first fuel channel, the second fuel channel and the third fuel channel are arranged, wherein, the first fuel channel is arranged at the center position, and the fuel is atomized and diffused from the center after being sprayed, the second fuel channel is arranged outside the first fuel channel, and the annular fuel is formed outside the first fuel channel when the atomized fuel in the first fuel channel diffuses, so that the fuel supply is increased, and the fuel in the flame tube assembly is more uniformly distributed, and more fuel can be fully combusted at the same time, so that the power of the combustion condition is increased on the basis of full combustion, and the third fuel channel is arranged outside the second fuel channel, so that the fuel distribution of the third fuel channel is outside the second fuel channel, and the fuel amount in the flame tube assembly is increased on the basis of uniform distribution, and the combustion condition with greater power can be obtained on the basis of full combustion. BRIEF DESCRIPTION OF DRAWINGS

[0024] The drawings described herein are used to provide further understanding of the embodiments of the present application, form a part of the present application, and do not constitute a limitation on the embodiments of the present application. In the drawings:

[0025] Fig. 1 is a structural schematic view of the present application;

[0026] Fig. 2 is a structural schematic view of the fuel atomization device of the present application;

[0027] Fig. 3 is another perspective view of the fuel atomization device of the present application;

[0028] The signs represented in the drawings are: 1, sudden expansion diffuser; 2, casing; 3, fuel atomization device; 31, centrifugal nozzle; 32, second fuel channel; 321, fuel flow uniformizing piece; 322, oil film; 33, third fuel channel; 4, double-stage cyclone; 41, primary cyclone; 42, secondary cyclone; 421, cyclone outer wall; 422, cyclone blade; 4221, oil injection hole; 423, cyclone inner wall; 5, flame tube assembly; 51, flame tube outer ring; 511, elliptical flange hole; 512, circular flange hole; 52, flame tube front wall; 53, flame tube inner ring. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical scheme and advantages of the present application more clear and explicit, the present application is further described in detail below in combination with the embodiments and drawings, the illustrative embodiments of the present application and the description thereof are used to explain the present application, and do not constitute a limitation on the present application.

[0030] Example:

[0031] like Figs. 1-3 As shown, this embodiment relates to a high-temperature combustion chamber for a high-speed turbine engine, including a casing 2. The casing 2 is provided with a sudden diffuser 1, which connects the inside of the casing 2 and the outside of the casing 2. The casing 2 is also provided with a flame tube assembly 5, one end of which faces the sudden diffuser 1, and the other end of which extends to the outside of the casing 2.

[0032] The flame tube assembly 5 is equipped with a fuel atomizing device 3 capable of staged fuel supply. The fuel atomizing device 3 is located between the flame tube assembly 5 and the burst diffuser 1 and is inserted into the flame tube assembly 5.

[0033] Currently, when adjusting the fuel intake of the fuel atomizing device 3, the fuel volume is usually increased by directly increasing the fuel injection volume. However, this will cause the fuel to accumulate relatively and not have sufficient contact with air. Although the fuel is in an atomized state, there is still a risk of incomplete combustion, which will result in the flame tube assembly 5 not getting a suitable amount of fuel combustion, limiting the power of the engine turbine and failing to achieve the purpose of wide-range fuel regulation.

[0034] This embodiment utilizes a fuel atomizing device 3 capable of staged fuel supply to achieve phased fuel supply within the flame tube assembly 5, thereby realizing a wide range of fuel adjustment and meeting the atomization quality requirements under high fuel-air ratio conditions. In this embodiment, the diffuser 1 is used to form an airflow vortex, the casing 2 is used to house the flame tube assembly 5, the flame tube assembly 5 is used to contain fuel combustion, and the fuel atomizing device 3 is used to atomize the fuel and evenly diffuse it into the flame tube assembly 5. The staged combustion effectively matches the airflow and fuel spray volume, thereby forming a uniform mixture. This ensures that, based on adjustments to the combustion conditions, each combustion condition can achieve complete combustion.

[0035] The flame tube assembly 5 includes an outer ring 51 and an inner ring 53, which are coaxially arranged.

[0036] It also includes a flame tube front wall 52, and the end faces of the outer ring 51 and the inner ring 53 of the flame tube are both fixed to the flame tube front wall 52.

[0037] In this embodiment, the coaxiality of the outer ring 51 and the inner ring 53 of the flame tube forms a gap space, thereby forming a combustion chamber. The front wall 52 of the flame tube is used to mount the fuel atomizing device 3, so that fuel can be stably injected and atomized between the outer ring 51 and the inner ring 53 of the flame tube.

[0038] The flame tube outer ring 51 is provided with a plurality of oval flanging holes 511 and a plurality of circular flanging holes 512, and the oval flanging holes 511 and the circular flanging holes 512 are staggered.

[0039] The plurality of oval flanging holes 511 and the plurality of circular flanging holes 512 provided on the flame tube outer ring 51 can ensure the jet depth of the mixed air through the staggered layout, and can also ensure the jet depth of the mixed air when the mixed air amount is reduced, thereby improving the distribution quality of the combustion chamber outlet temperature.

[0040] The fuel atomization device 3 is provided with a double-stage swirler 4, and the fuel atomization device 3 includes a first fuel channel, a second fuel channel 32 and a third fuel channel 33, wherein the first fuel channel, the second fuel channel 32 and the third fuel channel 33 are coaxially arranged, the second fuel channel 32 is sleeved outside the first fuel channel, and the third fuel channel 33 is sleeved outside the second fuel channel 32.

[0041] The first fuel channel, the second fuel channel 32, the third fuel channel 33 and the double-stage swirler 4 are coaxially arranged.

[0042] The end of the first fuel channel, the end of the second fuel channel 32 and the end of the third fuel channel 33 are all in communication with the double-stage swirler 4.

[0043] The double-stage swirler 4 includes a primary swirler 41 and a secondary swirler 42, and the primary swirler 41 and the secondary swirler 42 are coaxially arranged, and the secondary swirler 42 is sleeved outside the primary swirler 41.

[0044] The double-stage cyclone 4 can mix air and fuel by cyclone, and assist the fuel to uniformly diffuse on the basis of atomized fuel. In the embodiment, a first fuel passage, a second fuel passage 32 and a third fuel passage 33 are arranged. The first fuel passage is arranged at the center position, and the fuel sprayed from the first fuel passage is atomized and diffused from the center, and is mixed by the first-stage cyclone 41 at the end of the first fuel passage. After mixing, the oil-gas mixture is introduced into the flame tube assembly 5 for combustion. The second fuel passage 32 is arranged outside the first fuel passage. When the atomized fuel in the first fuel passage diffuses, annular fuel spray is formed outside the oil-gas mixture formed by the first fuel passage and the first-stage cyclone 41. The second fuel passage 32 is mixed by the double-stage cyclone 4 at the end of the second fuel passage 32, and is introduced into the flame tube assembly 5, thereby increasing the fuel supply. On the basis of increasing the fuel supply, the fuel sprayed from the first fuel passage is not collided with, thereby avoiding mutual influence, so that the fuel distribution in the flame tube assembly 5 is more uniform, and more fuel can be fully combusted at the same time, thereby increasing the power of the combustion condition on the basis of full combustion. The third fuel passage 33 is arranged outside the second fuel passage 32, so that the fuel sprayed from the third fuel passage 33 is mixed by the second-stage cyclone 42, and is introduced into the flame tube assembly 5 and is distributed outside the fuel sprayed from the second fuel passage 32. The fuel amount in the flame tube assembly 5 is increased on the basis of uniform distribution, and a larger power combustion condition can be obtained on the basis of full combustion.

[0045] In the embodiment, the first-stage cyclone 41 and the second-stage cyclone 42 introduce the air in the form of cyclone into the flame tube assembly 5, thereby assisting the fuel to be atomized and diffused, and achieving more uniform and rapid atomization and diffusion of the fuel.

[0046] The first fuel passage comprises a centrifugal nozzle 31, the end of the centrifugal nozzle 31 is communicated with the first-stage cyclone 41, and the gas in the first-stage cyclone 41 mixes the fuel sprayed from the centrifugal nozzle 31 and then is introduced into the flame tube assembly 5.

[0047] In the embodiment, the centrifugal nozzle 31 is used to spray fuel, the first-stage cyclone 41 mixes the fuel and air by cyclone, and disperses the fuel in the process of cyclone, so that the atomization form is more sufficient, and the fuel can be fully combusted after ignition when being finally introduced into the flame tube assembly 5.

[0048] There is a gap between the first-stage cyclone 41 and the second-stage cyclone 42, the second fuel passage 32 is located in the gap, the gap forms an annular cavity, and the annular cavity is arranged outside the first fuel passage.

[0049] In this embodiment, the second fuel channel 32 forms an annular cavity by utilizing the gap between the first-stage cyclone 41 and the second-stage cyclone 42, without having its own separate structure. This effectively utilizes the existing structure to form the fuel channel, saving the overall space and weight of this embodiment, which is more conducive to the propulsion of the aircraft.

[0050] The second fuel passage 32 is provided with a plurality of fuel flow equalization plates 321, which are evenly distributed circumferentially.

[0051] The second fuel passage 32 is equipped with 15 to 25 fuel flow equalization plates 321 to achieve uniform circumferential distribution of fuel. A uniform oil film 322 is formed at the end of the swirler. Under the aerodynamic action of the two-stage swirler 4, good atomization is achieved. The fuel concentration at the head of the combustion chamber is uniformly distributed circumferentially, achieving efficient combustion and improving the temperature distribution at the outlet of the combustion chamber.

[0052] The secondary cyclone separator 42 includes a cyclone separator outer wall 421, and cyclone separator blades 422 are provided inside the secondary cyclone separator 42. The cyclone separator blades 422 are provided with a first cavity, and the cyclone separator outer wall 421 is provided with a second cavity. The third fuel passage 33 includes the first cavity and the second cavity, and the first cavity and the second cavity are connected.

[0053] The cyclone blade 422 is provided with an injection hole 4221, which is located in the third fuel passage 33.

[0054] In this embodiment, the second cavity within the outer wall of the secondary cyclone separator and the first cavity within the cyclone blades form a third fuel channel. Under the combined action of the inner wall 423 of the cyclone separator, the third fuel channel can drive the fuel injected from the injection hole and disperse it using shear force to form an atomized fuel, which is then injected into the flame tube assembly outside the second fuel channel. This increases the fuel supply and mixes with air to achieve complete combustion. In this embodiment, the second cavity is located between the outer wall and the inner wall of the cyclone separator, using both walls as the cavity body.

[0055] In this embodiment, fuel is injected through a centrifugal nozzle in the first fuel channel, through a pre-film air atomizing nozzle in the second fuel channel, and through a fuel jet nozzle in the third fuel channel. The centrifugal nozzle, the pre-film air atomizing nozzle, and the fuel jet nozzle can inject fuel simultaneously or at intervals to adapt to more different fuel combustion conditions. The design point condition in this embodiment is the state in which the centrifugal nozzle, the pre-film air atomizing nozzle, and the fuel jet nozzle are working simultaneously.

[0056] In the specific application of the embodiment, the core of the embodiment is mainly in the fuel atomizing device. The fuel atomizing device 3 is composed of three oil passage channels. The first fuel passage channel is sprayed into the inside of the flame tube assembly 5 by the centrifugal nozzle 31 with small flow and low pressure drop. The fuel is atomized by the oil supply pressure and further atomized by the air power of the primary swirler 41, which greatly improves the combustion stability under low working conditions, reduces the lean blowout fuel gas ratio, and widens the working boundary of the high temperature rise combustion chamber.

[0057] The second fuel passage channel 32 is composed of the coaxial layout of the inner wall 423 of the primary swirler 41 and the secondary swirler 42 to form an annular channel, and the fuel forms an oil film 322 inside.

[0058] The second fuel passage channel 32 is internally arranged with 15-25 fuel flow uniformizing pieces 321 to realize the uniform distribution of the fuel in the circumferential direction, form a uniform oil film 322 at the end of the double-stage swirler 4, realize good atomization under the air power of the double-stage swirler 4, realize the uniform distribution of the fuel concentration in the circumferential direction at the head of the combustion chamber, and realize efficient combustion and improve the temperature distribution at the outlet of the combustion chamber.

[0059] Each swirler blade 422 is arranged with 1-2 rows of oil injection holes 4221 with a hole diameter of 0.3mm-0.6mm. The fuel sprayed through the oil injection holes 4221 is sprayed into the third fuel passage channel 33 in a nearly vertical flow direction, and the fuel is atomized under the action of the air shear force in the third fuel passage channel 33. The well-atomized fuel flows into the flame tube assembly 5 with the air in the secondary swirler 42, improves the radial fuel concentration distribution at the head of the flame tube assembly 5, realizes efficient combustion, and improves the temperature distribution quality at the outlet of the combustion chamber.

[0060] The mixing holes of the outer ring 51 of the flame tube are innovatively arranged in an interlaced manner of the oval flange hole 511 with a flange and the circular flange hole 512, which can maintain the jet depth of the mixing air under the condition of reduced mixing air quantity, and greatly improves the temperature distribution quality at the outlet of the combustion chamber.

[0061] The number of the oval flange hole 511 and the circular flange hole 512 is the same, and the number is 10-16. The flange depth is controlled to be 2.5mm-4mm.

[0062] When the small high-speed turbine engine is ignited and started to the slow vehicle working condition or the low working condition in the air, the oil supply system of the engine is only the centrifugal nozzle 31 oil passage of the high temperature rise combustion chamber. Due to the small fuel flow of the first fuel passage channel and the auxiliary fuel atomization by the air power of the primary swirler 41, the fuel of the oil passage can be well atomized in the working flow range. Under the ignition of the ignition device, stable combustion can be realized, the combustion chamber is not easy to be extinguished under low working conditions, the lean blowout boundary is wide, and the centrifugal nozzle 31 works under any working condition of the engine.

[0063] The small high-speed turbine engine from the slow vehicle condition to the cruise condition medium condition, the engine oil supply system is the second fuel passage 32 oil supply, that is, the pre-film air atomization nozzle works, the fuel is atomized well under the joint action of the double-stage cyclone 4, and the atomized fuel is distributed in the coaxial outer side area of the centrifugal nozzle 31 fuel, the fuel is uniformly distributed, the high-temperature rise combustion chamber can be efficiently combusted, and the combustion chamber outlet temperature distribution quality is good.

[0064] The small high-speed turbine engine from the cruise condition to the design point condition high condition, the engine oil supply system is the third fuel passage oil supply, that is, the fuel jet nozzle starts to work, the fuel jet is deformed rapidly, the oil film 322 is broken and atomized under the action of the lateral force of the secondary cyclone 42 air, and is mixed with the cyclone air to enter the flame tube assembly 5 for combustion. This part of the atomized fuel is distributed in the coaxial outer side area of the pre-film air atomization nozzle fuel, the fuel is uniformly distributed, the high-temperature rise combustion chamber can be efficiently combusted under high fuel flow, and the combustion chamber outlet temperature distribution quality is good.

[0065] As shown in the figure, Fig. 1 The air flow compressed by the sudden expansion diffuser 1 flows to the head of the flame tube assembly 5, flows along the geometric shape of the head of the flame tube assembly 5, is divided into three streams, flows into the combustion chamber through the mixing hole after flowing into the flame tube inner ring 53 and the flame tube outer ring 51, and the remaining air flows into the combustion chamber through the head double-stage cyclone 4. The small high-speed turbine engine is ignited and started to the slow vehicle condition or the low condition in the air, the engine oil supply system is only the centrifugal nozzle 31 oil circuit of the high-temperature rise combustion chamber, the fuel flow is small, the aerodynamic force of the primary cyclone assists the fuel atomization, so that the fuel of the oil circuit can be atomized well in the working flow range, stable combustion can be realized under the ignition of the ignition device, the value flame function is realized, the combustion chamber is not easy to be extinguished in the low condition, and the lean-out extinguishing boundary is wide. The centrifugal nozzle 31 works in any condition of the engine.

[0066] As shown in the figure, Fig. 2 The embodiment adopts a staged oil supply mode, when the small high-speed turbine engine is from the slow vehicle condition to the cruise condition medium condition, the engine oil supply system is the second fuel passage 32 oil supply, that is, the pre-film air atomization nozzle works, the fuel is atomized well under the joint action of the double-stage cyclone 4, and the atomized fuel is distributed in the coaxial outer side area of the centrifugal nozzle 31 fuel, the fuel is uniformly distributed, the high-temperature rise combustion chamber can be efficiently combusted, and the combustion chamber outlet temperature distribution quality is good.

[0067] As shown in the figure, Fig. 3As shown, when the small high-speed turbine engine is in higher operating conditions from the cruise operating condition to the design point operating condition, the engine fuel supply system supplies fuel to the third fuel passage 33, i.e., the fuel jet nozzle starts to work, and this part of fuel realizes rapid deformation of the fuel jet, breaking and atomization of the oil film 322 under the action of the transverse force of the air of the secondary swirler 42, and after mixing with the swirled air, enters the flame tube assembly 5 for combustion. This part of atomized fuel is distributed in the coaxial outer region of the pre-film air atomizing nozzle fuel, and the fuel is uniformly distributed, which can realize efficient combustion of the high-temperature-rise combustion chamber under high fuel flow, and has good combustion chamber outlet temperature distribution quality. At the same time, the elliptical flange hole 511 and the circular flange hole 512 are arranged in an interleaved manner, which can maintain the jet depth of the mixed air under the condition of reduced mixed air volume, and greatly improve the combustion chamber outlet temperature distribution quality. Because there is a cavity structure inside the double-stage swirler 4, the convection heat transfer of the low-temperature fuel has a certain cooling effect on the swirler.

[0068] The high-temperature-rise combustion chamber of such a small turbine jet engine can realize wide-range fuel adjustment, good fuel atomization quality, uniform fuel concentration distribution, high temperature rise, good combustion chamber outlet temperature distribution quality, higher reliability, lighter weight, stronger universality, and is more suitable for small turbine engines with wide air space and wide speed range.

[0069] The above specific embodiments further illustrate the purpose, technical solutions and beneficial effects of the present application. It should be understood that the above description is only a specific embodiment of the present application and is not intended to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims

1. A high-temperature-rise combustion chamber for a high-speed turbine engine, comprising a casing (2) provided with a divergent diffuser (1) communicating between the interior of the casing (2) and the exterior of the casing (2), characterized in that, The combustor (2) is further provided with a flame tube assembly (5), one end of the flame tube assembly (5) is towards the sudden expansion diffuser (1), and the other end extends out of the combustor (2); The flame tube assembly (5) is provided with a fuel atomizing device (3) capable of grading fuel supply, the fuel atomizing device (3) is located between the flame tube assembly (5) and the sudden expansion diffuser (1) and is inserted into the flame tube assembly (5); The flame tube assembly (5) comprises a flame tube outer ring (51) and a flame tube inner ring (53), and the flame tube outer ring (51) and the flame tube inner ring (53) are coaxially arranged; Further comprising a flame tube front wall (52), the end face of the flame tube outer ring (51) and the end face of the flame tube inner ring (53) are fixed with the flame tube front wall (52); The fuel atomizing device (3) is provided with a double-stage cyclone (4), the fuel atomizing device (3) comprises a first fuel channel, a second fuel channel (32) and a third fuel channel (33), the first fuel channel, the second fuel channel (32) and the third fuel channel (33) are coaxially arranged, the second fuel channel (32) is sleeved outside the first fuel channel, and the third fuel channel (33) is sleeved outside the second fuel channel (32); The first fuel channel, the second fuel channel (32), the third fuel channel (33) and the double-stage cyclone (4) are coaxially arranged; The end of the first fuel channel, the end of the second fuel channel (32) and the end of the third fuel channel (33) are in communication with the double-stage cyclone (4); The double-stage cyclone (4) comprises a primary cyclone (41) and a secondary cyclone (42), the primary cyclone (41) and the secondary cyclone (42) are coaxially arranged, and the secondary cyclone (42) is sleeved outside the primary cyclone (41); The secondary cyclone (42) comprises a cyclone outer wall (421), a plurality of cyclone blades (422) are arranged in the secondary cyclone (42), the cyclone blades (422) are provided with a first cavity, the cyclone outer wall (421) is provided with a second cavity, the third fuel channel (33) comprises the first cavity and the second cavity, and the first cavity and the second cavity are in communication; The cyclone blades (422) are provided with oil injection holes (4221), and the oil injection holes (4221) are located in the third fuel channel (33); Each of the cyclone blades (422) is arranged with 1-2 rows of the oil injection holes, and the diameter of the oil injection holes is 0.3-0.6 mm.

2. A high temperature rise combustor for a high speed turbine engine as recited in claim 1, characterized by The flame tube outer ring (51) is provided with a plurality of oval flange holes (511) and a plurality of circular flange holes (512), and the oval flange holes (511) and the circular flange holes (512) are staggered.

3. A high temperature rise combustor for a high speed turbine engine as recited in claim 1, characterized by The first fuel channel comprises a centrifugal nozzle (31), the tip of the centrifugal nozzle (31) communicates with the primary swirler (41), and the gas in the primary swirler (41) mixes with the fuel sprayed by the centrifugal nozzle (31) and then enters the flame tube assembly (5).

4. A high temperature rise combustor for a high speed turbine engine as recited in claim 1, characterized by There is a gap between the primary swirler (41) and the secondary swirler (42), and the second fuel channel (32) is located in the gap, the gap forms an annular cavity, and the annular cavity is sleeved outside the first fuel channel; The single-side gap between the inner wall tip of the primary swirler (41) and the secondary swirler (42) is 0.3mm-0.8mm.

5. A high temperature rise combustor for a high speed turbine engine as recited in claim 4, characterized by A plurality of fuel flow uniformizing pieces (321) are arranged in the second fuel channel (32), and the fuel flow uniformizing pieces (321) are uniformly distributed in the circumferential direction.

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