Multifunctional compact jet flame stabilizer integrating fuel oil flow path and ignition electric nozzle and application of multifunctional compact jet flame stabilizer

Abstract

The invention relates to the technical field of aero-engines, and discloses a multifunctional compact jet flame stabilizer integrating a fuel oil flow path and an ignition electric nozzle and application of the multifunctional compact jet flame stabilizer. The multifunctional compact jet flame stabilizer comprises a stabilizer body of a hollow structure, and the ignition electric nozzle is arranged in the hollow structure; an oil spraying hole is formed in the outer wall face of the stabilizer body and communicates with a combustion chamber oil supply pipeline. The ignition electric nozzle is inserted and integrated in the stabilizer body, the integrated stabilizer can be machined in an additive manufacturing mode, the effects of enabling the structure to be more compact, reducing the number of connecting pieces and reducing the weight are achieved, and the distance from an oil injection point to the tail edge of the stabilizer is reduced so as to adapt to the higher inlet temperature and the lower incoming flow Mach number; and on the other hand, the oil injection hole and the ignition electric nozzle are integrated on the stabilizer body, so that the ignition electric nozzle is effectively cooled, and compared with a traditional cantilever structure of the ignition electric nozzle, the integrated structure can enable the ignition electric nozzle to meet the strength requirement with a smaller diameter.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and discloses a multifunctional compact jet flame stabilizer integrating a fuel flow path and an ignition nozzle, and its application. Background Technology

[0002] The increasing demands on thrust, range, and weight in aircraft have led to a gradual rise in the incoming air temperature of afterburners in aero engines, and consequently, a gradual increase in the weight requirements for afterburners. To address these issues, advanced afterburners both domestically and internationally generally adopt an integrated structural design, combining the flame stabilizer and the rectifier support plate together. The fuel lines are located within the stabilizer, while the fuel nozzles are positioned on the side of the support plate. Compared to traditional afterburner designs, this structure is more compact, effectively shortening the combustion chamber length.

[0003] However, in the current integrated design, the fuel injector, ignition nozzle, and flame stabilizer are all independent components, which are then assembled into a functional device. This structural design has the following problems: 1) The ignition nozzle has a long cantilever structure with a long extension distance and poor stress distribution, making it susceptible to low-frequency vibration excitation and structural strength failure. 2) There are many parts and the thermal deformation is inconsistent. The parts installed on the outer casing and the inner casing have large differences in thermal deformation when they are cold and hot. The nozzles are affected by inconsistent thermal deformation and there is a risk of being blocked. 3) The integrated components are large in size and the distance from the nozzle on the spray bar to the flame stabilizer is long. After the fuel is sprayed from the nozzle, it is easy for it to spontaneously combust and burn the flame stabilizer before it reaches the return zone of the stabilizer. Summary of the Invention

[0004] The purpose of this invention is to provide a multifunctional compact jet flame stabilizer that integrates a fuel flow path and an ignition nozzle, and its application. This stabilizer can make the structure more compact, reduce the number of connecting parts, and reduce weight. It also reduces the distance from the fuel injection point to the stabilizer's trailing edge to accommodate higher inlet temperatures and lower incoming flow Mach numbers, and effectively cools the ignition nozzle.

[0005] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows: A multifunctional compact jet flame stabilizer integrating a fuel flow path and an ignition nozzle includes: a stabilizer body, one end of which is fixed to an outer casing, and the other end extending to a position near the outer wall of the central cone; the stabilizer body is a hollow structure, and an ignition nozzle is disposed within the hollow structure, with the tip of the ignition nozzle protruding from the inner cavity of the stabilizer body to a position near the outer wall of the central cone; an ignition fuel passage is also provided within the hollow structure for injecting fuel into the ignition nozzle; The outer wall of the stabilizer body is provided with an oil injection hole, which is connected to the fuel supply line of the combustion chamber.

[0006] Furthermore, the oil supply pipeline includes a main oil line and a secondary oil line, and the oil supply pipelines of both the main oil line and the secondary oil line are disposed within the hollow structure.

[0007] Furthermore, the stabilizer body has an integrally coaxially arranged first annular cavity and second annular cavity to form a fuel injection rod, with the first annular cavity being the main fuel passage and the second annular cavity being the auxiliary fuel passage.

[0008] Furthermore, multiple support plates are provided between the outer wall of the fuel injection rod and the inner wall of the stabilizer body.

[0009] Furthermore, a cavity is provided at the center of the fuel injector rod, and the ignition nozzle is inserted into the cavity.

[0010] Furthermore, the cavity is provided with a plurality of boss structures that abut against the outer wall of the ignition nozzle, and the boss structures are circumferentially distributed on the outer periphery of the outer wall of the ignition nozzle.

[0011] Furthermore, the upstream position of the stabilizer body is also provided with a connector into which the turbine rear support plate can be inserted.

[0012] Furthermore, the cross-section of the ignition oil circuit is a square with rounded corners, located on the outside of the second annular cavity.

[0013] To achieve the above-mentioned technical effects, the present invention also provides an application of a multifunctional compact jet flame stabilizer in an afterburner, wherein the afterburner has the multifunctional compact jet flame stabilizer.

[0014] Compared with the prior art, the beneficial effects of this invention are: 1. This invention integrates the ignition nozzle into the stabilizer body, and the integrated stabilizer can be manufactured using additive manufacturing, which makes the structure more compact, reduces the number of connecting parts, and reduces weight. It also reduces the distance from the injection point to the stabilizer tail edge to adapt to higher inlet temperatures and lower incoming flow Mach numbers.

[0015] 2. The integration of the fuel injection hole and the ignition nozzle on the stabilizer body of the present invention also enables the ignition nozzle to be effectively cooled. Compared with the traditional cantilever structure of the ignition nozzle, the integrated structure allows the ignition nozzle to meet the strength requirements with a smaller diameter. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of an afterburner chamber including a multifunctional compact jet flame stabilizer in the embodiment; Figure 2This is a schematic diagram of the cross-sectional structure of the stabilizer body in the embodiment; Figure 3 This is a schematic diagram showing the connection relationship between the turbine rear support plate and the stabilizer body in the embodiment; The components include: 1. Turbine rear support plate; 2. Stabilizer body; 3. Ignition nozzle; 4. Fuel supply line; 5. Fuel injection hole; 6. Ignition fuel line; 7. Outer casing; 8. Inner casing; 9. Inner cone; 10. Cavity; 11. Inner flow channel; 12. Outer flow channel; 13. First annular cavity; 14. Second annular cavity; 15. Direct-injection nozzle; 16. Support plate; 17. Air flow channel; 18. Cooling hole. Detailed Implementation

[0017] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0018] Example 1 See Figures 1 to 3 A multifunctional compact jet flame stabilizer integrating a fuel flow path and an ignition nozzle 3 is disclosed, comprising: a stabilizer body 2, one end of which is fixed to an outer casing 7, and the other end extending to a position near the outer wall of the central cone; the stabilizer body 2 is a hollow structure, and an ignition nozzle 3 is disposed within the hollow structure, the end of which protrudes from the inner cavity of the stabilizer body 2 to a position near the outer wall of the central cone; an ignition fuel passage 6 is also disposed within the hollow structure for injecting fuel into the ignition nozzle 3; The outer wall of the stabilizer body 2 is provided with an oil injection hole 5, which is connected to the combustion chamber fuel supply line 4.

[0019] In this embodiment, the ignition nozzle 3 is integrated into the stabilizer body 2. The integrated stabilizer can be manufactured using additive manufacturing, which makes the structure more compact, reduces the number of connecting parts, and reduces weight. It also reduces the distance from the injection point to the stabilizer tail edge to accommodate higher inlet temperatures and lower incoming flow Mach numbers. On the other hand, the integration of the injection hole 5 and the ignition nozzle 3 into the stabilizer body 2 also allows the ignition nozzle 3 to be effectively cooled. Compared with the traditional cantilever structure of the ignition nozzle 3, this integrated structure allows the ignition nozzle 3 to meet strength requirements with a smaller diameter.

[0020] In this embodiment, the oil supply line 4 includes a main oil line and a secondary oil line, both of which are located within the hollow structure. For example, a first annular cavity 13 and a second annular cavity 14 can be integrally and coaxially arranged within the inner cavity of the stabilizer body 2 to form an injection rod, where the first annular cavity 13 is the main oil line and the second annular cavity 14 is the secondary oil line.

[0021] In this embodiment, a cavity 10 is provided at the center of the fuel injector rod, and the ignition nozzle 3 is inserted into the cavity 10. The side wall of the cavity 10 provides support for the rod of the ignition nozzle 3, and the oil circuit cools the ignition nozzle 3, further ensuring that the diameter of the ignition nozzle 3 can be smaller under the same ignition conditions.

[0022] In this embodiment, the upstream position of the stabilizer body 2 is also provided with an insertion part into which the turbine rear support plate 1 can be inserted, so that the turbine rear support plate 1 installed on the inner casing 8 and the stabilizer body 2 installed on the outer casing 7 form a floating overlap structure at the insertion position, which can effectively offset the difference in axial and radial deformation caused by the inconsistent thermal deformation of the two casings.

[0023] Example 2 An afterburner with a multifunctional compact jet flame stabilizer is provided. The multifunctional compact jet flame stabilizer is located in the diffuser stabilization section inside the integrated afterburner and is mainly composed of components such as turbine rear support plate 1, stabilizer body 2, ignition nozzle 3, main oil circuit, auxiliary oil circuit, and ignition oil circuit 6.

[0024] The turbine rear support plate 1 is circumferentially fixed between the inner cone 9 and the inner casing 8 of the afterburner's internal flow channel 11 via a pin-like connection. The turbine rear support plate 1 is connected to the inner casing 8 by welding. The stabilizer body 2 is connected to the outer casing 7 by bolts. The stabilizer body 2 and the turbine rear support plate 1 are connected by an interlocking joint, allowing for radial and axial floating to compensate for the axial deformation difference caused by the inconsistent thermal deformation of the two casings.

[0025] The stabilizer body 2 has a first annular cavity 13 and a second annular cavity 14 coaxially integrated within its inner cavity to form a fuel injector. The fuel injector contains three fuel lines: a main fuel line (first annular cavity 13), a secondary fuel line (second annular cavity 14), and an ignition fuel line 6. The main and secondary fuel lines have annular cross-sections and are coaxial with the ignition nozzle 3. The main fuel line is located outside the secondary fuel line, and the secondary fuel line is located outside the ignition nozzle 3 and inside the main fuel line. The ignition fuel line 6 has a square cross-section with rounded corners and is located outside the secondary fuel line. The upper end of the main fuel line is connected to the fuel supply line 4, and the fuel therein is independently sprayed out through the fuel injection holes 5 on the side of the stabilizer body 2. The upper end of the secondary fuel line is also connected to the fuel supply line 4, and the fuel therein is independently sprayed out through the fuel injection holes 5 on the side of the stabilizer body 2. The fuel in the ignition fuel line 6 is sprayed out through a direct-fire nozzle 15 on the lower surface of the stabilizer body 2.

[0026] Multiple support plates 16 are provided between the outer wall of the fuel injector and the inner wall of the stabilizer body 2, which can further improve the strength of the structure and reduce the weight. In addition, the multiple support plates 16, in a circumferentially distributed and axially discontinuous manner, divide the gap between the fuel injector and the inner cavity of the stabilizer body 2 into multiple interconnected air flow channels 17, and cooling holes 18 begin at the downstream end face of the stabilizer body 2; the portion of the upper end of the stabilizer body 2 located in the outer bypass channel 12 has an air inlet in the upstream direction of the air flow. Cooling air from the outer bypass channel 12 flows into the air flow channel 17 in the stabilizer body 2 through the air inlet and flows out through the cooling holes 18 to cool the stabilizer body 2.

[0027] A cavity 10 is provided at the center of the fuel injector rod, and the ignition nozzle 3 is located inside the cavity 10 of the fuel injector rod, which can make full use of the oil in the fuel line to cool the ignition nozzle 3. In addition, the ignition nozzle 3 hole in the stabilizer body 2 has a boss structure, which can support the ignition nozzle 3, eliminating the cantilever structure of the ignition nozzle 3, and further allowing the ignition nozzle 3 to be designed with a smaller diameter to meet the strength requirements.

[0028] In this embodiment, the fuel injector, ignition nozzle 3, and stabilizer body 2 can be integrated into a single component through additive manufacturing, resulting in a more compact structure.

[0029] The advantages of the afterburner in this embodiment are as follows: I. The multi-functional compact jet flame stabilizer is manufactured using additive manufacturing, integrating the fuel injector, ignition nozzle 3, and flame stabilizer into a single integrated design, effectively reducing the number of parts and components, lowering weight, and improving reliability. 2. The integrated design of the fuel injector, ignition nozzle 3, and flame stabilizer effectively cools the ignition nozzle 3, creating conditions for the design of the electrical components inside the ignition nozzle 3; the fuel injection of the nozzle is not affected by the obstruction caused by the inconsistent thermal deformation of the side wall of the support plate and the injector, ensuring smooth fuel injection; the support of the boss inside the fuel injector cavity for the ignition nozzle 3 overcomes the stress disadvantage of the traditional cantilever arrangement of the ignition nozzle 3, and the stress distribution is more reasonable under the same size conditions; 3. The concentric design of the fuel injector and the ignition nozzle 3, compared with the traditional design of multiple fuel injectors and the ignition nozzle 3 arranged in front and behind, allows the distance between the nozzle and the rear end of the flame stabilizer to be designed to be shorter, which can adapt to higher inlet temperatures without spontaneous combustion.

[0030] IV. The floating design between the turbine rear support plate 1 and the multi-functional compact jet flame stabilizer can offset the difference in axial and radial deformation caused by the inconsistent thermal deformation of the two-layer casing, and match the structural design of the upstream and downstream components of the engine's afterburner.

[0031] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A multifunctional compact jet flame stabilizer integrating a fuel flow path and an ignition nozzle, characterized in that, include: The stabilizer body has one end fixed to the outer casing and the other end extending to a position near the outer wall of the central cone; The stabilizer body has a hollow structure, and an ignition nozzle is installed inside the hollow structure. The end of the ignition nozzle extends from the inner cavity of the stabilizer body to a position near the outer wall of the central cone. An ignition oil circuit is also provided inside the hollow structure for spraying oil onto the ignition nozzle. The outer wall of the stabilizer body is provided with an oil injection hole, which is connected to the fuel supply line of the combustion chamber.

2. The multifunctional compact jet flame stabilizer according to claim 1, characterized in that, The oil supply pipeline includes a main oil line and a secondary oil line, and both the main oil line and the secondary oil line are installed inside the hollow structure.

3. The multifunctional compact jet flame stabilizer according to claim 2, characterized in that, The stabilizer body has a first annular cavity and a second annular cavity coaxially arranged to form a fuel injection rod. The first annular cavity is the main fuel passage, and the second annular cavity is the auxiliary fuel passage.

4. The multifunctional compact jet flame stabilizer according to claim 3, characterized in that, Multiple support plates are provided between the outer wall of the fuel injector rod and the inner wall of the stabilizer body.

5. The multifunctional compact jet flame stabilizer according to claim 3, characterized in that, A cavity is provided at the center of the fuel injector rod, and the ignition nozzle is inserted into the cavity.

6. The multifunctional compact jet flame stabilizer according to claim 5, characterized in that, The cavity is provided with a plurality of protrusion structures that abut against the outer wall of the ignition nozzle, and the protrusion structures are distributed circumferentially on the outer periphery of the outer wall of the ignition nozzle.

7. The multifunctional compact jet flame stabilizer according to claim 1, characterized in that, The stabilizer body is also provided with a connector at its upstream position for inserting the turbine rear support plate.

8. The multifunctional compact jet flame stabilizer according to claim 1, characterized in that, The ignition oil circuit has a square cross-section with rounded corners and is located on the outside of the second annular cavity.

9. An application of a multifunctional compact jet flame stabilizer in an afterburner, characterized in that, The afterburner has the multifunctional compact jet flame stabilizer as described in any one of claims 1-8.

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