Airflow control function-equipped strut stabilizer and afterburner

Abstract

The present application relates to the technical field of aircraft engine afterburner, and particularly relates to a strut stabilizer with aerodynamic jet regulation function and an afterburner. The strut stabilizer comprises a strut body and a boss integrally formed on the top of the strut body; a first gas collection cavity, a second gas collection cavity and a duty oil supply cavity are sequentially and spacedly arranged in the strut body from front to back; a duty oil injection rod is inserted in the duty oil supply cavity; a first air inlet hole, a second air inlet hole and a third air inlet hole are arranged on the boss and used for introducing the outer-cowl air into the first gas collection cavity, the second gas collection cavity and the duty oil supply cavity respectively; a first jet slot, a second jet slot and a third jet slot are sequentially and opened on the left and right side surfaces of the strut body from front to back; the first jet slot is in communication with the first gas collection cavity, the second jet slot is in communication with the second gas collection cavity, and the third jet slot is in communication with the duty oil supply cavity.

Description

Technical Field

[0001] This invention relates to the field of afterburner technology for aero-engines, and more particularly to a support plate stabilizer and afterburner with aerodynamic jet control function. Background Technology

[0002] As afterburner components develop towards wider speed range, lower flow resistance, lighter weight, and higher performance, short-distance, low-resistance afterburner combustion technology with close-range oil-gas coupling is gradually being widely adopted.

[0003] In the existing technology, there are already a number of related patent applications for afterburners.

[0004] For example, patent application CN109340820A discloses an integrated afterburner with support plates and a cooling structure. Support plates are arranged on both sides of the rectifier support plate flame stabilizer. There are double rows of oblique injection holes at the rear of the support plates. The injection holes spray fuel onto the support plate wall for abrasion and secondary atomization, thereby improving the combustion efficiency and combustion stability of the afterburner.

[0005] For example, patent application CN118391707A discloses an afterburner ignition device and an afterburner. By introducing external cold air into the ignition device, it not only effectively ensures the cooling effect of the ignition device and increases the oxygen content, but also improves structural reliability and the stability of the standby flame. Simultaneously, the influence of the flow field within the standby flame stabilizer on the mainstream flow field is reduced, minimizing disruption to the mainstream gas flow. By guiding the flame from the flame acceleration cone into the mainstream of the afterburner, the ignition energy is effectively increased and the flame penetration depth is enhanced.

[0006] For example, patent application CN114738795 discloses a support plate stabilizer with air mixing function and an integrated afterburner. The support plate stabilizer has two symmetrical open concave cavities in the middle. These open concave cavities have an air mixing function and can replace the mixer in the traditional afterburner. This simplifies the structure of the afterburner. Since the outer bypass airflow flows into the inner channel through the holes on the front wall of the open concave cavity and mixes with the inner airflow, the mixing distance between the inner and outer bypass airflows is shortened, the mixing effect of the inner and outer bypass airflows is enhanced, which is beneficial to the mixing of fuel and air-fuel mixture in the rear and improves the uniformity of fuel distribution.

[0007] However, due to the high inlet airflow velocity of the afterburner, the short residence time of injected fuel, and the close distance between the fuel injection point and the stabilizer, organizing combustion under actual operating conditions is quite difficult. The aforementioned existing technologies have not solved this problem. Summary of the Invention

[0008] The main objective of this invention is to propose a support plate stabilizer and an afterburner with aerodynamic jet control function, in order to solve the above-mentioned technical problems.

[0009] To achieve the above objectives, on the one hand, the present invention proposes a support plate stabilizer with aerodynamic jet control function, comprising a support plate body and a boss integrally formed on the top of the support plate body; inside the support plate body, a first air collecting chamber, a second air collecting chamber, and a duty oil supply chamber are arranged sequentially from front to back at intervals; a duty oil injection rod is inserted in the duty oil supply chamber; a first air inlet, a second air inlet, and a third air inlet are provided on the boss, for introducing external air into the first air collecting chamber, the second air collecting chamber, and the duty oil supply chamber, respectively; a first jet slit, a second jet slit, and a third jet slit are sequentially opened from front to back on the left and right sides of the support plate body; the first jet slit is connected to the first air collecting chamber, the second jet slit is connected to the second air collecting chamber, and the third jet slit is connected to the duty oil supply chamber.

[0010] Preferably, the third jet slit is a long strip-shaped slit, and the third jet slit is arranged along the length direction of the support plate body; there are multiple first jet slits, and the multiple first jet slits are evenly distributed at intervals along the length direction of the support plate body; there are multiple second jet slits, and the multiple second jet slits are evenly distributed at intervals along the length direction of the support plate body; the first jet slits and the second jet slits are alternately distributed along the length direction of the support plate body.

[0011] Preferably, a trapezoidal groove is provided at the tail end of the support plate body, and the trapezoidal groove is arranged along the length of the support plate body.

[0012] Preferably, the included angle between the two inclined surfaces of the trapezoidal groove is ω, and 80°≤ω≤90°.

[0013] Preferably, the inlet of the first air inlet is located on the arc surface at the front end of the boss; there are two second air inlets, which are arranged in a V-shape, and the inlets of the two second air inlets are respectively located on the left and right curved surfaces of the boss; there are two third air inlets, which are arranged in a V-shape, and the inlets of the two third air inlets are respectively located on the left and right curved surfaces of the boss; both the second and third air inlets are inclined towards the front end of the boss.

[0014] Preferably, the included angle between the two second air inlets is α, and the included angle between the two third air inlets is β; and 70°≤α≤75°, 70°≤β≤75°.

[0015] Preferably, the first jet slit and the second jet slit are both inclined toward the rear of the support plate body; the third jet slit is perpendicular to the left and right symmetrical plane A of the support plate stabilizer.

[0016] Preferably, the included angle between the first jet slits on the left and right sides of the support plate body is γ, and 135°≤γ≤145°.

[0017] Preferably, the included angle between the second jet slits on the left and right sides of the support plate body is δ, and 135°≤δ≤145°.

[0018] On the other hand, the present invention also provides an afterburner, comprising a combustion chamber casing, a mixer and a center cone arranged coaxially from the outside to the inside; the mixer and the center cone are connected by a plurality of spoke-shaped support plate stabilizers; the support plate stabilizers are the support plate stabilizers described above, and the bosses extend into the outer bypass duct formed between the combustion chamber casing and the mixer.

[0019] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows: (1) A first gas collecting chamber, a second gas collecting chamber, and a shift oil supply chamber are sequentially arranged from front to back within the support plate body of the support plate stabilizer. The gas in the first gas collecting chamber is ejected through the first jet slit to form a transverse jet I; the gas in the second gas collecting chamber is ejected through the second jet slit to form a transverse jet II; and the oil-gas mixture in the shift oil supply chamber is ejected from the third jet slit. Since the first jet slit is located in front of the second jet slit, the transverse jet I is located in front of the transverse jet II. Therefore, in order to avoid mutual interference between the mainstream flow and the transverse jet II, the transverse jet I is introduced in front of the transverse jet II to form an aerodynamic barrier. This allows the mainstream flow that is turbulent near the wall surface to be lifted to a certain height and then flow backward, reducing the impact on the interaction flow between the downstream transverse jet II and the shift oil-gas mixture. This allows the transverse jet II to further mix with the downstream shift oil-gas mixture, improving the atomization quality and thus facilitating combustion.

[0020] (2) In the support plate stabilizer provided by the present invention, two transverse air jets can be formed successively during use, so that two aerodynamic barriers are formed on the wall surface of the support plate stabilizer, reducing the wall surface temperature and enabling it to work reliably at a higher incoming flow temperature.

[0021] (3) In the support plate stabilizer provided by the present invention, a reflux zone can be formed by setting a trapezoidal groove at the tail end of the support plate body, which is beneficial to generate a stable combustion flame in the reflux zone at the tail edge of the support plate body after the oil-gas mixture gradually aggregates.

[0022] (4) The support plate stabilizer provided by the present invention makes full use of the momentum difference between the jet and the injected fuel to enhance the atomization of fuel aerodynamics, so that the atomization quality of the supplied fuel is better, and can help form a fuel-air mixture equivalence ratio that is more conducive to combustion, thereby achieving stable combustion within a wider range of operating parameters.

[0023] (5) The support plate stabilizer provided by the present invention integrates multiple functions such as air cooling, shift fuel supply, and flame stabilization, and meets the requirements of high load and low flow resistance afterburner. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the structure of the afterburner provided by the present invention; Figure 2 This is an isometric view of the support plate stabilizer provided by the present invention; Figure 3 This is a front sectional view of the support plate stabilizer provided by the present invention. Figure 4 for Figure 3 Sectional view of AA; Figure 5 for Figure 3 BB section view; Figure 6 This is a schematic diagram illustrating the working principle of the support plate stabilizer provided by the present invention.

[0026] Reference numerals: 1. Combustion chamber casing; 2. Mixer; 3. Shift injector; 4. Support plate stabilizer; 4a. Boss; 4b. Trapezoidal groove; 4c. Support plate body; 5. Center cone; 6. First gas collection chamber; 6a. First air inlet; 6b. First jet slit; 7. Second gas collection chamber; 7a. Second air inlet; 7b. Second jet slit; 8. Shift fuel supply chamber; 8a. Third air inlet; 8b. Third jet slit. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0028] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0029] Furthermore, the use of terms such as "first" and "second" in this invention is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this invention.

[0030] Combination Figures 2 to 5 As shown, this embodiment provides a support plate stabilizer with aerodynamic jet control function. First, for ease of description, the end of the support plate stabilizer where the airflow-facing surface is located is defined as the front end.

[0031] The support plate stabilizer includes a support plate body 4c and a boss 4a integrally formed on the top of the support plate body 4c; inside the support plate body 4c, a first air collection chamber 6, a second air collection chamber 7, and a duty oil supply chamber 8 are arranged sequentially from front to back; a duty oil injection rod 3 is inserted into the duty oil supply chamber 8; a first air inlet 6a, a second air inlet 7a, and a third air inlet 8a are provided on the boss 4a, which are used to introduce external air into the first air collection chamber 6, the second air collection chamber 7, and the duty oil supply chamber 8, respectively; a first jet slit 6b, a second jet slit 7b, and a third jet slit 8b are opened sequentially from front to back on the left and right sides of the support plate body 4c; the first jet slit 6b is connected to the first air collection chamber 6, the second jet slit 7b is connected to the second air collection chamber 7, and the third jet slit 8b is connected to the duty oil supply chamber 8.

[0032] In this embodiment, the entire support plate stabilizer has a symmetrical structure, combined with Figure 4 and Figure 5 As shown, the plane of symmetry is plane A in the figure. The centerlines of the first gas collecting chamber 6, the second gas collecting chamber 7, and the shift oil supply chamber 8 are all located on the plane of symmetry A.

[0033] Combination Figure 2 and Figure 3 As shown, the first gas collecting chamber 6, the second gas collecting chamber 7, and the duty oil supply chamber 8 are all airflow channels extending along the length of the support plate body 4c; the third jet slit 8b is a long strip-shaped slit, and the third jet slit 8b is arranged along the length of the support plate body 4c; there are multiple first jet slits 6b, and the multiple first jet slits 6b are evenly distributed at intervals along the length of the support plate body 4c; there are multiple second jet slits 7b, and the multiple second jet slits 7b are evenly distributed at intervals along the length of the support plate body 4c; in the long direction of the support plate body 4c, the first jet slits 6b and the second jet slits 7b are alternately distributed.

[0034] Combination Figure 2 and Figure 5 As shown, a trapezoidal groove 4b is provided at the tail end of the support plate body 4c, and the trapezoidal groove 4b is arranged along the length direction of the support plate body 4c, with the opening of the trapezoidal groove 4b facing the tail end of the entire support plate stabilizer. Furthermore, the included angle between the inclined surfaces on both sides of the trapezoidal groove 4b is ω, and 80°≤ω≤90°.

[0035] Combination Figure 4 As shown, the inlet of the first air inlet 6a is located on the arc surface at the front end of the boss 4a; there are two second air inlets 7a, arranged in a V-shape, with their inlets located on the left and right curved surfaces of the boss 4a respectively; there are two third air inlets 8a, also arranged in a V-shape, with their inlets located on the left and right curved surfaces of the boss 4a respectively; both the second and third air inlets 7a are inclined towards the front end of the boss 4a. The two second air inlets 7a are symmetrically arranged about plane A, and the two third air inlets 8a are also symmetrically arranged about plane A. Specifically, the included angle between the two second air inlets 7a is α, and the included angle between the two third air inlets 8a is β; and 70°≤α≤75°, 70°≤β≤75°. By setting the second air inlets 7a and the third air inlets 8a to an inclined shape, it is convenient to introduce external air.

[0036] Combination Figure 5 As shown, the first jet slit 6b and the second jet slit 7b are both inclined towards the rear of the support plate body 4c; the third jet slit 8b is perpendicular to the left and right symmetrical plane A of the support plate stabilizer. Further, the first jet slits 6b on both sides of the support plate body 4c are symmetrically arranged about plane A, the second jet slits 7b on both sides of the support plate body 4c are symmetrically arranged about plane A, and the third jet slits 8b on both sides of the support plate body 4c are symmetrically arranged about plane A. Further, the included angle between the first jet slits 6b on the left and right sides of the support plate body 4c is γ, and 135°≤γ≤145°. The included angle between the second jet slits 7b on the left and right sides of the support plate body 4c is δ, and 135°≤δ≤145°.

[0037] Combination Figure 1 As shown, as a second aspect of this embodiment, an afterburner is provided, including a combustion chamber casing 1, a mixer 2 and a central cone 5 arranged coaxially from the outside to the inside; the mixer 2 and the central cone 5 are connected by a plurality of spoke-shaped support plate stabilizers 4; the support plate stabilizers 4 are the support plate stabilizers described above.

[0038] An outer bypass duct is formed between the combustion chamber casing 1 and the mixer 2, and an inner bypass duct is formed between the mixer 2 and the central cone 5. One end of the support plate stabilizer 4 is connected to the mixer 2, and the other end is connected to the central cone 5. The boss 4a on the support plate stabilizer 4 extends into the outer bypass duct formed between the combustion chamber casing 1 and the mixer 2, and the trapezoidal groove 4b at the tail end of the support plate body 4c extends from the inner surface of the mixer 2 to the outer surface of the central cone 5. The first gas collecting chamber 6, the second gas collecting chamber 7, and the shift fuel supply chamber 8 within the support plate body 4c are all airflow channels extending from the mixer 2 towards the central cone 5.

[0039] The center cone 5 is a typical component in an afterburner and will not be described in detail here. The center cone 5 is used to decelerate and diffuse the internal airflow.

[0040] Combination Figures 4 to 6 As shown, the working principle of the support plate stabilizer and afterburner provided in this embodiment is as follows: Within the support plate body 4c of the support plate stabilizer 4, a first air collection chamber 6, a second air collection chamber 7, and a duty oil supply chamber 8 are arranged sequentially from front to back. External air is introduced into the first air collection chamber 6 through the first air inlet 6a, external air is introduced into the second air collection chamber 7 through the second air inlet 7a, and external air is introduced into the duty oil supply chamber 8 through the third air inlet 8a.

[0041] Gas in the first gas collecting chamber 6 is ejected through the first jet slit 6b, forming transverse jet I; gas in the second gas collecting chamber 7 is ejected through the second jet slit 7b, forming transverse jet II; the oil-gas mixture in the duty oil supply chamber 8 is ejected from the third jet slit. Since the first jet slit 6b is located in front of the second jet slit 7b, transverse jet I is located in front of transverse jet II. Therefore, to avoid mutual interference between the mainstream flow and transverse jet II, transverse jet I is introduced before transverse jet II, forming an aerodynamic barrier. This allows the mainstream flow, which is near the wall surface and causing turbulence, to be lifted to a certain height and flow backward, reducing the impact on the interaction flow between the downstream transverse jet II and the duty oil-gas mixture. This allows the transverse jet II to further mix with the downstream duty oil-gas mixture, improving atomization quality.

[0042] During operation, the simultaneous presence of transverse jet I and transverse jet II creates two aerodynamic barriers on the wall of the support plate stabilizer 4, reducing the wall temperature and enabling it to operate reliably at higher incoming flow temperatures.

[0043] By setting a trapezoidal groove 4b at the tail end of the support plate body, a reflux zone can be formed, which is conducive to the gradual aggregation of the oil and gas mixture during the shift and the generation of a stable combustion flame in the reflux zone at the tail edge of the support plate body 4c.

[0044] When the boost is engaged, the duty injector 3 supplies fuel to the duty fuel supply chamber 8, and external air is drawn into the duty fuel supply chamber 8 through the third air intake 8a. It forms a duty fuel-air mixture with the fuel mixture sprayed from the duty injector 3. It is then sprayed out from the third jet slit 8b into the main stream and mixed with the transverse jet II at its front end. The difference in flow rate between the two streams enhances the atomization effect of the duty fuel and plays a role in forming the appropriate fuel-air mixture after mixing with the duty fuel. After that, it enters the recirculation zone for stable combustion.

[0045] During the cooling state, external air is drawn into the duty oil supply chamber 8 through the third air inlet 8a and ejected from the third jet slit 8b, forming an aerodynamic barrier on the wall surface, reducing the wall surface temperature, and enabling it to work reliably at a higher incoming flow temperature.

[0046] Because the first jet slit 6b and the second jet slit 7b are alternately distributed along the long direction of the support plate body 4c, the transverse jet I and transverse jet II formed by the first jet slit 6b and the second jet slit 7b are alternately distributed.

[0047] In the afterburner, because a trapezoidal groove 4b is provided at the tail end of the support plate body 4c, the distance between two adjacent support plate stabilizers 4 is relatively close at the outer surface of the central cone 5, so the small-pitch recirculation zone can achieve circumferential flame connection.

[0048] In this embodiment, both the first jet slit 6b and the second jet slit 7b are inclined toward the rear of the support plate body 4c, so that the ejected transverse jet I and transverse jet II are directed toward the rear of the support plate body 4c.

[0049] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A support plate stabilizer with aerodynamic jet control function, characterized in that, It includes a support plate body (4c) and a boss (4a) integrally formed on the top of the support plate body (4c); a first gas collection chamber (6), a second gas collection chamber (7) and a duty oil supply chamber (8) are arranged sequentially from front to back inside the support plate body (4c); a duty oil injection rod (3) is inserted in the duty oil supply chamber (8). The boss (4a) is provided with a first air inlet (6a), a second air inlet (7a) and a third air inlet (8a), which are used to introduce external air into the first air collection chamber (6), the second air collection chamber (7) and the duty oil supply chamber (8), respectively. The first jet slit (6b), the second jet slit (7b), and the third jet slit (8b) are sequentially opened from front to back on the left and right sides of the support plate body (4c); the first jet slit (6b) is connected to the first gas collecting chamber (6), the second jet slit (7b) is connected to the second gas collecting chamber (7), and the third jet slit (8b) is connected to the duty oil supply chamber (8).

2. The support plate stabilizer as described in claim 1, characterized in that, The third jet slit (8b) is a long strip-shaped slit, and the third jet slit (8b) is set along the length direction of the support plate body (4c); There are multiple first jet slits (6b), and the multiple first jet slits (6b) are evenly distributed at intervals along the length direction of the support plate body (4c); The number of the second jet slits (7b) is multiple, and the multiple second jet slits (7b) are evenly distributed at intervals along the length direction of the support plate body (4c); Along the long direction of the support plate body (4c), the first jet slit (6b) and the second jet slit (7b) are alternately distributed.

3. The support plate stabilizer as described in claim 1, characterized in that, A trapezoidal groove (4b) is provided at the tail end of the support plate body (4c), and the trapezoidal groove (4b) is arranged along the long direction of the support plate body (4c).

4. The support plate stabilizer as described in claim 3, characterized in that, The included angle between the inclined surfaces on both sides of the trapezoidal groove (4b) is ω, and 80°≤ω≤90°.

5. The support plate stabilizer as described in claim 1, characterized in that, The inlet of the first air inlet (6a) is opened on the arc surface at the front end of the boss (4a); There are two second air inlets (7a), and the two second air inlets (7a) are arranged in a V-shape. The inlets of the two second air inlets (7a) are respectively opened on the left and right curved surfaces of the boss (4a); The number of the third air inlet (8a) is two, and the two third air inlets (8a) are arranged in a V-shape. The inlets of the two third air inlets (8a) are respectively opened on the left and right curved surfaces of the boss (4a). The second air inlet (7a) and the third air inlet (8a) are both inclined toward the front end of the boss (4a).

6. The support plate stabilizer as described in claim 1, characterized in that, The included angle between the two second air inlets (7a) is α, and the included angle between the two third air inlets (8a) is β; and 70°≤α≤75°, 70°≤β≤75°.

7. The support plate stabilizer as described in claim 1, characterized in that, The first jet slit (6b) and the second jet slit (7b) are both inclined toward the rear of the support plate body (4c); the third jet slit (8b) is perpendicular to the left and right symmetrical plane A of the support plate stabilizer.

8. The support plate stabilizer as described in claim 7, characterized in that, The included angle between the first jet slits (6b) on the left and right sides of the support plate body (4c) is γ, and 135°≤γ≤145°.

9. The support plate stabilizer as described in claim 7, characterized in that, The included angle between the second jet slits (7b) on the left and right sides of the support plate body (4c) is δ, and 135°≤δ≤145°.

10. An afterburner, comprising a combustion chamber casing (1), a mixer (2), and a central cone (5) arranged coaxially from the outside to the inside; the mixer (2) and the central cone (5) are connected by a plurality of spoke-shaped support stabilizers (4); characterized in that, The support plate stabilizer (4) adopts the support plate stabilizer according to any one of claims 1 to 9, and the boss (4a) extends into the outer bypass formed between the combustion chamber casing (1) and the mixer (2).

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