Novel flame stabilizer structure

Abstract

The invention discloses a novel stabilizer structure. The novel stabilizer structure comprises a stabilizer structure body which enables fuel oil sprayed out of an oil supply device to generate fuel oil penetration. The stabilizer structure comprises a stabilizer with the interior being hollow. A radial boss is arranged on the outer surface of the outlet trailing edge of the stabilizer; a jet flow seam with the width of L is formed in the boss, an angle alpha is formed between the jet flow seam and the main flow flowing direction, and the jet flow seam inclines towards the windward side of the stabilizer at the angle alpha. The surface of the boss is a jet flow plane in an inclined state. When the fuel oil supply device sprays fuel oil out of the stabilizer, swirling airflow in the backflow area b enables the fuel oil to generate fuel oil penetration and be more fully mixed with a main flow, and the problem that the fuel oil sprayed out of the fuel oil supply device can only flow tightly attached to the surface of the flame stabilizer under the action of the main flow to be mixed with air and cannot generate fuel oil penetration is solved.

Description

Technical Field

[0001] The invention relates to a novel flame stabilizer structure and belongs to the technical field of aviation engines. Background Art

[0002] The flame stabilizer in the afterburner plays an important role in stabilizing the ignition source in high-speed airflow, organizing stable combustion, and flame transmission.

[0003] Although the existing flame stabilizer (such as the Chinese patent publication number CN116697403A) is provided with an oil outlet for fuel to be discharged and mixed with air, the mainstream air will cause the fuel at the oil outlet to flow closely to the surface of the flame stabilizer to mix with the air. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides a novel flame stabilizer structure.

[0005] The present invention is achieved through the following technical solutions.

[0006] The present invention provides a novel stabilizer structure, comprising:

[0007] A stabilizer structure is provided to realize fuel penetration of the fuel sprayed by the fuel supply device.

[0008] The stabilizer structure comprises a stabilizer which is hollow inside;

[0009] The outer surface of the trailing edge of the stabilizer outlet is provided with a radial boss; a jet slot with a width of L is provided in the boss, the jet slot has an angle α with the mainstream flow direction, and the jet slot is inclined toward the windward surface of the stabilizer at the angle α; the surface of the boss is an inclined jet plane.

[0010] The jet slot width L is 2 mm to 4 mm; the stabilizer width D is 10 mm to 35 mm; and the boss thickness H is not less than 1 mm.

[0011] The windward surface of the stabilizer facing the mainstream air is semicircular; the trailing edge of the stabilizer away from the mainstream air is square; the bosses are symmetrically distributed on the stabilizer; the α angle is greater than or equal to 90°; and the jet plane is perpendicular to the jet slit.

[0012] The windward surface of the stabilizer at the front end of the boss is equipped with an oil supply device for spraying fuel to the outside of the stabilizer, and the oil supply device is symmetrically distributed on the windward surface of the stabilizer; the mainstream flow interacts with the jet gas sprayed from the jet gap to form a low-speed reflux reflux zone b outside the stabilizer at the oil supply device.

[0013] The square tail of the stabilizer forms a recirculation zone a.

[0014] The beneficial effect of the present invention is that when the fuel supply device sprays fuel to the outside of the stabilizer, the swirling airflow in the recirculation zone b causes the fuel to penetrate and mix more fully with the mainstream, thereby solving the problem that the fuel sprayed by the fuel supply device can only flow close to the surface of the flame stabilizer to mix with the air under the action of the mainstream and cannot produce fuel penetration. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the structure of the present invention;

[0016] Figure 2 is a cross-sectional view of a cross section of the present invention;

[0017] Figure 3 It is a cross-sectional view of the present invention in a working state;

[0018] In the figure: 1-fuel supply device; 11-fuel; 2-stabilizer; 21-protrusion; 22-jet slot; 23-jet plane; 24-jet gas; 3-main stream. DETAILED DESCRIPTION

[0019] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0020] like Figures 1 to 3 shown.

[0021] A novel stabilizer structure design method of the present application includes the following steps:

[0022] Step 1: Given the physical blockage ratio of the stabilizer, the characteristic dimensions of the stabilizer 2, including the slot width, number, and radial height, can be preliminarily designed so that the blockage ratio of the stabilizer in the cross section of the afterburner meets the requirements;

[0023] Step 2: Based on the above-mentioned groove width, number, and radial height dimensions of the stabilizer 2, the stabilizer 2 is designed to have a semicircular windward surface and a square tail structure. This structure is similar to the turbine support support plate structure and can be coupled with the turbine support as needed, that is, an afterburner chamber solution integrated with the turbine rear frame, in which the windward surface can be designed as a blade-shaped shape according to the inlet airflow angle.

[0024] Step 3: A boss 21 is designed at a certain distance (2mm-5mm) in front of the tail edge of the outlet of the stabilizer 2 shell designed above, and a jet slit 22 with a width of L is opened on the boss 21. The characteristic design parameters of the boss 21 and the jet slit 22 are as shown in the attached figure. Figure 2As shown. The radial surface of the boss 21 is a jet plane 23, wherein the jet plane 23 is symmetrically distributed about the axis of the stabilizer 2, and the jet plane forms a certain angle α with the mainstream flow direction, and the angle α should be greater than or equal to 90°. The position of the jet plane 23 has a certain height H compared to the blunt body to ensure that the jet gas can further penetrate the mainstream 3. The width L of the jet slit 22 determines the jet flow rate under a certain jet pressure. The width L or distribution form of the jet slit 22 can be adjusted to adapt to the uneven distribution conditions of the inlet flow to organize combustion.

[0025] Step 4: Based on the above preliminary design, the design is carried out through UG modeling, and then CFD simulation is performed to calculate the jet plane 23 under different jet pressures under different inlet conditions, and observe the size of the recirculation zone, the frequency of vortex shedding, the fuel penetration, and the wall temperature of the stabilizer 2 in the simulation. If the size of the recirculation zone, the frequency of vortex shedding, the fuel penetration, and the stabilizer wall temperature meet the design requirements, the design is completed. If they do not meet the requirements, the layout, number, jet plane jet angle, jet height, jet plane width and other parameters of the stabilizer 2 need to be readjusted until the requirements are met.

[0026] The stabilizer 2 of the present application is designed through UG modeling. When using CFD simulation, the layout, number, jet plane jet angle, jet height, and jet plane width elements of the stabilizer 2 are adjusted to optimize the multivariate simulation of the stabilizer 2, thereby solving the problem that the prior art only considers the air flow and fuel flow conditions for simulation, but cannot realize the optimization of the flame stabilizer through multivariate simulation.

[0027] According to the above design method, a new stabilizer structure is obtained, including:

[0028] The stabilizer 2 has a semicircular windward surface and a square tail, and the stabilizer 2 is hollow for high-pressure air input. The bosses 21 are symmetrically distributed on the stabilizer 2.

[0029] The stabilizer 2 has a radial boss 21 on the outer surface of the outlet trailing edge.

[0030] The boss 21 is provided with a jet slot 22 with a width of L. The jet slot 22 forms an angle α with the flow direction of the mainstream 3. The jet slot 22 is inclined toward the windward surface of the stabilizer 2 at the angle α, and the angle α is greater than or equal to 90°.

[0031] The surface of the boss 21 is an inclined jet plane 23 , and the jet plane 23 is perpendicular to the jet slit 22 .

[0032] The windward surface of the stabilizer 2 at the front end of the boss 21 is equipped with an oil supply device 1, which is symmetrically distributed on the windward surface of the stabilizer 2. The flow of the mainstream 3 interacts with the jet gas 24 ejected from the jet slit 22 to form a low-speed reflux reflow zone b outside the stabilizer 2 at the oil supply device 1. The size of the reflow zone is adjusted by adjusting the jet pressure of the jet gas 24, achieving the advantage of adaptive adjustment of the reflow zone according to the working conditions. The jet gas 24 can be hydrogen or other combustible gases, and there is no need to draw gas from the main engine.

[0033] When the fuel supply device 1 sprays the fuel 11 to the outside of the stabilizer 2, the swirling airflow in the recirculation zone b causes the fuel 11 to penetrate and mix more fully with the main flow 3, solving the problem that the fuel 11 sprayed by the fuel supply device 1 can only flow close to the surface of the flame stabilizer 2 in the main flow 3 to mix with the air and cannot penetrate. Fuel penetration can also be built into the stabilizer 2 cavity by injecting oil, and the oil is mixed with the high-pressure air in the stabilizer cavity to form an oil-gas mixture, and then sprayed from the jet slit 22, which can also play an auxiliary penetration role. The blockage ratio of this type of flame stabilizer does not exceed 0.15.

[0034] The width L of the jet slit 22 is 2 mm to 4 mm; the width D of the stabilizer 2 is 10 mm to 35 mm; and the thickness H of the boss 21 is not less than 1 mm.

Claims

1. A novel flame stabilizer structure, characterized in that: include: A stabilizer structure is provided for achieving fuel penetration of the fuel (11) sprayed out by a fuel supply device (1).

2. The novel flame stabilizer structure according to claim 1 is characterized in that: The stabilizer structure comprises a stabilizer (2) which is hollow inside; The stabilizer (2) has a radial boss (21) on its outlet trailing edge; a jet slit (22) with a width of L is provided in the boss (21); the jet slit (22) has an angle α with the flow direction of the mainstream (3); the jet slit (22) is inclined toward the windward side of the stabilizer (2) at the angle α; and the surface of the boss (21) is an inclined jet plane (23).

3. The novel flame stabilizer structure according to claim 2 is characterized in that: The width L of the jet slit (22) is 2 mm to 4 mm.

4. The novel flame stabilizer structure according to claim 2 is characterized in that: The thickness H of the boss (21) is not less than 1 mm.

5. The novel flame stabilizer structure according to claim 2 is characterized in that: The width D of the stabilizer (2) is 10 mm to 35 mm.

6. The novel flame stabilizer structure according to claim 2 is characterized in that: The windward surface of the stabilizer (2) facing the mainstream (3) air is semicircular; the trailing edge of the stabilizer (2) away from the mainstream (3) air is square; the bosses (21) are symmetrically distributed on the stabilizer (2); the α angle is greater than or equal to 90°; and the jet plane (23) is perpendicular to the jet slit (22).

7. The novel flame stabilizer structure according to claim 2 is characterized in that: The windward surface of the stabilizer (2) at the front end of the boss (21) is equipped with an oil supply device (1) for spraying fuel (11) to the outside of the stabilizer (2), and the oil supply device (1) is symmetrically distributed on the windward surface of the stabilizer (2); the flow of the mainstream (3) interacts with the jet gas (24) sprayed from the jet slit (22) to form a low-speed reflux recirculation area b outside the stabilizer (2) at the oil supply device (1).

8. The novel flame stabilizer structure according to claim 7 is characterized in that: The square tail of the stabilizer (2) forms a recirculation zone a.

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