A novel flame holder structure

Abstract

The application discloses a novel stabilizer structure, which comprises a stabilizer with a hollow interior, a radial boss on the outer surface of the tail edge of the stabilizer outlet, a jet gap with a width of L arranged in the boss, the jet gap being inclined to the windward surface of the stabilizer at an angle of alpha with the main flow direction, and a jet plane with an inclined surface of the boss. When the fuel sprayed by the fuel supply device flows to the outside of the stabilizer, the backflow area b is rotated to make the fuel fully mixed with the main flow through fuel penetration, thereby solving the problem that the fuel sprayed by the fuel supply device can only flow along the surface of the flame stabilizer to mix with air under the action of the main flow and cannot generate fuel penetration.

Description

Technical Field

[0001] This invention relates to a novel flame stabilizer structure, belonging to the field of aero-engine technology. Background Technology

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

[0003] Existing flame stabilizers (such as those with Chinese patent publication number CN116697403A) have oil outlets for fuel to be discharged and mixed with air. However, the mainstream air causes the fuel at the oil outlet to flow closely to the surface of the flame stabilizer and mix with the air. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a novel flame stabilizer structure.

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

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

[0007] A stabilizer structure that enables fuel penetration of the fuel injected by the fuel supply device.

[0008] The stabilizer structure includes a hollow stabilizer.

[0009] The stabilizer outlet trailing edge has a radial boss; the boss has a jet slit with a width of L, the jet slit has an angle α with the main flow direction, and the jet slit is inclined towards the windward side of the stabilizer at an angle α; the surface of the boss is an inclined jet plane.

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

[0011] The stabilizer's windward side facing the mainstream air is semi-circular; the stabilizer's trailing edge away from the mainstream air is square; the protrusions 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] A fuel supply device is installed on the windward surface of the stabilizer at the front end of the boss, which sprays fuel to the outside of the stabilizer. The fuel supply devices are symmetrically distributed on the windward surface of the stabilizer. The interaction between the mainstream flow and the jet gas ejected from the jet slot forms a low-speed recirculation zone b outside the stabilizer at the fuel supply device.

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

[0014] The beneficial effects of this invention are as follows: when the fuel supply device sprays fuel to the outside of the stabilizer, the swirling airflow in the return zone b causes the fuel to penetrate and mix more fully with the mainstream, which solves 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 and cannot penetrate the mainstream. Attached Figure Description

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

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

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

[0018] In the diagram: 1-Fuel supply device; 11-Fuel; 2-Stabilizer; 21-Boss; 22-Jet slot; 23-Jet plane; 24-Injected gas; 3-Main stream. Detailed Implementation

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

[0020] like Figures 1 to 3 As shown.

[0021] This application discloses a novel stabilizer structure design method, which includes the following steps:

[0022] Step 1: Given the physical blockage ratio of the stabilizer, the characteristic dimensions of stabilizer 2, including slot width, number, and radial height, can be preliminarily designed to ensure 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 stabilizer 2 slot width, number, and radial height dimensions, stabilizer 2 is designed with a semi-circular frontal surface and a square rear end. This structure is similar to the turbine support plate structure and can be coupled with the turbine support as needed, which is an integrated afterburner scheme with the turbine rear frame. The frontal surface can be designed with a blade-shaped shape according to the inlet airflow angle.

[0024] Step 3: A boss 21 is designed at a certain distance (2mm~5mm) before the outlet tail edge of the stabilizer 2 housing as described above. 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 shown in the attached figure. Figure 2As shown. The radial surface of the boss 21 is the jet plane 23, which is symmetrically distributed about the axis of the stabilizer 2. This 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 relative to the blunt body to ensure that the jet gas can further penetrate the mainstream 3. The width L of the jet slot 22 determines the jet flow rate under a certain jet pressure. Combustion can be organized by adjusting the width L or the distribution of the jet slot 22 to adapt to the uneven distribution of the inlet flow.

[0025] Step 4: Based on the preliminary design above, design is carried out using UG modeling, followed by CFD simulation calculations to determine the jet plane 23 under different inlet conditions and jet pressures. The simulation results are observed for the size of the recirculation zone, the frequency of vortex shedding, fuel penetration, and the wall temperature of stabilizer 2. If the size of the recirculation zone, the frequency of vortex shedding, the fuel penetration, and the stabilizer wall temperature all meet the design requirements, the design is complete. If they do not meet the requirements, the layout, number, jet plane angle, jet height, and jet plane width of stabilizer 2 need to be readjusted until the requirements are met.

[0026] The stabilizer 2 in this application is designed through UG modeling. During CFD simulation, the layout, number, jet plane angle, jet height, and jet plane width of the stabilizer 2 are adjusted to optimize the multi-dimensional simulation of the stabilizer 2. This solves the problem that the existing technology only considers the air flow and fuel flow conditions for simulation and cannot achieve multi-dimensional simulation optimization of the flame stabilizer.

[0027] Based on the above design method, a novel stabilizer structure is obtained, comprising:

[0028] The stabilizer 2 has a semi-circular front and a square rear, and its interior is hollow to allow high-pressure air input. The protrusions 21 are symmetrically distributed on the stabilizer 2.

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

[0030] The boss 21 has a jet slit 22 with a width of L. The jet slit 22 has an angle α with the flow direction of the main flow 3. The jet slit 22 is inclined towards the windward side of the stabilizer 2 at an 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, which is perpendicular to the jet slot 22.

[0032] An oil supply device 1 is installed on the windward surface of the stabilizer 2 at the front end of the boss 21. The oil supply devices 1 are symmetrically distributed on the windward surface of the stabilizer 2. The main flow 3 interacts with the jet gas 24 ejected from the jet slot 22 to form a low-speed recirculation zone b outside the stabilizer 2 at the oil supply device 1. The size of the recirculation zone can be adjusted by adjusting the jet pressure of the jet gas 24, achieving the advantage of adaptive adjustment of the recirculation zone according to the operating conditions. The jet gas 24 can be hydrogen or other combustible gas, without the need to draw gas from the main unit.

[0033] When the fuel supply device 1 sprays 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 thoroughly with the mainstream 3. This solves 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 and mix with air in the mainstream 3 without achieving fuel penetration. Fuel penetration can also be achieved by injecting fuel into the stabilizer 2 cavity, where the fuel mixes with the high-pressure air in the stabilizer cavity to form an oil-air mixture, which is then sprayed out from the jet slit 22, thus also aiding in penetration. The blockage ratio of this type of flame stabilizer does not exceed 0.15.

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

Claims

1. A novel flame stabilizer structure, characterized in that, include: A stabilizer structure that enables fuel penetration of the fuel (11) injected by the fuel supply device (1); The stabilizer structure includes a hollow stabilizer (2); The stabilizer (2) has a radial boss (21) on the outer surface of the outlet tail edge; the boss (21) has a jet slit (22) with a width of L, the jet slit (22) has an angle α with the flow direction of the main stream (3), and the jet slit (22) is inclined towards the windward side of the stabilizer (2) at an angle α; the surface of the boss (21) is an inclined jet plane (23); The windward side of the stabilizer (2) facing the mainstream air (3) is semi-circular; the trailing edge of the stabilizer (2) away from the mainstream air (3) is square; the bosses (21) are symmetrically distributed on the stabilizer (2); the α angle is greater than or equal to 90°; the jet plane (23) is perpendicular to the jet slot (22); A fuel supply device (1) is installed on the windward surface of the stabilizer (2) at the front end of the boss (21) to spray fuel (11) to the outside of the stabilizer (2). The fuel supply devices (1) are symmetrically distributed on the windward surface of the stabilizer (2). The main flow (3) and the jet gas (24) ejected from the jet slit (22) interact to form a low-speed backflow zone b outside the stabilizer (2) at the fuel supply device (1).

2. The novel flame stabilizer structure as described in claim 1, characterized in that: The width L of the jet slit (22) is 2mm~4mm.

3. The novel flame stabilizer structure as described in claim 1, characterized in that: The thickness H of the boss (21) is not less than 1 mm.

4. The novel flame stabilizer structure as described in claim 1, characterized in that: The width D of the stabilizer (2) is 10mm~35mm.

5. The novel flame stabilizer structure as described in claim 1, characterized in that: The stabilizer (2) has a square tail section that forms a recirculation zone a.

Images