Novel stabilizer structure design method

Abstract

The invention discloses a novel stabilizer structure design method. According to the design method, a stabilizer is optimized through multivariate simulation during CFD simulation. The stabilizer is designed through UG modeling, when CFD simulation is carried out, multi-element simulation of the stabilizer is optimized by adjusting the layout, the number, the jet plane jet angle, the jet height and the jet plane width element of the stabilizer, and the problem that in the prior art, simulation is carried out only by considering the air flow and fuel flow conditions, and the simulation efficiency is low is solved. And multi-element simulation of the flame stabilizer cannot be realized for optimization.

Description

Technical Field

[0001] The invention relates to a novel stabilizer structure design method, belonging to the technical field of aeroengines. 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] The flame stabilizer needs to be simulated after design, but the existing simulation of combustion structures only considers conditions such as air flow and fuel flow for simulation (see Chinese patent publication number CN117494331A), and cannot realize multivariate simulation of the flame stabilizer for optimization. Summary of the invention

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

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

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

[0007] The stabilizer is designed by multivariate simulation during CFD simulation.

[0008] The design method comprises the following steps: Step 1: given a known physical blockage ratio of the stabilizer, a preliminary design can be made for characteristic dimensions of the stabilizer including slot width, number, and radial height, so that the blockage ratio of the stabilizer in the cross section of the afterburner chamber meets the requirements.

[0009] The design method also includes step 2: based on the groove width, number, and radial height dimensions of the stabilizer, the stabilizer is designed to have a semicircular windward surface and a square tail.

[0010] The design method also includes step three: designing a boss at the tail edge of the stabilizer shell outlet, and a jet slot with a width of L is opened on the boss; the radial surface of the boss is a jet plane, wherein the jet plane is symmetrically distributed about the stabilizer axis, and the jet plane forms an angle α with the mainstream flow direction.

[0011] The design method also includes step 4: designing through UG modeling, and then performing CFD simulation calculations under different inlet conditions, the jet plane under different jet pressures, and observing the size of the recirculation zone, the frequency of vortex shedding, the fuel penetration, and the stabilizer wall temperature in the simulation. 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 completed. If they do not meet the requirements, the stabilizer layout, number, jet plane jet angle, jet height, jet plane width and other parameters need to be readjusted until the requirements are met.

[0012] The beneficial effect of the present invention is that the stabilizer is designed through UG modeling, and when it is simulated through CFD, the layout, number, jet plane jet angle, jet height, and jet plane width elements of the stabilizer are adjusted to optimize the multivariate simulation of the stabilizer, 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 multivariate simulation. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of the structure of the present invention;

[0014] Figure 2 is a cross-sectional view of a cross section of the present invention;

[0015] Figure 3 It is a cross-sectional view of the present invention in a working state;

[0016] 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

[0017] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0018] like Figures 1 to 3 shown.

[0019] A novel stabilizer structure design method of the present application includes the following steps:

[0020] 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;

[0021] 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.

[0022] 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 jet plane 23 is located at 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 of the jet slit 22 or the distribution form can be adjusted to adapt to the uneven distribution conditions of the inlet flow to organize combustion.

[0023] 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.

[0024] 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.

[0025] According to the above design method, a new stabilizer structure is obtained, including:

[0026] 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.

[0027] The stabilizer 2 has a radial boss 21 on the outer surface of the outlet trailing edge.

[0028] 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°.

[0029] The surface of the boss 21 is an inclined jet plane 23 , and the jet plane 23 is perpendicular to the jet slit 22 .

[0030] 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.

[0031] 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 mainstream 3, so as to avoid the fuel 11 sprayed by the fuel supply device 1 can only flow close to the surface of the flame stabilizer 2 to mix with the air in the mainstream 3. At the same time, the jet gas 24 is introduced into the airflow by the outer duct or the compressor, and the temperature is relatively low. When it is sprayed from the jet plane 23, it can play a certain role in reducing the wall temperature of the stabilizer 2 shell. After the mainstream 3 and the fuel 11 flow through the boss 21, a recirculation zone a is formed at the square tail of the stabilizer 2. 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 role in penetration. The blockage ratio of this type of flame stabilizer does not exceed 0.15.

[0032] 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 stabilizer structure design method, characterized in that: include: A design method for optimizing the stabilizer (2) through multivariate simulation during CFD simulation.

2. The novel stabilizer structure design method according to claim 1, characterized in that: The design method comprises the following steps: Step 1: when the physical blockage ratio of the stabilizer is known, the characteristic dimensions of the stabilizer (2) including the groove width, number and radial height can be preliminarily designed so that the blockage ratio of the stabilizer in the cross section of the afterburner chamber meets the requirements.

3. The novel stabilizer structure design method according to claim 2, characterized in that: The design method further comprises: step 2: based on the groove width, number and radial height dimensions of the stabilizer (2), designing the stabilizer (2) to have a semicircular windward surface and a square tail.

4. The novel stabilizer structure design method according to claim 3, characterized in that: The design method further comprises the following steps: step 3: designing a stabilizer (2) shell outlet tail edge provided with a boss (21), the boss (21) being provided with a jet slit (22) having a width of L; the radial surface of the boss (21) being a jet plane (23), wherein the jet plane (23) is symmetrically distributed about the axis of the stabilizer (2), and the jet plane (23) forms an angle α with the mainstream flow direction.

5. The novel stabilizer structure design method according to claim 4, characterized in that: The design method also Including, step 4: design through UG modeling, and then perform CFD simulation calculation under different inlet conditions, the jet plane (23) under different jet pressures, observe the size of the recirculation zone, the frequency of vortex shedding, the fuel penetration, and the stabilizer (2) wall temperature in the simulation. 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 completed. If they do not meet the requirements, the stabilizer (2) layout, number, jet plane jet angle, jet height, jet plane width and other parameters need to be readjusted until the requirements are met.

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