Design method of aero-engine flame stabilizer with reinforced skirt

Abstract

The invention provides a design method of a skirt-reinforced aero-engine flame stabilizer, which comprises the following steps of: 1, checking the thickness of a raw material by using a micrometer, and carrying out multi-point measurement along the periphery of a plate without an out-of-tolerance condition; secondly, laser equipment is checked, the end face of a laser nozzle should be flat, laser cutting blanking is carried out, dragging is not allowed in the process, and the surface of the plate is prevented from being scratched. And thirdly, burrs are manually removed, and it should be guaranteed that the surface is free of burrs and sharp edges. And 4, the mold is adjusted, the cut plate is put into the mold to be subjected to stretch forming, and after forming, whether indentation and creases exist or not is checked. And fifthly, the end face and the small hole of the flame stabilizer are machined, a remelting layer is removed, the turned edge is knocked and repaired, and component forming is completed. The method has the advantages that the manufacturability complexity and the manufacturing cost are low, and the manufacturing cost, the part replacement cost, the maintenance cost and the test run cost are saved.

Description

Technical Field

[0001] The invention relates to the field of aeroengines, and in particular to a design method for a skirt-reinforced aeroengine flame stabilizer. Background Art

[0002] The flame stabilizer of an aircraft engine is the main component for ignition and stable combustion of the afterburner. The air flowing out of the outer duct is mixed with the gas in the inner duct after the low-pressure turbine through the mixer. The mixed gas first reduces the flow rate in the diffuser and mixes with the fuel sprayed by the fuel injection device, but its flow rate is still very high, so a flame stabilizer must be used to organize combustion. At present, the V-groove structure is mostly used. The flame stabilizer is similar to a windbreak in a strong wind. The V-groove structure can form a recirculation zone, continuously ignite the fresh oil and gas mixture at the edge of the stabilizer, stabilize the flame and spread it out. At the same time, the flame stabilizer is also subjected to long-term erosion of high-temperature gas, resulting in ablation of the skirt, which increases the maintenance cost of engine parts. Summary of the invention

[0003] The purpose of the present invention is to improve the structural strength of the skirt of an aircraft engine flame stabilizer to ensure reliable operation of the flame stabilizer during the overhaul period, and a design method for an aircraft engine flame stabilizer with a reinforced skirt is provided.

[0004] The present invention provides a method for designing a skirt-reinforced flame stabilizer for an aircraft engine. The method comprises the following steps: step 1: using a micrometer to check the thickness of the raw material, measuring at multiple points along the periphery of the plate, and not allowing any out-of-tolerance situation.

[0005] Step 2: Check the laser equipment. The end face of the laser nozzle should be flat. Perform laser cutting and blanking. Dragging is not allowed during this process to avoid scratching the surface of the sheet.

[0006] Step 3: Manual deburring, the surface should be free of burrs and sharp edges.

[0007] Step 4: Adjust the mold, put the cut sheet into the mold, stretch it, and check whether there are pits and folds after forming.

[0008] Step 5: Machining the end face and small hole of the flame stabilizer, removing the remelted layer and hammering the flange to complete the component forming.

[0009] The working environment of aircraft engine flame stabilizers is relatively harsh, and its structural reliability cannot be improved simply by increasing the thickness of the components. Since the weight of the structure directly affects the thrust-to-weight ratio of the engine, it is necessary to locally strengthen the ablation position and ensure that the flame stabilizer forms a stable reflow zone at the V-groove position.

[0010] The present invention adopts flow field analysis and strength verification methods, invents a skirt structure strength enhancement method, and proposes and improves the existing process forming method to improve the overall strength of the flame stabilizer outlet edge as a whole.

[0011] Compared with the prior art, the present invention has the following advantages:

[0012] The design method of the skirt-reinforced aircraft engine flame stabilizer described in the present invention has improved structural strength, and its process complexity and manufacturing cost are both low. It only needs to modify the stretching forming mold to fundamentally solve the existing structural ablation problem. Currently, the ablation problem on aircraft engines is solved by replacing new parts. Therefore, the present invention saves considerable manufacturing cost, replacement cost, maintenance cost and trial run cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments:

[0014] Figure 1 Schematic diagram of the local reinforcement of the flame stabilizer skirt. DETAILED DESCRIPTION

[0015] The present invention will be further explained below in conjunction with specific implementation plans, but the present invention is not limited thereto. The structures, proportions, sizes, etc. illustrated in the drawings of the specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the restrictive conditions under which the present invention can be implemented. Therefore, they have no substantive technical significance. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed by the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0016] A method for designing a skirt-reinforced flame stabilizer for an aircraft engine is characterized by: Step 1: Using a micrometer to check the thickness of the raw material, measuring at multiple points along the periphery of the plate, and not allowing any out-of-tolerance situation.

[0017] Step 2: Check the laser equipment. The end face of the laser nozzle should be flat. Perform laser cutting and blanking. Dragging is not allowed during this process to avoid scratching the surface of the sheet.

[0018] Step 3: Manual deburring, the surface should be free of burrs and sharp edges.

[0019] Step 4: Adjust the mold, put the cut sheet into the mold, stretch it, and check whether there are pits and folds after forming.

[0020] Step 5: Machining the end face and small hole of the flame stabilizer, removing the remelted layer and hammering the flange to complete the component forming.

[0021] The working environment of aircraft engine flame stabilizers is relatively harsh, and its structural reliability cannot be improved simply by increasing the thickness of the components. Since the weight of the structure directly affects the thrust-to-weight ratio of the engine, it is necessary to locally strengthen the ablation position and ensure that the flame stabilizer forms a stable reflow zone at the V-groove position.

[0022] The present invention adopts flow field analysis and strength verification methods, invents a skirt structure strength enhancement method, and proposes and improves the existing process forming method to improve the overall strength of the flame stabilizer outlet edge as a whole.

[0023] Matters not covered by the present invention are known technologies.

[0024] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A method for designing a skirt-reinforced flame stabilizer for an aircraft engine, characterized in that: The following steps are involved: Step 1: Use a micrometer to check the thickness of the raw material, and measure at multiple points along the periphery of the plate. No out-of-tolerance is allowed; Step 2: Check the laser equipment. The end surface of the laser nozzle should be flat. Perform laser cutting and blanking. Dragging is not allowed during this process to avoid scratching the surface of the sheet. Step 3: Manual deburring, the surface should be free of burrs and sharp edges; Step 4: Adjust the mold, put the cut sheet into the mold, stretch it, and check whether there are pits and folds after forming; Step 5: Machining the end face and small hole of the flame stabilizer, removing the remelted layer and hammering the flange to complete the component forming.

2. The method for designing a skirt-reinforced flame stabilizer for an aircraft engine according to claim 1, characterized in that: A local reinforcement structure is set at the ablation position, and at the same time, it is ensured that the flame stabilizer forms a stable reflow zone at the V-groove position.

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