Process for simultaneously forming multiple lobe parts of aero-engine mixer

Abstract

The invention is applicable to the technical field of aero-engine mixer lobe processing, and provides a process for simultaneously forming multiple aero-engine mixer lobes, which comprises the following steps: step 1, blanking; step 2, primary stretching; step 3, secondary stretching; step 4, carrying out first heat treatment; 5, stretching for the third time; step 6, stretching for the fourth time; the convex hull is stretched into a spline curve, the highest position of the spline curve is R470, the lowest position of the spline curve is R390, the middle of the spline curve is in transition according to coordinate points of a design drawing, the width of the spline curve is 52.7 cm, and the angles of the two sides of the plate are 14 degrees 43 '32 ''; step 8, carrying out secondary heat treatment; and 9, multiple pieces are formed, specifically, a middle convex hull is used for positioning, and four single pieces are formed on the two sides of the convex hull through a bending and stretching conforming process. After multiple parts are formed, 12 single parts are welded into a circular ring shape, the number of welding seams is 12, and the number of the welding seams is reduced to 12, so that welding deformation is controlled, and airflow of the inner duct and airflow of the outer duct are fully mixed.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine mixer lobe processing, in particular to a simultaneous molding process of multiple aircraft engine mixer lobes. Background Art

[0002] The mixer flap in an aircraft engine is a structural element used for airflow control, which is mainly used in propulsion systems to optimize air flow, enhance combustion efficiency, and reduce engine emissions and noise. It is usually used to mix air and fuel, or mix gas flows from different airflow sources.

[0003] In turbine engines, mixer lobes are usually located at the front of the combustion chamber. They ensure the best mixing of air and fuel in the combustion chamber by controlling the mixed airflow. Specifically, mixer lobes have the following key functions:

[0004] 1. Airflow regulation: The mixer lobes help achieve smooth mixing of airflow by changing the speed and direction of the airflow, especially between the high-pressure and low-pressure areas of the engine.

[0005] 2. Improved combustion efficiency: By optimizing airflow mixing, the mixer lobes help the combustion process to be more complete, improving combustion efficiency and engine performance.

[0006] 3. Reduce emissions: Good air flow mixing can help reduce the generation of harmful emissions, especially nitrogen oxides (NOx) and hydrocarbons (HC).

[0007] 4. Noise suppression: In some engine designs, mixer lobes can also reduce jet noise by changing the airflow distribution, especially the noise generated by supersonic jets.

[0008] 5. Shock and vibration reduction: It can also act as a shock absorber in certain designs to avoid unnecessary vibrations in the engine.

[0009] Traditional aircraft engine mixer lobe forming processing methods mostly adopt single-piece forming, and the specific method is as follows: cutting → bending → primary stretching → heat treatment → secondary stretching → heat treatment → shaping → knocking → trimming → edge cutting → rib pressing → knocking → inspection. In this way, after the single-piece forming is completed, 24 pieces are welded into a circular ring with 24 welds, which causes serious welding deformation and affects the full mixing of the airflow.

[0010] In view of the above reasons, the present invention proposes a process for simultaneously molding multiple pieces of aircraft engine mixer lobes. Summary of the invention

[0011] The purpose of the present invention is to provide a process for simultaneously forming multiple pieces of mixer lobes of an aircraft engine, so as to solve the problem in the prior art that after the single piece forming is completed, the welding deformation is serious, which affects the full mixing of the airflow.

[0012] To achieve the above object, the present invention provides the following technical solution: a process for simultaneously molding multiple pieces of mixer lobes of an aircraft engine, comprising the following steps:

[0013] Step 1, cutting:

[0014] Placing the workpiece on the mold;

[0015] Step 2, one stretch:

[0016] The sheet is stretched into a convex shape to form a convex hull with a middle height of 16 cm, a width of 52.7 cm, and an angle of 3 degrees on both sides of the sheet;

[0017] Step 3, secondary stretching:

[0018] The convex hull is stretched into a convexity with a middle height of 32 cm, a width of 52.7 cm, and an angle of 6 degrees on both sides of the sheet;

[0019] Step 4, first heat treatment:

[0020] Heat treating the workpiece in step 2 to remove the stress generated by forming;

[0021] Step 5, three stretches:

[0022] The convex hull is stretched into a convexity with a middle height of 48 cm, a width of 52.7 cm, and an angle of 9 degrees on both sides of the sheet;

[0023] Step 6, four stretches:

[0024] The convex hull is stretched to a middle height of 64cm, a width of 52.7cm, and an angle of 12 degrees on both sides of the sheet;

[0025] Step 7, five stretches:

[0026] The convex hull is stretched to a maximum of R470 and a minimum of R390. The middle transition is a spline curve according to the coordinate points of the design drawing. The width is 52.7cm and the angles on both sides of the sheet are 14°43'32";

[0027] Step 8, second heat treatment:

[0028] Heat treating the workpiece in step 7 to remove the stress generated by forming;

[0029] Step 9, multi-piece molding:

[0030] The middle convex hull is used for positioning, and four single pieces are formed by bending and stretching on both sides of the convex hull.

[0031] Preferably, the aircraft engine mixer lobe multi-piece simultaneous molding process further comprises the following initial post-processing steps after the multi-piece molding process in step 9:

[0032] Step 10, cutting:

[0033] Cut the parts symmetrically in half, so that each half consists of two separate pieces;

[0034] Step 11, Flanging:

[0035] Flip up the flange edges on both sides of the part;

[0036] Step 12, leveling:

[0037] Correct the deformation of the parts from previous processes.

[0038] Preferably, after the leveling process in step 12, negative angle processing is performed, and the steps are as follows:

[0039] Step 13, negative angle flanging:

[0040] Negative angle of the formed flange edge;

[0041] Step 14, negative angle molding:

[0042] A negative angle formed when joining two separate parts.

[0043] Preferably, the workpiece after negative angle treatment is subjected to secondary post-processing, the steps are as follows:

[0044] Step 15, rib pressing:

[0045] Press the ribs on both sides of the parts;

[0046] Step 16, Reshaping:

[0047] Overall part calibration to ensure part profile and size requirements;

[0048] Step 17, cutting edges:

[0049] Cut off the excess material around the parts;

[0050] Step 18, Inspection:

[0051] The products in step 17 are inspected and qualified products are put into storage.

[0052] The present invention has at least the following beneficial effects:

[0053] The present invention provides a process for simultaneously forming multiple pieces of aircraft engine mixer lobes. After the multiple pieces are formed, 12 pieces are welded into a circular ring. There are 12 welds, which reduces 12 welds. Thus, welding deformation is controlled and the inner and outer duct airflows are fully mixed. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] Figure 1 This is a product diagram of the present invention after one-time stretching treatment;

[0055] Figure 2 This is a product diagram of the secondary stretching process of the present invention;

[0056] Figure 3 This is a product diagram of the first heat treatment of the present invention;

[0057] Figure 4 This is a picture of a product subjected to three-time stretching treatment of the present invention;

[0058] Figure 5 This is a product diagram of the present invention after four stretching treatments;

[0059] Figure 6 This is a picture of a product subjected to five stretching treatments of the present invention;

[0060] Figure 7 This is a product diagram of the second heat treatment of the present invention;

[0061] Figure 8 This is a product diagram of the multi-piece molding process of the present invention;

[0062] Fig. 9 Product diagram for cutting and processing of the present invention;

[0063] Fig.10 This is a product diagram of the flanging process of the present invention;

[0064] Fig.11 A product image of the leveling process of the present invention;

[0065] Fig.12 This is a product diagram of the negative angle flanging process of the present invention;

[0066] Fig.13 This is a product diagram of the negative angle forming process of the present invention;

[0067] Fig.14 This is a product diagram of the present invention subjected to rib pressing treatment;

[0068] Fig.15 This is a product image of the plastic surgery process of the present invention;

[0069] Fig.16 This is a product image of the trimming process of the present invention;

[0070] Fig.17This is a product picture after inspection of the present invention. DETAILED DESCRIPTION

[0071] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0072] Example

[0073] A process for simultaneously molding multiple pieces of mixer lobes of an aero-engine, comprising the following steps:

[0074] Step 1, cutting:

[0075] Placing the workpiece on the mold;

[0076] Step 2, one stretch:

[0077] The sheet is stretched into a convex shape, such as Figure 1 As shown, a convex hull is formed, the middle height is 16cm, the width is 52.7cm, and the angles on both sides of the sheet are 3 degrees;

[0078] Step 3, secondary stretching:

[0079] The convex hull is stretched into a convexity with a middle height of 32cm, a width of 52.7cm, and an angle of 6 degrees on both sides of the sheet, such as Figure 2 As shown;

[0080] Step 4, first heat treatment:

[0081] The workpiece in step 2 is heat treated to remove the stress caused by forming, such as Figure 3 As shown;

[0082] Step 5, three stretches:

[0083] The convex hull is stretched into a convexity with a middle height of 48cm, a width of 52.7cm, and an angle of 9 degrees on both sides of the sheet, such as Figure 4 As shown;

[0084] Step 6, four stretches:

[0085] The convex hull is stretched to a middle height of 64cm, a width of 52.7cm, and an angle of 12 degrees on both sides of the sheet. Figure 5 As shown;

[0086] Step 7, five stretches:

[0087] The convex hull is stretched to a maximum of R470 and a minimum of R390. The intermediate transition is a spline curve of the coordinate points of the design drawing, with a width of 52.7cm and an angle of 14°43′32″ on both sides of the sheet. Figure 6 As shown;

[0088] Step 8, second heat treatment:

[0089] The workpiece in step 7 is heat treated to remove the stress caused by forming, such as Figure 7 As shown;

[0090] Step 9, multi-piece molding:

[0091] Position the middle convex hull and use the bending and stretching process on both sides of the convex hull to form four single pieces, such as Figure 8 As shown;

[0092] Step 10, cutting:

[0093] Cut the parts symmetrically in half, so that each half consists of two separate pieces. Fig. 9 As shown;

[0094] Step 11, Flanging:

[0095] Fold up the flange edges on both sides of the part. Fig.10 As shown;

[0096] Step 12, leveling:

[0097] Correct the deformation of the parts in previous processes, such as Fig.11 As shown;

[0098] Step 13, negative angle flanging:

[0099] Negative angle of the formed flange edge, such as Fig.12 As shown;

[0100] Step 14, negative angle molding:

[0101] The negative angle of the middle connection between two single parts is formed, such as Fig.13 As shown;

[0102] Step 15, rib pressing:

[0103] Press the ribs on both sides of the part, such as Fig.14 As shown;

[0104] Step 16, shaping:

[0105] Overall part calibration to ensure part profile and size requirements, such as Fig.15 As shown;

[0106] Step 17, cutting edges:

[0107] Excess material around the cut parts, such as Fig.16 As shown;

[0108] Step 18, Inspection:

[0109] Inspect the products in step 17 and put qualified products into storage. Fig.17 shown.

[0110] After the multi-piece forming is completed, 12 single pieces are welded into a circular ring with 12 welds. The number of welds is reduced by 12, the welding deformation is controlled, and the inner and outer duct airflows are fully mixed.

[0111] The above shows and describes the basic principles, main features and advantages of the present invention. It is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and that the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention.

[0112] 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 process for simultaneously molding multiple pieces of mixer lobes of an aircraft engine, characterized in that: The following steps are involved: Step 1, cutting: Placing the workpiece on the mold; Step 2, one stretch: The sheet is stretched into a convex shape to form a convex hull with a middle height of 16 cm, a width of 52.7 cm, and an angle of 3 degrees on both sides of the sheet; Step 3, secondary stretching: The convex hull is stretched into a convexity with a middle height of 32 cm, a width of 52.7 cm, and an angle of 6 degrees on both sides of the sheet; Step 4, first heat treatment: Heat treating the workpiece in step 2 to remove the stress generated by forming; Step 5, three stretches: The convex hull is stretched into a convexity with a middle height of 48 cm, a width of 52.7 cm, and an angle of 9 degrees on both sides of the sheet; Step 6, four stretches: The convex hull is stretched to a middle height of 64cm, a width of 52.7cm, and an angle of 12 degrees on both sides of the sheet; Step 7, five stretches: The convex hull is stretched to a maximum of R470 and a minimum of R390. The middle transition is a spline curve according to the coordinate points of the design drawing. The width is 52.7cm and the angles on both sides of the sheet are 14°43'32"; Step 8, second heat treatment: Heat treating the workpiece in step 7 to remove the stress generated by forming; Step 9, multi-piece molding: The middle convex hull is used for positioning, and four single pieces are formed by bending and stretching on both sides of the convex hull.

2. The process for simultaneously molding multiple pieces of mixer lobes of an aircraft engine according to claim 1, characterized in that: The aircraft engine mixer lobe multi-piece simultaneous molding process further includes the following initial post-processing steps after the multi-piece molding process in step 9: Step 10, cutting: Cut the parts symmetrically in half, so that each half consists of two separate pieces; Step 11, Flanging: Flip up the flange edges on both sides of the part; Step 12, leveling: Correct the deformation of the parts from previous processes.

3. A process for simultaneously molding multiple pieces of mixer lobes for an aircraft engine according to claim 2, characterized in that: After the leveling process in step 12, negative angle processing is performed, and the steps are as follows: Step 13, negative angle flanging: Negative angle of the formed flange edge; Step 14, negative angle molding: A negative angle formed when joining two separate parts.

4. A process for simultaneously molding multiple pieces of mixer lobes for an aircraft engine according to claim 3, characterized in that: The steps for secondary post-processing of the workpiece after negative angle processing are as follows: Step 15, rib pressing: Press the ribs on both sides of the parts; Step 16, shaping: Overall part calibration to ensure part profile and size requirements; Step 17, cutting edges: Cut off the excess material around the parts; Step 18, Inspection: The products in step 17 are inspected and qualified products are put into storage.

Images