Integral forming method of aero-engine stabilizer

Abstract

The invention discloses an integral forming method of an aero-engine stabilizer, which comprises the following steps of: drawing a whole plate for four times, and finally forming a first V-shaped section part, a second V-shaped section part, a third V-shaped section part and a fourth V-shaped section part of the stabilizer. Wherein a first V-shaped section part, a second V-shaped section part and a flange edge of the circumferential outer edge are obtained during the first-time deep drawing forming and the second-time deep drawing forming, meanwhile, an upwards-protruding part is formed on a plate to serve as a storage material, then a groove is formed in the upwards-protruding part through third-time deep drawing, the groove is cut into two parts, and the two parts are connected with the first-time deep drawing forming and the second-time deep drawing forming. And a third V-shaped section part and a fourth V-shaped section part are obtained through fourth-time deep drawing, finally, the flange edge is cut, the transfer arc connected with the flange edge is straightened, and then the straightened transfer arc is cut to obtain the final height and width of the V-shaped section. According to the method, the wall thickness is guaranteed while the shape precision of the stabilizer is guaranteed, the quality requirements for size and shape precision are met, the machining efficiency is greatly improved, and the machining cost is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aero-engine processing, and in particular relates to an integral forming method for an aero-engine stabilizer. Background Art

[0002] like Figure 1 As shown in the figure, it is a stabilizer for the high temperature hot end component of an aircraft engine, which is made of high temperature alloy sheet with a material thickness of 1.2±0.12, and local thinning to 1.0 is allowed. The stabilizer mainly consists of four parts, namely Figure 1 The first V-shaped cross-sectional portion 1, the second V-shaped cross-sectional portion 2, the third V-shaped cross-sectional portion 3 and the fourth V-shaped cross-sectional portion 4 in the part have a V-shaped cross-sectional shape (see the cross-sectional view) Figure 2 ), the V-groove height is H, and the bottom is an arc of R3.

[0003] Figure 1 In the embodiment, the first V-shaped cross-sectional portion 1 is an arc segment with Ra as the center of the V-shape, Figure 1 The second V-shaped cross-sectional portion 2, the third V-shaped cross-sectional portion 3, and the fourth V-shaped cross-sectional portion 4 are straight-arm V-shaped grooves connected to the first V-shaped cross-sectional portion 1 through an arc R1. The second V-shaped cross-sectional portion 2 and the third V-shaped cross-sectional portion 3 are respectively on the inner and outer wall sides of the first V-shaped cross-sectional portion 1, and their centers are on a straight line. The fourth V-shaped cross-sectional portion 4 is on the outer wall of the first V-shaped cross-sectional portion 1 and forms a certain angle with the third V-shaped cross-sectional portion 3. The five V-shaped ends of the first V-shaped cross-sectional portion 1, the second V-shaped cross-sectional portion 2, the third V-shaped cross-sectional portion 3, and the fourth V-shaped cross-sectional portion 4 are open. If the structure is formed as a whole, there will be serious wrinkles at the arc transition between the second V-shaped section part 2, the third V-shaped section part 3, the fourth V-shaped section part 4 and the first V-shaped section part 1, and there will be serious thinning or even cracks at the transition between the middle of the third V-shaped section part 3 and the fourth V-shaped section part 4 and the outer arc of the first V-shaped section part 1. There will be certain thinning at the transition between the other straight walls and the arc. For a long time, the processing of the stabilizer adopts the method of separately processing four parts and then welding them, and then overall correction is performed, which has a large number of welds, large overall deformation, low production efficiency and great processing difficulty.

[0004] Based on the above reasons, it is necessary to study a reasonable and feasible process method to achieve overall forming of parts, reduce the number of welds, improve work efficiency and ensure product quality. Summary of the invention

[0005] The present invention aims to provide an integral forming method for an aircraft engine stabilizer, so as to realize the integral forming of the stabilizer, ensure the shape accuracy and the wall thickness of the part, achieve and meet the quality requirements of the part size and shape accuracy, greatly improve the processing efficiency and reduce the processing cost of the part.

[0006] To achieve the above object, the present invention adopts the following technical solutions:

[0007] A method for integrally forming an aircraft engine stabilizer, wherein the stabilizer is mainly composed of a first V-shaped cross-sectional portion, a second V-shaped cross-sectional portion, a third V-shaped cross-sectional portion, and a fourth V-shaped cross-sectional portion, wherein the first V-shaped cross-sectional portion is in an arc shape, the second V-shaped cross-sectional portion, the third V-shaped cross-sectional portion, and the fourth V-shaped cross-sectional portion are in a straight line shape, and the second V-shaped cross-sectional portion is located on the arc-shaped concave side of the first V-shaped cross-sectional portion, and the third V-shaped cross-sectional portion and the fourth V-shaped cross-sectional portion are located on the arc-shaped convex side of the first V-shaped cross-sectional portion, and the centers of the second V-shaped cross-sectional portion and the third V-shaped cross-sectional portion are on a straight line, and both ends of the first V-shaped cross-sectional portion, the end of the second V-shaped cross-sectional portion, the end of the third V-shaped cross-sectional portion, and the end of the fourth V-shaped cross-sectional portion are all open structures, and the integral forming method comprises:

[0008] First, a whole sheet of sheet metal is deep drawn to obtain a deep-drawn blank with a circle of excess material along the circumferential edge. The deep-drawn blank has the following features:

[0009] The V-shaped cross-sectional feature and the circular arc feature of the first V-shaped cross-sectional portion;

[0010] The V-shaped cross-sectional features of the second V-shaped cross-sectional portion and the features distributed on the arc-shaped concave side of the first V-shaped cross-sectional portion;

[0011] A drawing area located on the convex side of the arc-shaped first V-shaped cross-section portion, wherein the top surface of the drawing area is convex upward along the arc length of the arc-shaped first V-shaped cross-section portion;

[0012] Both ends of the first V-shaped cross-sectional portion, the end of the second V-shaped cross-sectional portion and the end of the drawn region are all closed structures with inclined surfaces;

[0013] Then, the top surface of the aforementioned drawn area is first drawn to form a groove, the direction of the groove is opposite to the upward convex direction of the drawn area, and then the groove is cut open, and the drawing method is used again to obtain the V-shaped cross-sectional features of the third V-shaped cross-sectional part and the fourth V-shaped cross-sectional part respectively;

[0014] Finally, a circle of excess material is cut off along the circumferential edge, leaving a margin, and the closed structures at both ends of the first V-shaped cross-section, the closed structure at the end of the second V-shaped cross-section, the closed structure at the end of the third V-shaped cross-section, and the closed structure at the end of the fourth V-shaped cross-section are cut to obtain open features, and the edge margin after cutting off the excess material is straightened, and the straightened part is cut again to obtain the cross-sectional height and width required by the stabilizer part drawing.

[0015] Furthermore, the integral forming method of the aircraft engine stabilizer includes:

[0016] Step 1: Make a blank, unfold the stabilizer along the profile into a plane, and add a margin in the length and width directions of the first V-shaped cross-section part, the second V-shaped cross-section part, the third V-shaped cross-section part, and the fourth V-shaped cross-section part to form a blank before deep drawing;

[0017] Step 2: The first deep drawing process is to draw the blank into a structure with a circumferential flange, fully closed circumferentially, and a drawing height less than the final height H of the stabilizer, wherein the flange is transitioned through a transfer arc, and the structure includes the following features:

[0018] The V-shaped cross-sectional feature and the circular arc feature of the first V-shaped cross-sectional portion;

[0019] The V-shaped cross-sectional features of the second V-shaped cross-sectional portion and the features distributed on the arc-shaped concave side of the first V-shaped cross-sectional portion;

[0020] A drawing area located on the convex side of the arc-shaped first V-shaped cross-section portion, wherein the top surface of the drawing area is convex upward along the arc length of the arc-shaped first V-shaped cross-section portion;

[0021] bevel features at both ends of the first V-shaped cross-sectional portion, bevel features at the end of the second V-shaped cross-sectional portion, and bevel features at the end of the drawn region;

[0022] Step 3: Correct the corrugations to a smooth state, correct the corrugations at the transition arc R3 at the bottom of the corresponding V-shaped cross-section on the first V-shaped cross-section part and the second V-shaped cross-section part, the corrugations at the top arc of the upwardly protruding part of the drawing area, and the corrugations at the intersection of the transition arc R3 at the bottom of the V-shaped cross-section of the first V-shaped cross-section part, the transition arc R3 at the bottom of the V-shaped cross-section of the second V-shaped cross-section part, and the top arc of the upwardly protruding part of the drawing area;

[0023] Step 4: Heat treatment to remove the forming stress of the first deep drawing;

[0024] Step 5: The second deep drawing is performed, and the drawing height is enlarged on the basis of the first deep drawing, and the rest of the parts except the upward protruding part of the drawing area are drawn to the final height H of the stabilizer, and the maximum height of the upward protruding part of the drawing area is H+H2, H2>0;

[0025] Step 6: The third deep drawing is performed, based on the second deep drawing, the upward convex part of the drawn area is reversely drawn to obtain a groove, thereby dividing the drawn area into two parts corresponding to the third V-shaped cross-section part and the fourth V-shaped cross-section part, and the reverse drawing height is less than the final height H of the stabilizer;

[0026] Step 7: Heat treatment to remove the forming stress of the third deep drawing;

[0027] Step 8: cutting the groove, opening a hole in the middle of the groove obtained in step 6 and close to the first V-shaped cross-sectional portion, and then using the hole as a starting point, cutting the groove in a direction away from the first V-shaped cross-sectional portion, with two sides of the cutting line being respectively used to form two parts of the third V-shaped cross-sectional portion and the fourth V-shaped cross-sectional portion;

[0028] Step 9: The fourth deep drawing is performed on two parts on both sides of the cutting line, which are used to form the third V-shaped cross-section part and the fourth V-shaped cross-section part respectively, until the final height H of the stabilizer is reached. The third V-shaped cross-section part and the fourth V-shaped cross-section part obtained by deep drawing have flange edges, and the flange edges are transitioned through a transfer arc;

[0029] Step 10: cutting the flange edge, retaining the transition arc, and cutting off the flange edge obtained in step 2 and step 9, and cutting along the transition arc between the flange edge and the first V-shaped cross-section part, the second V-shaped cross-section part, the third V-shaped cross-section part, and the fourth V-shaped cross-section part close to the flange edge;

[0030] Step 11: Correcting the cross-sectional dimensions, correcting the overall profile of the stabilizer so that the transfer arc retained in step 10 is straightened, and ensuring that the cross-sectional height dimensions and cross-sectional width dimensions of the first V-shaped cross-sectional portion, the second V-shaped cross-sectional portion, the third V-shaped cross-sectional portion, and the fourth V-shaped cross-sectional portion after correction are greater than the cross-sectional height dimension H and the cross-sectional width dimension L required in the stabilizer part drawing;

[0031] Step 12: Cut the shape of the stabilizer, remove the section height dimension allowance and section width dimension allowance of the first V-shaped section part, the second V-shaped section part, the third V-shaped section part and the fourth V-shaped section part, and obtain the section height dimension H and section width dimension L required in the stabilizer part drawing.

[0032] As a solution, in step 2, nitrocellulose lacquer is sprayed on the surface of the blank before the first deep drawing for protection and lubrication.

[0033] As a solution, in step three, correction is performed by manual hammering.

[0034] As a scheme, in the step five, the upward protruding part of the drawing area is used as storage material for subsequent drawing and forming, and the method for determining the height H2 is: flattening the cross-sectional contour lines of the third V-shaped cross-sectional part and the fourth V-shaped cross-sectional part into a straight line segment respectively, and then expanding the line length of the two straight line segments obtained to no more than 1.2 times the original length, connecting the two straight line segments with the expanded line length with the spacing length line segment of the third V-shaped cross-sectional part and the fourth V-shaped cross-sectional part to obtain a broken line segment, and then connecting the two end points of the broken line segment with a circular arc curve, and taking the maximum chord height of the circular arc curve as H2.

[0035] As a solution, in step six, the inner surface obtained by the second deep drawing in step five is used as the positioning surface to form the groove by deep drawing.

[0036] As a solution, in step eight, the edges of the holes after opening are rounded before cutting.

[0037] As a solution, a five-axis laser cutting machine is used for cutting in steps eight, ten and twelve.

[0038] The present invention proposes an integral forming method for an aircraft engine stabilizer, converting an open structure into a fully enclosed deep drawing structure, adopting a reasonable intermediate process shape to achieve sufficient material storage, and realizing the integral forming of a special-shaped stabilizer through a full deep drawing method, while ensuring that the local thinning of the parts meets the requirement of no more than 12.5%, greatly improving the processing efficiency and the quality and performance of the parts. At present, the processing method of the present invention has been used on site and has achieved the purpose and requirements of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 This is the main view of the stabilizer;

[0040] Figure 2 It is the cross-sectional view of stabilizer CC, BB, and FF;

[0041] Figure 3 It is the outline drawing of the blank after the first and second deep drawing;

[0042] Figure 4 yes Figure 3 AA section view of the middle blank;

[0043] Figure 5 This is the appearance of the blank after the third deep drawing;

[0044] Figure 6 After the fourth deep drawing, Figure 5 AA section view at the middle groove;

[0045] Figure 7 It is a schematic diagram of the H2 determination method;

[0046] In the figure, 1 is a first V-shaped cross-sectional portion, 2 is a second V-shaped cross-sectional portion, 3 is a third V-shaped cross-sectional portion, and 4 is a fourth V-shaped cross-sectional portion. DETAILED DESCRIPTION

[0047] The present invention is further described below in conjunction with specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to common technical knowledge and customary means in the field are included in the scope of the present invention.

[0048] The present invention adopts the overall deep drawing to restrict the material flow and reduce the wrinkling to realize the external shape of the part, and the middle of the third V-shaped cross-section part 3 and the fourth V-shaped cross-section part 4 adopts the intermediate transition process shape of upward convexity for material storage, and then the two sides (i.e. Figure 1 The second V-shaped cross-sectional portion is formed by drawing the second V-shaped cross-sectional portion 3 and the second V-shaped cross-sectional portion 4 on two opposite sides thereof.

[0049] A method for processing an aircraft engine titanium alloy special-shaped wall comprises the following steps:

[0050] Step 1: Make a blank, unfold the stabilizer along the profile, increase (70-100) mm in length and width directions as the blank before deep drawing, the first V-shaped cross-section part 1, the second V-shaped cross-section part 2, the third V-shaped cross-section part 3, and the fourth V-shaped cross-section part 4 have V-shaped cross-sections, wherein the second V-shaped cross-section part 2, the third V-shaped cross-section part 3, and the fourth V-shaped cross-section part 4 are rectangular after being unfolded into a plane, and the first V-shaped cross-section part 1 is also rectangular after being flattened and straightened, and the length and width here refer to the length and width of the rectangle;

[0051] Step 2: The first pre-drawing is performed, and the shape after drawing is as follows Figure 3 The drawing height is 20-25mm. Before drawing, nitro varnish is sprayed on both sides of the blank for protection and lubrication. The drawing equipment is a hydraulic press. The shape after drawing is as follows: Figure 3 As shown in the figure, it is a fully enclosed structure with a flange edge on the circumferential outer edge. The flange edge is connected to the main body of the drawn part (the main body here refers to Figure 1 The first V-shaped cross-sectional portion 1, the second V-shaped cross-sectional portion 2, and the upwardly protruding deep-drawn portion for forming the third V-shaped cross-sectional portion 3 and the fourth V-shaped cross-sectional portion 4 are transitioned through a transition arc R, and the second V-shaped cross-sectional portion 2, the upwardly protruding deep-drawn portion for forming the third V-shaped cross-sectional portion 3 and the fourth V-shaped cross-sectional portion 4 and the first V-shaped cross-sectional portion 1 are all transitioned through a transition arc R2, and R2 is greater than Figure 1 R1 in the figure is flattened and convexed upwardly by an arc H2 at the middle of the corresponding forming positions of the third V-shaped cross-section part 3 and the fourth V-shaped cross-section part 4 as the storage material for subsequent forming. The method for determining the value of H2 is as follows: Figure 7 , take the two endpoints h and k in the broken line segment hijk as the chord, and make a circular arc curve connecting the endpoints h and k. The maximum chord height of the chord is H2. It should be noted that when determining the value of H2, Figure 3 The length of the line corresponding to the third V-shaped cross-sectional portion 3 and the fourth V-shaped cross-sectional portion 4 is equal to 1 to 1.2 times the length of the corresponding cross-sectional profile line of the third V-shaped cross-sectional portion 3 and the fourth V-shaped cross-sectional portion 4. Figure 7 The original endpoints h' and k' (line segment h'i and line segment jk' are respectively the third V-shaped cross-sectional portion 3 and the fourth V-shaped cross-sectional portion 4 are respectively Figure 2 The straight line segment obtained by flattening the middle section into a straight line) moves to the left and right to point h and point k respectively, passes through the arc curve to transfer point h and point k, and takes the chord height of the arc curve as H2; the transfer arc R2>10mm, the flange edge and the part body transfer arc R=(15-18)mm, and the V-shaped section ends of the first V-shaped section part 1, the second V-shaped section part 2, the third V-shaped section part 3, and the fourth V-shaped section part 4 are fully enclosed structures using a slope transfer at an angle of α;

[0052] Step 3: Manual correction, repair the first V-shaped section part 1 and the second V-shaped section part 2 Figure 2 The ripples at the transfer arc R3 and Figure 3 The corrugations at the top of the upwardly protruding part, as well as the corrugations at the intersection of the transition arc R3 at the bottom of the V-shaped section of the first V-shaped section 1, the transition arc R3 at the bottom of the V-shaped section of the second V-shaped section 2, and the arc at the top of the upwardly protruding part of the drawing area ensure smooth transition;

[0053] Step 4: Heat treatment to remove drawing stress;

[0054] Step 5: Second deep drawing, on the hydraulic press according to Figure 3 The shape is further drawn, and the drawing height H1 is 40mm;

[0055] Step 6: The third deep drawing process is carried out according to Figure 5 The shape is drawn. Figure 3 The upward convex part of the groove is obtained, wherein a pad is added under the drawing die to ensure that the drawing height of the groove is 20 to 24 mm. The third drawing forming is performed by Figure 3 The inner profile of the blank shown has been drawn, and the groove is formed by drawing. Figure 4 The convex arc corresponding to H2 in the middle presses down a groove with a depth of 20-24mm. It is required that there is no thinning and cracking. When drawing the groove, all flange edges of the blank are pressed tightly. The ejection force on a 4000KN press is (10-15)T;

[0056] Step 7: Heat treatment to remove drawing stress;

[0057] Step 8: Cut the groove. Use a five-axis laser cutting machine to cut a φ10 small hole in the middle of the groove (such as Figure 5The dotted line in the middle shows the small hole and the cutting line), the small hole is 15 mm away from the convex side of the first V-shaped cross-section part 1 and the transition point between the bottom of the groove and the arc of the groove side wall, the burrs on the hole edge are removed, the hole edge is polished and rounded, the surface roughness is not greater than Ra1.6, and the groove is cut in a straight line along the small hole away from the first V-shaped cross-section part 1;

[0058] Step 9: Deep drawing, deep drawing the parts to Figure 6 The height H of the part shown is 40mm, the drawing equipment is a 4000KN hydraulic press, the drawing pressure is (30~50)T, and the drawing rate is 0.05m / s;

[0059] Step 10: Cut the flange edge. The cutting equipment is a five-axis laser cutting machine. Cut the flange edge of the part along the connection between the flange edge and the transition arc R (the transition arc R has two connection points, one of which is connected to the flange edge, and the other is connected to the side of the V-shaped section of the first V-shaped section part 1, the second V-shaped section part 2, the third V-shaped section part 3, and the fourth V-shaped section part 4. When cutting, the connection point with the flange edge is used as the tangent point to retain the transition arc R). Retain the transition arc R, and at the same time, close the two ends of the first V-shaped section part 1, the end of the second V-shaped section part 2, the end of the third V-shaped section part 3, and the end of the fourth V-shaped section part 4 (corresponding to Figure 4 The middle α angle hypotenuse) is cut into an open structure;

[0060] Step 11: Correct the transition arc R to a straight wall (i.e. straighten the transition arc to be collinear with the side of the V-shaped section), correct the overall profile of the part, and ensure that the section height and section width of the V-shaped section of the first V-shaped section part 1, the second V-shaped section part 2, the third V-shaped section part 3, and the fourth V-shaped section part 4 are greater than Figure 2 Height dimension H (40 mm) and width dimension L (33 mm) shown;

[0061] Step 12: Cut the straight wall. The cutting equipment is a five-axis laser cutting machine. Cut the part shape to ensure that the height dimension H = 40 ± 0.2mm and the width dimension L = 33 ± 0.35mm of the V-shaped section.

[0062] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in the field. Although the illustrative specific embodiments of the present invention are described above to facilitate the understanding of the present invention by the technical personnel in the field, it should be clear that the present invention is not limited to the scope of the specific embodiments. For the ordinary technical personnel in the field, as long as various changes are within the spirit and scope of the present invention defined and determined by the attached claims, these changes are obvious, and all inventions and creations using the concept of the present invention are protected.

Claims

1. A method for integrally forming an aircraft engine stabilizer, wherein the stabilizer mainly consists of a first V-shaped cross-sectional portion (1), a second V-shaped cross-sectional portion (2), a third V-shaped cross-sectional portion (3), and a fourth V-shaped cross-sectional portion (4), wherein the first V-shaped cross-sectional portion (1) is in an arc shape, the second V-shaped cross-sectional portion (2), the third V-shaped cross-sectional portion (3), and the fourth V-shaped cross-sectional portion (4) are in a straight line shape, and the second V-shaped cross-sectional portion (2) is located on the arc-shaped concave side of the first V-shaped cross-sectional portion (1), and the third V-shaped cross-sectional portion (3) and the fourth V-shaped cross-sectional portion (4) are located on the arc-shaped convex side of the first V-shaped cross-sectional portion (1), the centers of the second V-shaped cross-sectional portion (2) and the third V-shaped cross-sectional portion (3) are on a straight line, and both ends of the first V-shaped cross-sectional portion (1), the end of the second V-shaped cross-sectional portion (2), the end of the third V-shaped cross-sectional portion (3), and the end of the fourth V-shaped cross-sectional portion (4) are all open structures, characterized in that: The overall forming method includes: First, a whole sheet of sheet metal is used for overall deep drawing to obtain a deep-drawn blank with a circle of excess material along the circumferential edge. The deep-drawn blank includes the following features: The V-shaped cross-sectional features and the circular arc features of the first V-shaped cross-sectional portion (1); The V-shaped cross-sectional features of the second V-shaped cross-sectional portion (2) and the features distributed on the arc-shaped concave side of the first V-shaped cross-sectional portion (1); A deep drawing area located on the convex side of the circular arc of the first V-shaped cross-section portion (1), wherein the top surface of the deep drawing area is in an upward convex state along the arc length of the circular arc of the first V-shaped cross-section portion (1); Both ends of the first V-shaped cross-section portion (1), the end of the second V-shaped cross-section portion (2) and the end of the drawn area are all closed structures with inclined surfaces; Then, the top surface of the aforementioned drawn area is first drawn to form a groove, the direction of the groove being opposite to the upward convex direction of the drawn area, and then the groove is cut open, and the drawing method is used again to obtain the V-shaped cross-sectional features of the third V-shaped cross-sectional part (3) and the fourth V-shaped cross-sectional part (4), respectively; Finally, a circle of excess material on the circumferential edge is cut off and a margin is left, and the closed structures at both ends of the first V-shaped cross-section part (1), the closed structure at the end of the second V-shaped cross-section part (2), the closed structure at the end of the third V-shaped cross-section part (3) and the closed structure at the end of the fourth V-shaped cross-section part (4) are cut to obtain open features, and the edge margin after cutting off the excess material is straightened, and the straightened part is cut again to obtain the cross-sectional height and width required by the stabilizer part drawing.

2. The method for integrally forming an aircraft engine stabilizer according to claim 1, characterized in that: include: Step 1: Making a blank, unfolding the stabilizer along the profile into a plane, and increasing a margin in the length and width directions of the first V-shaped cross-section portion (1), the second V-shaped cross-section portion (2), the third V-shaped cross-section portion (3), and the fourth V-shaped cross-section portion (4) to form a blank before deep drawing; Step 2: The first deep drawing process is to draw the blank into a structure with a circumferential flange, fully closed circumferentially, and a drawing height less than the final height H of the stabilizer, wherein the flange is transitioned through a transfer arc, and the structure includes the following features: The V-shaped cross-sectional features and the circular arc features of the first V-shaped cross-sectional portion (1); The V-shaped cross-sectional features of the second V-shaped cross-sectional portion (2) and the features distributed on the arc-shaped concave side of the first V-shaped cross-sectional portion (1); A deep drawing area located on the convex side of the circular arc of the first V-shaped cross-section portion (1), wherein the top surface of the deep drawing area is in an upward convex state along the arc length of the circular arc of the first V-shaped cross-section portion (1); Bevel features at both ends of the first V-shaped cross-sectional portion (1), bevel features at the end of the second V-shaped cross-sectional portion (2), and bevel features at the end of the drawn area; Step 3: Correct the corrugations to a smooth state, correct the corrugations at the transition arc R3 at the bottom of the corresponding V-shaped cross-section on the first V-shaped cross-section part (1) and the second V-shaped cross-section part (2), the corrugations at the top arc of the upwardly protruding part of the drawing area, and the corrugations at the intersection of the transition arc R3 at the bottom of the V-shaped cross-section of the first V-shaped cross-section part (1), the transition arc R3 at the bottom of the V-shaped cross-section of the second V-shaped cross-section part (2) and the top arc of the upwardly protruding part of the drawing area; Step 4: Heat treatment to remove the forming stress of the first deep drawing; Step 5: The second deep drawing is performed, and the drawing height is enlarged on the basis of the first deep drawing, and the rest of the parts except the upward protruding part of the drawing area are drawn to the final height H of the stabilizer, and the maximum height of the upward protruding part of the drawing area is H+H2, H2>0; Step 6: The third deep drawing is performed, based on the second deep drawing, the upward convex part of the drawn area is reversely drawn to obtain a groove, thereby dividing the drawn area into two parts corresponding to the third V-shaped cross-section part (3) and the fourth V-shaped cross-section part (4), and the reverse drawing height is less than the final height H of the stabilizer; Step 7: Heat treatment to remove the forming stress of the third deep drawing; Step 8: cutting the groove, a hole is opened in the middle of the groove obtained in step 6 and close to the first V-shaped cross-sectional portion (1), and then the groove is cut away from the first V-shaped cross-sectional portion (1) with the hole as the starting point, and two sides of the cutting line are respectively used to form two parts of the third V-shaped cross-sectional portion (3) and the fourth V-shaped cross-sectional portion (4); Step 9: The fourth deep drawing is performed on two parts on both sides of the cutting line, which are used to form the third V-shaped cross-sectional part (3) and the fourth V-shaped cross-sectional part (4), until the final height H of the stabilizer is reached. The third V-shaped cross-sectional part (3) and the fourth V-shaped cross-sectional part (4) obtained by deep drawing have flange edges, and the flange edges are transitioned through a transition arc. Step 10: cutting the flange edge, retaining the transition arc, and cutting off the flange edge obtained in step 2 and step 9, and cutting along the transition arc between the flange edge and the first V-shaped cross-sectional portion (1), the second V-shaped cross-sectional portion (2), the third V-shaped cross-sectional portion (3), and the fourth V-shaped cross-sectional portion (4) close to the flange edge; Step 11: Correcting the cross-sectional dimensions, correcting the overall profile of the stabilizer so that the transition arc retained in step 10 is straightened, and ensuring that the cross-sectional height dimension and cross-sectional width dimension of the first V-shaped cross-sectional portion (1), the second V-shaped cross-sectional portion (2), the third V-shaped cross-sectional portion (3) and the fourth V-shaped cross-sectional portion (4) after correction are greater than the cross-sectional height dimension H and the cross-sectional width dimension L required in the stabilizer parts drawing; Step 12: Cut the shape of the stabilizer, remove the cross-sectional height dimension allowance and cross-sectional width dimension allowance of the first V-shaped cross-sectional portion (1), the second V-shaped cross-sectional portion (2), the third V-shaped cross-sectional portion (3) and the fourth V-shaped cross-sectional portion (4), and obtain the cross-sectional height dimension H and cross-sectional width dimension L required in the stabilizer part drawing.

3. The method for integrally forming an aircraft engine stabilizer according to claim 2, characterized in that: In the step 2, nitrocellulose varnish is sprayed on the surface of the blank before the first deep drawing for protection and lubrication.

4. The method for integrally forming an aircraft engine stabilizer according to claim 2, characterized in that: In the step three, manual repair is used for correction.

5. The method for integrally forming an aircraft engine stabilizer according to claim 2, characterized in that: In step five, the upwardly protruding portion of the drawing area is used as a storage material for subsequent drawing and forming, wherein the height H2 is determined by: flattening the cross-sectional contour lines of the third V-shaped cross-sectional part (3) and the fourth V-shaped cross-sectional part (4) into a straight line segment respectively, and then expanding the line length of the two straight line segments obtained to no more than 1.2 times the original length, connecting the two straight line segments with the distance length of the third V-shaped cross-sectional part (3) and the fourth V-shaped cross-sectional part (4) to obtain a broken line segment, and then connecting the two end points of the broken line segment with a circular arc curve, and taking the maximum chord height of the circular arc curve as H2.

6. The method for integrally forming an aircraft engine stabilizer according to claim 2, characterized in that: In the step six, the inner surface obtained by the second deep drawing in the step five is used as the positioning surface to form the groove by deep drawing.

7. The method for integrally forming an aircraft engine stabilizer according to claim 2, characterized in that: In the step eight, the edges of the holes after opening are rounded before cutting.

8. The method for integrally forming an aircraft engine stabilizer according to claim 2, characterized in that: In the steps eight, ten and twelve, a five-axis laser cutting machine is used for cutting.

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