Integral forming method of aircraft engine stabilizer

Abstract

The present invention discloses a method for integrally forming an aircraft engine stabilizer. The method uses a single sheet of sheet metal and performs four deep drawing operations to form the stabilizer's first, second, third, and fourth V-shaped cross-sections. The first and second deep drawing operations produce the first and second V-shaped cross-sections, as well as a flange along the circumferential outer edge. A raised portion is formed on the sheet metal as a material reservoir. A third deep drawing operation forms a groove at the raised portion, which is then split into two sections. A fourth deep drawing operation produces the third and fourth V-shaped cross-sections. Finally, the flange is cut, and the transition arc connected to the flange is straightened. The straightened transition arc is then cut to obtain the final V-shaped cross-section height and width. This method maintains both the shape accuracy of the stabilizer and the wall thickness, meeting and satisfying quality requirements for dimensional and shape accuracy, significantly improving processing efficiency and reducing processing costs.

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 The figure shows 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, the cross-sectional shape of the part is V-shaped (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-section 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, with their centers 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 cross-section part 2, the third V-shaped cross-section part 3, the fourth V-shaped cross-section part 4 and the first V-shaped cross-section part 1, and there will be serious thinning or even cracks at the transition between the middle of the third V-shaped cross-section part 3 and the fourth V-shaped cross-section part 4 and the outer arc of the first V-shaped cross-section part 1. There will be a certain thinning at the transition between the other straight walls and the arc. For a long time, the processing of this stabilizer has adopted the method of separately processing four parts and then welding them, and then performing overall shape correction. There are many 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 the 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 a method for integrally forming an aircraft engine stabilizer, thereby realizing the integral forming of the stabilizer, ensuring the shape accuracy while ensuring the wall thickness of the part, achieving and meeting the quality requirements of the part size and shape accuracy, greatly improving the processing efficiency, and reducing 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 mainly consists 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 arc-shaped, and the second V-shaped cross-sectional portion, the third V-shaped cross-sectional portion, and the fourth V-shaped cross-sectional portion are linear, and the second V-shaped cross-sectional portion is located on the concave side of the arc 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 convex side of the arc of the first V-shaped cross-sectional portion, 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. The integral forming method comprises:

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

[0009] V-shaped cross-sectional features and arc-shaped features of the first V-shaped cross-sectional portion;

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

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

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

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

[0014] Finally, a circle of excess material is cut off along the circumferential edge, leaving a margin. 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. 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. Expand the stabilizer into a plane along the mold surface. For 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, a certain margin is added in the length and width directions 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 enclosed circumferentially, and a drawing height less than the final height H of the stabilizer. The flange is transitioned through a transition arc. The structure includes the following features:

[0018] V-shaped cross-sectional features and arc-shaped features of the first V-shaped cross-sectional portion;

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

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

[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, correcting the corrugations at the transition arc R3 at the bottom of the V-shaped cross-section on the first V-shaped cross-section portion and the second V-shaped cross-section portion, the corrugations at the top arc of the upwardly convex portion of the drawn 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 portion, the transition arc R3 at the bottom of the V-shaped cross-section of the second V-shaped cross-section portion, and the top arc of the upwardly convex portion of the drawn 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. The drawing height is expanded on the basis of the first deep drawing. The rest of the parts except the upward convex part of the drawn area are drawn to the final height H of the stabilizer. The maximum height of the upward convex part of the drawn area is H+H2, and H2>0.

[0025] Step 6: The third deep drawing is performed. Based on the second deep drawing, the upward convex portion of the drawn area is reversely drawn to form 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. 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: a hole is opened in the middle of the groove obtained in step 6 and close to the first V-shaped cross-section. Then, starting from the hole, the groove is cut in a direction away from the first V-shaped cross-section. Two parts on both sides of the cutting line are respectively used to form the third V-shaped cross-section and the fourth V-shaped cross-section.

[0028] Step 9: The fourth deep drawing is performed on the 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 transition arc;

[0029] Step 10: Cut the flange edge, retain the transition arc, and cut off the flange edge obtained in step 2 and step 9. When cutting, cut along the transition arc between the flange edge and the first V-shaped cross-section portion, the second V-shaped cross-section portion, the third V-shaped cross-section portion, and the fourth V-shaped cross-section portion, close to the flange edge.

[0030] Step 11: Correct the cross-sectional dimensions. Correct the overall profile of the stabilizer so that the transition arc retained in step 10 is straightened. Ensure that the cross-sectional height and cross-sectional width 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 H and cross-sectional width L required in the stabilizer parts drawing.

[0031] 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 part, the second V-shaped cross-sectional part, the third V-shaped cross-sectional part and the fourth V-shaped cross-sectional part, and obtain the cross-sectional height dimension H and cross-sectional 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, manual hammering is used for correction.

[0034] As a solution, in step five, the upward protruding portion of the drawing area is used as storage material for subsequent drawing and forming, and the height H2 is determined by 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 hole 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] This invention proposes a method for integrally forming aircraft engine stabilizers. This method converts an open structure into a fully enclosed, deep-drawn structure, employing appropriate intermediate process shapes to ensure sufficient material storage. Through a fully deep-drawn process, the integral forming of the special-shaped stabilizer is achieved. This method significantly improves processing efficiency, part quality, and performance while ensuring that localized thinning of the part does not exceed 12.5%. The method is currently in field use and has achieved its objectives and requirements. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

[0041] Figure 3 It is the outline 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 outline of the blank after the third deep drawing;

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

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

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

[0047] The present invention is further described below with reference to specific embodiments. However, 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 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 of the third V-shaped cross-section part 3 and the fourth V-shaped cross-section part 4 (i.e. Figure 1 The two opposite side surfaces between the third V-shaped cross-sectional portion 3 and the fourth V-shaped cross-sectional portion 4 are drawn out.

[0049] A method for processing a titanium alloy special-shaped wall of an aerospace engine, comprising the following steps:

[0050] Step 1: Prepare a blank. Expand the stabilizer along the profile and increase the length and width by (70-100) mm to form the blank before deep drawing. The cross-sections 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 are V-shaped. 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 are rectangular when expanded into a plane. The first V-shaped cross-section portion 1 is also rectangular when flattened and straightened. The length and width here refer to the length and width of the rectangle.

[0051] Step 2: The first pre-drawing is done, 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, 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 convex drawn portion for forming the third V-shaped cross-sectional portion 3 and the fourth V-shaped cross-sectional portion 4 are transitioned by a transition arc R, and the second V-shaped cross-sectional portion 2, the upwardly convex 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 by a transition arc R2, and R2 is greater than Figure 1 In the R1, the corresponding third V-shaped cross-section portion 3 and the fourth V-shaped cross-section portion 4 are flattened and convex upward in an arc shape H2 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-section part 3 and the fourth V-shaped cross-section part 4 is equal to 1 to 1.2 times the length of the corresponding cross-section profile line of the third V-shaped cross-section part 3 and the fourth V-shaped cross-section part 4. Figure 7 The original endpoints h' and k' (line segments h'i and jk' are respectively the third V-shaped cross-section portion 3 and the fourth V-shaped cross-section portion 4 are respectively Figure 2 The straight line segment obtained by flattening the middle section into a straight line is moved to the left and right to point h and point k respectively, and the arc curve is used to transfer points h and k, and the chord height of the arc curve is taken as H2; the transfer arc R2 is greater than 10mm, the transfer arc R between the flange edge and the part body is (15-18)mm, and the V-shaped cross-section ends of 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 are fully enclosed structures using an inclined plane transfer at an angle α;

[0052] Step 3: Manual correction, knock and 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 corrugation at the top of the upward convex part, as well as the corrugation 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 arc at the top of the upward convex part of the drawn 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 is carried out according to Figure 5 The shape is drawn, Figure 3 The upward convex part is used to obtain the groove, wherein the drawing height of the groove is ensured to be 20 to 24 mm by adding a pad under the drawing die. 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 to 24 mm. It is required that there is no thinning or cracking. When drawing the groove, all flange edges of the blank are pressed tightly. The ejection force on a 4000KN press is (10 to 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 portion 1 and the tangent point of the arc transition between the groove bottom and the groove sidewall. The burrs on the hole edge are removed and the hole edge is polished and chamfered. The surface roughness is not greater than Ra1.6. The groove is cut in a straight line along the small hole away from the first V-shaped cross-section portion 1.

[0058] Step 9: Deep drawing, deep drawing the part to Figure 6 The height H of the part shown is 40 mm, the drawing equipment is a 4000 KN hydraulic press, the drawing pressure is (30-50) T, and the drawing rate is 0.05 m / 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 structure of 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 cut at the hypotenuse of the middle α angle is 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 surface 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 (40mm) and width dimension L (33mm) 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 ± 0.2 mm and the width dimension L = 33 ± 0.35 mm of the V-shaped section.

[0062] Any matters not described in detail in the present specification are prior art known to those skilled in the art. Although the above description of the present invention is based on illustrative embodiments to facilitate understanding of the present invention by those skilled in the art, it should be understood that the present invention is not limited to the scope of the specific embodiments. As long as various modifications are within the spirit and scope of the present invention as defined and determined by the appended claims, such modifications will be obvious to those skilled in the art, and all inventions and creations utilizing the concepts 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 concave side of the arc shape 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 convex side of the arc shape 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: Integral forming methods include: First, a whole sheet of sheet metal is deep-drawn to obtain a drawn blank with a circle of excess material along the circumferential edge. The drawn blank has the following features: The first V-shaped cross-sectional feature (1) has a V-shaped cross-sectional feature and a circular arc feature; 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 portion (3) and the fourth V-shaped cross-sectional portion (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-section 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 into a plane along the profile, and adding 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 enclosed circumferentially, and a drawing height less than the final height H of the stabilizer. The flange is transitioned through a transition arc. The structure includes the following features: The first V-shaped cross-sectional feature (1) has a V-shaped cross-sectional feature and a circular arc feature; 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 convex part of the drawn 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 convex part of the drawn area; Step 4: Heat treatment to remove the forming stress of the first deep drawing; Step 5: The second deep drawing is performed. The drawing height is expanded on the basis of the first deep drawing. The rest of the parts except the upward convex part of the drawn area are drawn to the final height H of the stabilizer. The maximum height of the upward convex part of the drawn area is H+H2, and 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, opening a hole in the middle of the groove obtained in step 6 and close to the first V-shaped cross-sectional portion (1), and then using the hole as a starting point, cutting the groove in a direction away from the first V-shaped cross-sectional portion (1), with the two sides of the cutting line forming two parts for forming the third V-shaped cross-sectional portion (3) and the fourth V-shaped cross-sectional portion (4); Step nine: the fourth deep drawing process, wherein the 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), are deep drawn 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: Cut the flange edge, retain the transition arc, and cut off the flange edge obtained in step 2 and step 9. When cutting, cut 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 end of the flange edge; Step 11: cross-sectional dimension correction, correcting the overall profile of the stabilizer so that the transition arc retained in step 10 is straightened, 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 cross-sectional width dimension L required in the stabilizer parts drawing; Step 12: Cut the outer shape of the stabilizer, remove the cross-sectional height dimension allowance and cross-sectional width dimension allowance of the first V-shaped cross-sectional part (1), the second V-shaped cross-sectional part (2), the third V-shaped cross-sectional part (3) and the fourth V-shaped cross-sectional part (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 second step, 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 hammering is used for correction.

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