Composite forging method of T-shaped airfoil section part

Abstract

The invention discloses a composite forging method for a part with a T-shaped airfoil section. The composite forging method comprises the step that a blank is machined into the part with the airfoil section through two times of forging by using a forming tool. The forming tool comprises a pre-forming die, a forming die and an ejector head, the pre-forming die and the ejector head are used for machining in the first forging step, and the forming die and the ejector head are used for machining in the second forging step. According to the method, operation and use are easy and not complex, the forming speed is high, rapid batch production can be carried out by using a forming tool and two forging steps, the cost of raw materials, machining and manufacturing periods is reduced, and the method is a feasible forming method which is high in universality, conforms to the actual manufacturing environment and is convenient to popularize.

Description

Technical Field

[0001] The invention belongs to the technical field of mechanical manufacturing, and in particular relates to a composite forging method for a T-shaped wing section part. Background Art

[0002] A T-shaped cross-section part, characterized by its thin and long overall structure, is often used for embedded applications within certain devices. Due to the high volume of demand and the high volume of parts required, forging is the primary method for mass production of these parts. Given the high volume demand, unique shape, thin thickness, and variable length of these parts, the thin top transverse structure of these parts is prone to bending during machining. Conventional forging, where the forging blank size aligns with the part size, would be difficult to achieve in large quantities.

[0003] Conventional manufacturing methods primarily combine and splice parts based on their dimensional characteristics, then forge the parts as a whole into regular square-section forgings. Machining is then used to cut the integral forging into the desired part blank size, and finally, turning and milling are used to machine the parts to the required dimensions. This type of manufacturing method has the following drawbacks: First, it uses an "envelope" integral forging method for production, which results in high raw material consumption, high production costs, and difficulty in efficient manufacturing. Second, forgings produced using conventional forging methods require piece-by-piece sawing and large-allowance machining to obtain the final parts that meet the requirements. This process can easily lead to high processing stress, long production cycles, and unstable part quality. Therefore, it is necessary and meaningful to seek a new manufacturing solution that can save material consumption, promote rapid batch prototyping of such parts, reduce production cycles, improve part quality, and lower production costs.

[0004] Patent application CN115592058A discloses a method for forging L-shaped thin sheet metal forgings. This method requires a roll forging and drawing step, where the reduction in each pass must be precisely controlled to produce a T-shaped thin sheet metal blank. However, this method is not suitable for producing thinner parts with a large T-shaped top span, as the connection between the top and base of the T-shaped part formed by roll forging and drawing does not form a right angle.

[0005] Patent application CN117139535A discloses a method for forging six-way forgings, using a die, multiple forging passes, and heating to produce the forgings. The die has complex curved surfaces, resulting in high manufacturing costs. The second die pressing process requires the forging material to be placed on a vibrating machine for low-frequency vibration, which requires high vibration accuracy and can lead to increased processing costs. Summary of the Invention

[0006] In order to solve the above technical problems, the present invention provides a composite forging method for a T-shaped airfoil cross-section part.

[0007] The present invention is achieved through the following technical solutions.

[0008] The present invention provides a composite forging method for a T-shaped airfoil cross-section part, comprising the steps of processing a blank into the airfoil cross-section part through two forgings using a forming tool.

[0009] Preferably, the forming tooling comprises a preforming die, a forming die and a plug; the preforming die and the plug are used for processing in the first forging step, and the forming die and the plug are used for processing in the second forging step.

[0010] Preferably, the preforming mold includes a first forming mold, a spacer block and a pressure head. The first forming mold is provided with a first cavity. The spacer block is placed at the bottom of the first cavity for sliding connection. The pressure head is placed at the top of the first cavity for sliding connection.

[0011] Preferably, the first mold cavity includes a lower mold cavity and an upper mold cavity, the lower mold cavity and the upper mold cavity are connected, the cross-section of the lower mold cavity is rectangular, the cross-section of the upper mold cavity is funnel-shaped, and the width of the upper mold cavity is greater than that of the upper mold cavity.

[0012] Preferably, the forming mold includes a second forming mold and a spacer block, the second forming mold is provided with a second cavity, and the spacer block is placed at the bottom of the second cavity and is slidably connected.

[0013] Preferably, a placement groove is provided on the top of the second molding die, the top of the second cavity is connected to the placement groove, and the width of the placement groove is greater than the width of the second cavity.

[0014] Preferably, the two forging steps include the following steps: S1: Place the spacer block and the blank into the first cavity in sequence, place the blank on the spacer block, place the ram on top of the blank, use the upper flat anvil attached to the hydraulic forging equipment to press the ram, and move it downward to apply pressure, causing the upper end of the blank to deform and fill the upper cavity of the first forming die to obtain a preformed blank, then turn the first forming die 180°, and use the ram to push the spacer block, preformed blank and ram out of the first forming die to complete the first forging; S2: Place the raising block and the preformed blank into the second cavity in sequence, place the preformed blank on the raising block, and perform the second forging. Use the upper flat anvil attached to the hydraulic forging equipment to press the top of the preformed blank so that the preformed blank fills the placement slot of the second forming die under the action of the flat anvil to obtain a forging. Then, the second forming die is turned 180°, and the raising block and the forging are ejected from the second forming die by a punch. The forging is post-processed to obtain an airfoil section part.

[0015] Preferably, in step S1, before placing the blank into the first cavity, the blank is heated to 900-1200° C. and then kept warm; In the step S2, before the preform is placed in the second cavity, the preform is heated to 900-1200° C. and then kept warm.

[0016] Preferably, the calculation formula for the holding time in step S1 is: t=η1×m×T The calculation formula for the holding time in step S2 is: t=η2×m×T In the formula: t is the calculated holding time, in min; η1 is the heat conductivity coefficient of the cold billet in the furnace, η2 is the heat conductivity coefficient of the hot billet in the furnace; T is the maximum effective cross-sectional thickness of the part, in mm; m is the heating coefficient, in min / mm.

[0017] Preferably, the heat conduction coefficient η1 of the cold billet in the furnace is 0.8-1, and the heat conduction coefficient η2 of the hot billet in the furnace is 0.3-0.6; and the heating coefficient is 0.7-0.9 min / mm.

[0018] The beneficial effects of the present invention are: The method of the present invention is simple to operate and uncomplicated, has a fast forming speed, and can be quickly mass-produced by using forming tooling and two forging steps. Due to the use of forming tooling, the utilization rate of raw materials in the forging process is high, which reduces the costs of raw materials, processing and manufacturing cycles. It is a practical forming method with strong versatility, conforming to the actual manufacturing environment, and easy to promote. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic structural diagram of the present invention before step S1 forging; Figure 2 This is a schematic diagram of the structure after forging in step S1 of the present invention; Figure 3 This is a schematic structural diagram of the present invention before step S2 forging; Figure 4 This is a schematic diagram of the structure after forging in step S2 of the present invention; Figure 5 It is a schematic structural diagram of the blank of the present invention; Figure 6 It is a schematic structural diagram of the preform of the present invention; Figure 7 It is a schematic structural diagram of the forging of the present invention; Figure 8 is a front view of the forging of the present invention; In the figure: 1-blank, 2-preformed blank, 3-forging, 4-airfoil section part, 5-first forming die, 51-first cavity, 52-lower cavity, 53-upper cavity, 6-second forming die, 61-second cavity, 62-placement groove, 7-press head, 8-spacer. DETAILED DESCRIPTION

[0020] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0021] Example 1: like Figures 1 to 8 As shown, a composite forging method for a T-shaped airfoil section part includes the steps of processing a plate blank 1 into an airfoil section part through two forging steps using a forming tool.

[0022] The forming tooling comprises a preforming die, a forming die and a plug. The preforming die and the plug are used for processing in the first forging step, and the forming die and the plug are used for processing in the second forging step.

[0023] The preforming mold includes a first forming mold 5, a padding block 8 and a pressing head 7. A first cavity 51 is provided on the first forming mold 5. The padding block 8 is placed at the bottom of the first cavity 51 for sliding connection. The pressing head 7 is placed at the top of the first cavity 51 for sliding connection.

[0024] The first die cavity 51 includes a lower die cavity 52 and an upper die cavity 53. The lower die cavity 52 and the upper die cavity 53 are connected. The cross-section of the lower die cavity 52 is rectangular, and the cross-section of the upper die cavity 53 is funnel-shaped. The width of the upper die cavity 53 is greater than that of the upper die cavity 53, so that the blank 1 can form a top with a larger width after being pressed, which is convenient for the next forging step.

[0025] The molding die includes a second molding die 6 and a spacer block 8 . The second molding die 6 is provided with a second cavity 61 . The spacer block 8 is placed at the bottom of the second cavity 61 and is slidably connected thereto.

[0026] A placement groove 62 is provided at the top of the second forming die 6. The top of the second cavity 61 is connected to the placement groove 62. The width of the placement groove 62 is greater than the width of the second cavity 61, allowing the formed blank 2 to be forged and pressed to form a T-shaped airfoil cross-section. The shape of the placement groove 62 can be customized to facilitate the formation of different angles at the junction between the top and the root of the T-shaped airfoil component.

[0027] The steps of the two forgings are: S1: Place the raising block 8 and the blank 1 into the first cavity 51 in sequence, place the blank 1 on the raising block 8, place the ram 7 on top of the blank 1, use the upper flat anvil attached to the hydraulic forging equipment to press the ram 7, and move it downward to apply pressure, so that the upper end of the blank 1 is deformed and fills the upper cavity 53 of the first forming die 5, thereby obtaining the preformed blank 2. Then, with the help of auxiliary equipment, the first forming die 5 is turned 180°, and the raising block 8, the preformed blank 2 and the ram 7 are ejected from the first forming die 5 by a ram, thus completing the first forging. S2: Place the raising block 8 and the preformed blank 2 into the second cavity 61 in sequence, place the preformed blank 2 on the raising block 8, and perform the second forging. Use the upper flat anvil attached to the hydraulic forging equipment to press the top of the preformed blank 2, so that the preformed blank 2 fills the placement groove 62 of the second forming die 6 under the action of the flat anvil to obtain the forging 3, and then use the auxiliary equipment to flip the second forming die 6 180°, and use the head to push the raising block 8 and the forging 3 out of the second forming die 6. After deburring and other post-processing steps, the forging 3 obtains the wing section part 4, which is a part with a T-shaped wing section.

[0028] In step S1, before the blank 1 is placed into the first cavity 51, the blank 1 is heated to 900°C and then kept warm to ensure the mechanical properties and grain size requirements of the part; In step S2 , before the preform 2 is placed into the second cavity 61 , the preform 2 is heated to 900° C. and then kept warm.

[0029] The calculation formula for the holding time in step S1 is: t=η1×m×T The calculation formula for the holding time in step S2 is: t=η2×m×T In the formula: t is the calculated holding time, in min; η1 is the heat conductivity coefficient of the cold billet in the furnace, η2 is the heat conductivity coefficient of the hot billet in the furnace; T is the maximum effective cross-sectional thickness of the part, in mm; m is the heating coefficient, in min / mm.

[0030] The heat conduction coefficient η1 in the cold billet furnace is taken as 0.8, and the heat conduction coefficient η2 in the hot billet furnace is taken as 0.3; the heating coefficient is calculated according to 0.7min / mm. The higher the requirements of the parts, the more reasonable the m value must be selected. For stainless steel parts with grain size requirements, the selection of the m value must be strictly controlled. If the holding time is too long, the grain size is likely to grow excessively.

[0031] Example 2: like Figures 1 to 8 As shown, a composite forging method for a T-shaped airfoil section part includes the steps of processing a plate blank 1 into an airfoil section part through two forging steps using a forming tool.

[0032] The forming tooling comprises a preforming die, a forming die and a plug. The preforming die and the plug are used for processing in the first forging step, and the forming die and the plug are used for processing in the second forging step.

[0033] The preforming mold includes a first forming mold 5, a padding block 8 and a pressing head 7. A first cavity 51 is provided on the first forming mold 5. The padding block 8 is placed at the bottom of the first cavity 51 for sliding connection. The pressing head 7 is placed at the top of the first cavity 51 for sliding connection.

[0034] The first die cavity 51 includes a lower die cavity 52 and an upper die cavity 53. The lower die cavity 52 and the upper die cavity 53 are connected. The cross-section of the lower die cavity 52 is rectangular, and the cross-section of the upper die cavity 53 is funnel-shaped. The width of the upper die cavity 53 is greater than that of the upper die cavity 53, so that the blank 1 can form a top with a larger width after being pressed, which is convenient for the next forging step.

[0035] The molding die includes a second molding die 6 and a spacer block 8 . The second molding die 6 is provided with a second cavity 61 . The spacer block 8 is placed at the bottom of the second cavity 61 and is slidably connected thereto.

[0036] A placement groove 62 is provided at the top of the second forming die 6. The top of the second cavity 61 is connected to the placement groove 62. The width of the placement groove 62 is greater than the width of the second cavity 61, allowing the formed blank 2 to be forged and pressed to form a T-shaped airfoil cross-section. The shape of the placement groove 62 can be customized to facilitate the formation of different angles at the junction between the top and the root of the T-shaped airfoil component.

[0037] The steps of the two forgings are: S1: Place the raising block 8 and the blank 1 into the first cavity 51 in sequence, place the blank 1 on the raising block 8, place the ram 7 on top of the blank 1, use the upper flat anvil attached to the hydraulic forging equipment to press the ram 7, and move it downward to apply pressure, so that the upper end of the blank 1 is deformed and fills the upper cavity 53 of the first forming die 5, thereby obtaining the preformed blank 2. Then, with the help of auxiliary equipment, the first forming die 5 is turned 180°, and the raising block 8, the preformed blank 2 and the ram 7 are ejected from the first forming die 5 by a ram, thus completing the first forging. S2: Place the raising block 8 and the preformed blank 2 into the second cavity 61 in sequence, place the preformed blank 2 on the raising block 8, and perform the second forging. Use the upper flat anvil attached to the hydraulic forging equipment to press the top of the preformed blank 2, so that the preformed blank 2 fills the placement groove 62 of the second forming die 6 under the action of the flat anvil to obtain the forging 3, and then use the auxiliary equipment to flip the second forming die 6 180°, and use the head to push the raising block 8 and the forging 3 out of the second forming die 6. After deburring and other post-processing steps, the forging 3 obtains the wing section part 4, which is a part with a T-shaped wing section.

[0038] In step S1, before the blank 1 is placed into the first cavity 51, the blank 1 is heated to 1200°C and then kept warm to ensure the mechanical properties and grain size requirements of the part; In step S2 , before the preform 2 is placed into the second cavity 61 , the preform 2 is heated to 1200° C. and then kept warm.

[0039] The calculation formula for the holding time in step S1 is: t=η1×m×T The calculation formula for the holding time in step S2 is: t=η2×m×T In the formula: t is the calculated holding time, in min; η1 is the heat conductivity coefficient of the cold billet in the furnace, η2 is the heat conductivity coefficient of the hot billet in the furnace; T is the maximum effective cross-sectional thickness of the part, in mm; m is the heating coefficient, in min / mm.

[0040] The heat conduction coefficient η1 in the cold billet furnace is taken as 1, and the heat conduction coefficient η2 in the hot billet furnace is taken as 0.6; the heating coefficient is calculated according to 0.9min / mm. The higher the requirements of the parts, the more reasonable the m value must be selected. For stainless steel parts with grain size, the selection of the m value must be strictly controlled. If the holding time is too long, the grain size is likely to grow excessively.

[0041] Example 3: like Figures 1 to 8 As shown, a composite forging method for a T-shaped airfoil section part includes the steps of processing a plate blank 1 into an airfoil section part through two forging steps using a forming tool.

[0042] The forming tooling comprises a preforming die, a forming die and a plug. The preforming die and the plug are used for processing in the first forging step, and the forming die and the plug are used for processing in the second forging step.

[0043] The preforming mold includes a first forming mold 5, a padding block 8 and a pressing head 7. A first cavity 51 is provided on the first forming mold 5. The padding block 8 is placed at the bottom of the first cavity 51 for sliding connection. The pressing head 7 is placed at the top of the first cavity 51 for sliding connection.

[0044] The first die cavity 51 includes a lower die cavity 52 and an upper die cavity 53. The lower die cavity 52 and the upper die cavity 53 are connected. The cross-section of the lower die cavity 52 is rectangular, and the cross-section of the upper die cavity 53 is funnel-shaped. The width of the upper die cavity 53 is greater than that of the upper die cavity 53, so that the blank 1 can form a top with a larger width after being pressed, which is convenient for the next forging step.

[0045] The molding die includes a second molding die 6 and a spacer block 8 . The second molding die 6 is provided with a second cavity 61 . The spacer block 8 is placed at the bottom of the second cavity 61 and is slidably connected thereto.

[0046] A placement groove 62 is provided at the top of the second forming die 6. The top of the second cavity 61 is connected to the placement groove 62. The width of the placement groove 62 is greater than the width of the second cavity 61, allowing the formed blank 2 to be forged and pressed to form a T-shaped airfoil cross-section. The shape of the placement groove 62 can be customized to facilitate the formation of different angles at the junction between the top and the root of the T-shaped airfoil component.

[0047] The steps of the two forgings are: S1: Place the raising block 8 and the blank 1 into the first cavity 51 in sequence, place the blank 1 on the raising block 8, place the ram 7 on top of the blank 1, use the upper flat anvil attached to the hydraulic forging equipment to press the ram 7, and move it downward to apply pressure, so that the upper end of the blank 1 is deformed and fills the upper cavity 53 of the first forming die 5, thereby obtaining the preformed blank 2. Then, with the help of auxiliary equipment, the first forming die 5 is turned 180°, and the raising block 8, the preformed blank 2 and the ram 7 are ejected from the first forming die 5 by a ram, thus completing the first forging. S2: Place the raising block 8 and the preformed blank 2 into the second cavity 61 in sequence, place the preformed blank 2 on the raising block 8, and perform the second forging. Use the upper flat anvil attached to the hydraulic forging equipment to press the top of the preformed blank 2, so that the preformed blank 2 fills the placement groove 62 of the second forming die 6 under the action of the flat anvil to obtain the forging 3, and then use the auxiliary equipment to flip the second forming die 6 180°, and use the head to push the raising block 8 and the forging 3 out of the second forming die 6. After deburring and other post-processing steps, the forging 3 obtains the wing section part 4, which is a part with a T-shaped wing section.

[0048] In step S1, before the blank 1 is placed into the first cavity 51, the blank 1 is heated to 1100°C and then kept warm to ensure the mechanical properties and grain size requirements of the part; In the step S2 , before the preform 2 is placed into the second cavity 61 , the preform 2 is heated to 1000° C. and then kept warm.

[0049] The calculation formula for the holding time in step S1 is: t=η1×m×T The calculation formula for the holding time in step S2 is: t=η2×m×T In the formula: t is the calculated holding time, in min; η1 is the heat conductivity coefficient of the cold billet in the furnace, η2 is the heat conductivity coefficient of the hot billet in the furnace; T is the maximum effective cross-sectional thickness of the part, in mm; m is the heating coefficient, in min / mm.

[0050] The heat conduction coefficient η1 in the cold billet furnace is taken as 0.6, and the heat conduction coefficient η2 in the hot billet furnace is taken as 0.4; the heating coefficient is calculated according to 0.8min / mm. The higher the requirements of the parts, the more reasonable the m value must be selected. For stainless steel parts with grain size requirements, the selection of the m value must be strictly controlled. If the holding time is too long, the grain size is likely to grow excessively.

[0051] In steps S1 and S2 of the embodiments 1-3, first, before the blank 1 is put into the mold, the preforming mold and the forming mold must be preheated to ensure that during the deformation process, the temperature difference between the part and the mold is too large, resulting in the part temperature not dropping too quickly due to heat transfer, thereby reducing the quality of the product; second, before the blank 1 is put into the mold, sufficient lubricating oil must be applied to the inner cavity of the mold, which is more conducive to the subsequent demolding of the part; third, after the preforming blank 2 is formed and demolded, the folds, pits or cracks on the upper cavity head of the part surface that may be formed due to improper operation must be cleaned and polished to avoid more folds or cracks in the final forging 3, which affects the quality of the part; fourth, during the forming process, deformation cannot continue after the final forging temperature is lower than 850°C to avoid product cracking due to too low temperature and too high deformation resistance.

[0052] Comparative Example 1: A composite forging method for a T-shaped airfoil cross-section part has the same steps as those in Example 3, except that in step S1 , heating is not performed before placing the part into the first cavity 51 .

[0053] Comparative Example 2: A composite forging method for a T-shaped airfoil cross-section part has the same steps as those in Example 3, except that in step S2 , heating is not performed before placing the part into the second cavity 61 .

[0054] Comparative Example 3: A composite forging method for a T-shaped airfoil section part, the steps are basically the same as those in Example 3, except that step S1 does not heat the part before placing it into the second cavity 51 , and step S2 does not heat the part before placing it into the second cavity 61 .

[0055] Parts made of 316L stainless steel were produced using the methods of Examples 1-3 and Comparative Examples 1-3. The wing surface thickness was set to 20 mm. Ten parts were taken from each group for mechanical property testing. The testing was carried out in accordance with GB / T 228.1-2021 "Room Temperature Tensile Test Method for Metallic Materials". The average values of each group are shown in the following table.

[0056] Group Tensile strength (MPa) Yield strength (MPa) Example 1 630 420 Example 2 655 410 Example 3 645 442 Comparative Example 1 570 397 Comparative Example 2 595 403 Comparative Example 3 487 310 As can be seen from the table above, the parts produced in Example 3 have better mechanical properties and can adapt to a wider range of working conditions. The data of Comparative Examples 1-3 show that the lack of a heating step or forging without heating has a significant impact on the mechanical properties of the forgings. The mechanical strength of the parts can be improved by heating treatment.

Claims

1. A composite forging method for a T-shaped airfoil cross-section part, characterized in that: The invention comprises the steps of processing a blank (1) into an airfoil section part by forging twice using a forming tool.

2. A composite forging method for a T-shaped airfoil cross-section part according to claim 1, characterized in that: The forming tooling comprises a preforming die, a forming die and a plug. The preforming die and the plug are used for processing in the first forging step, and the forming die and the plug are used for processing in the second forging step.

3. A composite forging method for a T-shaped airfoil cross-section part according to claim 2, characterized in that: The preforming mold comprises a first forming mold (5), a spacer block (8) and a pressure head (7); a first cavity (51) is provided on the first forming mold (5); the spacer block (8) is placed at the bottom of the first cavity (51) and is slidably connected to the first cavity (51); and the pressure head (7) is placed at the top of the first cavity (51) and is slidably connected to the first cavity (51).

4. A composite forging method for a T-shaped airfoil cross-section part according to claim 3, characterized in that: The first mold cavity (51) comprises a lower mold cavity (52) and an upper mold cavity (53), wherein the lower mold cavity (52) and the upper mold cavity (53) are connected, the lower mold cavity (52) has a rectangular cross-section, the upper mold cavity (53) has a funnel-shaped cross-section, and the width of the upper mold cavity (53) is greater than that of the upper mold cavity (53).

5. The composite forging method of a T-shaped airfoil cross-section part according to claim 1, characterized in that: The forming mold comprises a second forming mold (6) and a padding block (8); a second cavity (61) is provided on the second forming mold (6); and the padding block (8) is placed at the bottom of the second cavity (61) and is slidably connected to the second forming mold (6).

6. A composite forging method for a T-shaped airfoil cross-section part according to claim 5, characterized in that: A placement groove (62) is provided on the top of the second molding die (6), and the top of the second cavity (61) is connected to the placement groove (62). The width of the placement groove (62) is greater than the width of the second cavity (61).

7. A composite forging method for a T-shaped airfoil cross-section part according to any one of claims 1 to 6, characterized in that: The two forging steps include the following steps: S1: placing the shim block (8) and the blank (1) into the first cavity (51) in sequence, placing the blank (1) on the shim block (8), placing the ram (7) on top of the blank (1), using the upper flat anvil attached to the hydraulic forging equipment to press the ram (7), and moving it downward to apply pressure, causing the upper end of the blank (1) to deform and fill the upper cavity (53) of the first forming die (5), thereby obtaining a preformed blank (2), and then turning the first forming die (5) 180°, and using a ram to push the shim block (8), the preformed blank (2) and the ram (7) out of the first forming die (5), thereby completing the first forging; S2: The raising block (8) and the preformed blank (2) are sequentially placed in the second cavity (61), the preformed blank (2) is placed on the raising block (8), and a second forging is performed. The upper flat anvil attached to the hydraulic forging equipment is used to press the top of the preformed blank (2), so that the preformed blank (2) fills the placement groove (62) of the second forming die (6) under the action of the flat anvil to obtain a forging (3), and then the second forming die (6) is turned 180 degrees, and the raising block (8) and the forging (3) are ejected from the second forming die (6) by a head. The forging (3) is post-processed to obtain an airfoil cross-section part (4).

8. The composite forging method of a T-shaped airfoil cross-section part according to claim 7, characterized in that: In the step S1, before placing the blank (1) into the first cavity (51), the blank (1) is heated to 900-1200° C. and then kept warm; In the step S2, before the preformed blank (2) is placed into the second cavity (61), the preformed blank (2) is heated to 900-1200° C. and then kept warm.

9. A composite forging method for a T-shaped airfoil cross-section part according to claim 8, characterized in that: The calculation formula for the holding time in step S1 is: t=η1×m×T The calculation formula for the holding time in step S2 is: t=η2×m×T Where: t—calculated holding time, in min; η1—heat conductivity coefficient of cold billet in furnace, η2—heat conductivity coefficient of hot billet in furnace; T—maximum effective cross-sectional thickness of part, in mm; m—heating coefficient, in min / mm.

10. The composite forging method of a T-shaped airfoil cross-section part according to claim 9, characterized in that: The heat conduction coefficient η1 in the cold billet furnace is 0.8-1, and the heat conduction coefficient η2 in the hot billet furnace is 0.3-0.6; the heating coefficient is 0.7-0.9 min / mm.

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