CN113878191A - Multistage vacuum brazing processing method for high-pressure turbine guide component - Google Patents
Multistage vacuum brazing processing method for high-pressure turbine guide component Download PDFInfo
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- CN113878191A CN113878191A CN202111056459.XA CN202111056459A CN113878191A CN 113878191 A CN113878191 A CN 113878191A CN 202111056459 A CN202111056459 A CN 202111056459A CN 113878191 A CN113878191 A CN 113878191A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/008—Soldering within a furnace
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
Abstract
The invention discloses a multistage vacuum brazing processing method for a high-pressure turbine guide component, which comprises the following steps: s10, performing first-stage vacuum brazing, namely welding the guide vane and the turbine casing in a vacuum brazing furnace by adopting first-stage brazing filler metal with a solid-liquid line of 1080-1135 ℃ and adopting a brazing temperature of 1140-1190 ℃; and S20, performing second-stage vacuum brazing, namely connecting an inner ring assembly formed by welding the turbine casing and the guide vane with an orifice plate ring in a vacuum brazing furnace at a brazing temperature of 1040-1070 ℃ by using a second-stage brazing filler metal with a solid-liquid line of 970-1000 ℃, wherein the brazing time of the second-stage brazing is less than or equal to that of the first-stage brazing. The multistage vacuum brazing processing method for the high-pressure turbine guide component meets the welding technical requirements of the guide blade, the turbine casing and the orifice plate ring, is convenient to operate, ensures that a brazing welding seam is formed well, has high welding qualification rate and ensures that the combined high-pressure turbine guide component has good air tightness.
Description
Technical Field
The invention relates to the technical field of welding of high-pressure turbine guide assemblies, in particular to a multistage vacuum brazing processing method of a high-pressure turbine guide assembly.
Background
As shown in fig. 1, a high pressure turbine nozzle assembly for an aircraft engine of some type is comprised of a turbine casing, nozzle vanes, and an orifice ring. The turbine casing is provided with a blade profile hole which radially penetrates through the annular wall of the turbine casing, the blade profile hole is arranged close to an air inlet of the turbine casing, the guide vanes and the blade profile hole are arranged in a one-to-one correspondence mode, and the turbine casing, the guide vanes and the orifice plate ring need to be connected.
At present, the high-pressure turbine guider component is welded and combined by fusion welding and connected by fusion welding, and the high-pressure turbine guider component has the defects of complex structure, more welding seams, poor weldability of materials and poor operability, and the welding seams are easy to generate welding defects such as cracks, incomplete fusion and the like after fusion welding, so that the air tightness of the component is influenced; meanwhile, because the fusion welding temperature is high, a welding heat affected zone exists, the mechanical property of the assembly is greatly affected, local heating is performed during fusion welding, the part deformation is large, and the size and flow distribution of the high-pressure turbine guider assembly are greatly affected.
Disclosure of Invention
The invention provides a multistage vacuum brazing processing method for a high-pressure turbine guider component, which aims to solve the technical problems that the existing high-pressure turbine guider component is poor in operability in the welding and combining process, and the high-pressure turbine guider component formed after combination is poor in air tightness.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
the high-pressure turbine guider component comprises a turbine casing, guider blades and a hole plate ring, wherein the turbine casing is provided with blade-shaped holes which radially penetrate through the side wall of the turbine casing, the blade-shaped holes are close to an air inlet of the turbine casing, the blade-shaped holes are uniformly distributed at intervals along the circumferential direction of the turbine casing, the guider blades are distributed in one-to-one correspondence with the blade-shaped holes, the guider blades are inserted into the corresponding blade-shaped holes from the inner side of the turbine casing, and the hole plate ring is sleeved on the circumferential outer wall surface of the turbine casing. S10, performing first-stage vacuum brazing, namely welding the guide vane and the turbine casing in a vacuum brazing furnace by adopting first-stage brazing filler metal with a solid-liquid line of 1080-1135 ℃ and adopting a brazing temperature of 1140-1190 ℃; and S20, performing second-stage vacuum brazing, namely connecting an inner ring assembly formed by welding the turbine casing and the guide vane with an orifice plate ring in a vacuum brazing furnace at a brazing temperature of 1040-1070 ℃ by using a second-stage brazing filler metal with a solid-liquid line of 970-1000 ℃, wherein the brazing time of the second-stage brazing is less than or equal to that of the first-stage brazing.
Further, the outer side wall of the turbine casing is provided with a feeding groove for placing brazing filler metal inwards in the radial direction, the feeding groove and the blade-shaped hole are arranged in a one-to-one correspondence mode, the feeding groove is arranged in the circumferential direction of the blade-shaped hole and is close to the outer edge of the blade-shaped hole, and the step S10 is preceded by the following steps: s101, carrying out laser spot welding positioning, positioning all the guide vanes on corresponding vane-shaped holes in a preset position, enabling the axial position difference of all the guide vanes along the turbine casing to be not more than 0.2 mm, S102, removing an oxide film on the periphery of the laser positioning point, S103, vertically placing the turbine casing, and enabling an air inlet of the turbine casing to be positioned below an air outlet; adding a first-stage brazing filler metal into a feeding groove from the outer side of the turbine casing, and filling part of the first-stage brazing filler metal into a gap to be welded between the guide vane and the turbine casing through the feeding groove; filling a first-stage brazing filler metal in a gap to be welded between a guide vane and a turbine casing from the inner side of the turbine casing, and S104, brushing a flow-resisting agent on the outer wall surface of the turbine casing for protection, so that the first-stage brazing filler metal on the outer wall surface of the turbine casing is enclosed in a flow-resisting ring formed by the flow-resisting agent, and the first-stage brazing filler metal close to the outer wall surface of the turbine casing is prevented from overflowing in the first-stage brazing process; brushing a flow resisting agent on the inner wall surface of the turbine casing for protection, so that the first-stage brazing filler metal on the inner wall surface of the turbine casing is enclosed in a flow resisting ring formed by the flow resisting agent ring, the first-stage brazing filler metal close to the inner wall surface of the turbine casing is prevented from overflowing in the first-stage brazing process, a first part body is obtained, S105, the first part body is placed into an oven, and the first part body is baked at the temperature of 100-120 ℃ to remove moisture in the first-stage brazing filler metal.
Further, first order brazing filler metal includes mixed paste brazing filler metal and BNi71CrSi paste brazing filler metal that BNi71CrSi brazing filler metal and nickel powder were mixed and were made one by one, add first order brazing filler metal in the charge tank from the outside of turbine case in step S103 to make part first order brazing filler metal fill in the clearance between director blade and turbine case through the charge tank, specifically include: penetrating the mixed paste-shaped brazing filler metal through a feeding groove from the outer side of the turbine casing and filling the mixed paste-shaped brazing filler metal into a target gap, wherein the target gap is a gap of which the single-side gap between a guide vane and a corresponding blade-shaped hole is 0.1-0.15 mm; and adding the BNi71CrSi paste solder into the feed tank from the outer side of the turbine casing, so that the BNi71CrSi paste solder covers the to-be-welded outer wall surface of the guide vane along the circumferential direction of the guide vane.
Further, the guide vane includes a large arc area, a medium arc area, and a small arc area that are sequentially distributed from the tip toward the tail along the bending direction thereof, and the brazing filler metal is filled in the gap between the guide vane and the turbine casing from the inner side of the turbine casing in step S103, specifically including: a first-stage brazing filler metal with the diameter of 1.0-1.4 mm is added into a gap between a large-radian area of a guide vane and a turbine casing from the inner side of the turbine casing, and a first-stage brazing filler metal with the diameter of 0.4-0.6 mm is added into a gap between a middle-radian area of the guide vane and the turbine casing from the inner side of the turbine casing.
Further, step S10 specifically includes: the method comprises the following steps of performing first-stage vacuum brazing, vertically placing a turbine casing in a vacuum brazing furnace, enabling an air inlet of the turbine casing to be located above an air outlet, adopting a first-stage brazing filler metal with a solid-liquid line of 1080-1135 ℃, adopting a brazing temperature of 1140-1190 ℃, and welding the turbine casing and a guide vane for 10-20 minutes.
Further, the following steps are included before step S101: trial combination is carried out on the guide vane and the turbine casing, all the guide vane can be ensured to be arranged in the corresponding blade profile hole, and the single-side gap between the guide vane and the corresponding blade profile hole is not more than 0.15 mm; separating the pilot blade and the turbine casing after the pilot assembly; cleaning an oxide layer on the to-be-welded outer wall surface of the guider blade, cleaning an oxide layer on the to-be-welded inner wall surface of the blade-shaped hole, cleaning the to-be-welded outer wall surface of the guider blade and the to-be-welded inner wall surface of the blade-shaped hole, and removing oil stains and impurities on the to-be-welded surface of the guider blade and the to-be-welded surface of the blade-shaped hole; brushing nickel plating is carried out on the outer wall surface to be welded of the guide vane, and brushing nickel plating is carried out on the inner wall surface to be welded of the vane-shaped hole; a layer of BNi71CrSi sticky tape brazing filler metal ring is arranged on the to-be-welded outer wall surface of the guide vane along the circumferential direction of the guide vane; the guide vanes with BNi71CrSi sticky tape brazing ring are assembled on the corresponding profile holes of the turbine casing through a clamp, and the axial position difference of all the guide vanes along the turbine casing is not more than 0.2 mm.
Further, the following steps are added after step S10: cleaning up redundant brazing filler metal and residual flow resisting agent; and (4) carrying out leakage detection by using kerosene, checking whether the kerosene leakage of the inner ring assembly is qualified or not, and entering the next step after the kerosene leakage is qualified.
Further, before step S20, the following steps are added: s201, trial combination is carried out on the orifice plate ring and the inner ring assembly, and a single-side gap between the inner wall surface of the to-be-welded circumference of the orifice plate ring and the outer wall surface of the to-be-welded circumference of the turbine casing is ensured to be 0.05-0.08 mm; s202, brushing nickel on the inner wall surface of the to-be-welded circumference of the orifice plate ring, and brushing nickel on the outer wall surface of the to-be-welded circumference of the turbine casing; s203, arranging a layer of BNi82CrSiB amorphous solder ring on the to-be-welded circumferential outer wall surface of the turbine casing; s204, assembling and sleeving the orifice plate ring on the turbine casing, and welding the orifice plate ring on the turbine casing by adopting laser spot welding positioning; s205, filling a second-stage brazing filler metal in a gap to be welded between the orifice plate ring and the turbine casing to form a second part body, putting the second part body into an oven, baking at the temperature of 100-120 ℃ to remove moisture in the second-stage brazing filler metal, and arranging a layer of BNi82CrSiB sticky ring for pressing the second-stage brazing filler metal on the second-stage brazing filler metal between the orifice plate ring and the turbine casing; and S206, brushing a flow resisting agent at the position close to the outer edge of the second-stage brazing filler metal, so that the second-stage brazing filler metal on the inner wall surface of the turbine casing is enclosed in a flow resisting ring formed by the flow resisting agent, and the second-stage brazing filler metal is prevented from overflowing in the second-stage brazing process.
Further, step S20 specifically includes: and (2) performing second-stage vacuum brazing, vertically placing the turbine casing in a vacuum brazing furnace, enabling the air inlet of the turbine casing to be positioned above the air outlet, adopting a second-stage brazing filler metal with a solid-liquid line of 970-1000 ℃, adopting a brazing temperature of 1040-1070 ℃ for 5-10 minutes, and connecting an inner ring assembly formed by welding the turbine casing and the guide vane with the orifice plate ring in the vacuum brazing furnace.
Further, after step S20, the following steps are added: and performing leakage detection by using kerosene, checking whether the high-pressure turbine guide assembly formed after the second-stage brazing has kerosene leakage or not, and judging that the welding of the high-pressure turbine guide assembly is qualified under the condition of no kerosene leakage.
The invention has the following beneficial effects:
the invention discloses a multistage vacuum brazing processing method of a high-pressure turbine guide component. Welding the guide vane and the turbine casing by first-stage vacuum brazing, and simultaneously welding the circumferential outer wall surfaces of the guide vanes in the vane holes; welding the turbine casing and the orifice plate ring through second-stage vacuum brazing to enable the orifice plate ring to be welded on an inner ring assembly formed by combining the turbine casing and the guide vane, and further completing assembly of the turbine casing assembly; because the solid-liquid line of the first-stage brazing filler metal used for the first-stage vacuum brazing is 1080-1135 ℃, the temperature of the first-stage vacuum brazing is 1140-1190 ℃, the solid-liquid line of the second-stage brazing filler metal is 970-1000 ℃, the brazing temperature during the second-stage vacuum brazing is 1040-1070 ℃, the temperature of the second-stage vacuum brazing does not exceed the solidus line of the first-stage brazing filler metal used for the first-stage vacuum brazing, the brazing time length of the second-stage brazing is less than or equal to that of the first-stage brazing, when the inner ring combination is connected with the perforated plate ring through the second-stage vacuum brazing, the influence on the first-stage brazing seam is small, and the first-stage brazing seam cannot be melted; the method has the advantages that the first-stage vacuum brazing is carried out after the first-stage brazing filler metal is filled in the welding seam to be welded, the second-stage vacuum brazing is carried out after the second-stage brazing filler metal is filled in the welding seam to be welded, the welding technical requirements of the guide vane, the turbine casing and the orifice plate ring are met, the process flow is reasonable, the operation is convenient, the engineering application of the welding process is realized, the welding seam is well formed, the welding qualification rate is high, and the air tightness of the combined high-pressure turbine guide assembly is good.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic structural view of a high pressure turbine nozzle assembly of a preferred embodiment of the present invention;
FIG. 2 is a flow chart of a multi-stage vacuum brazing process for a high pressure turbine nozzle assembly in accordance with a preferred embodiment of the present invention.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
FIG. 1 is a schematic structural view of a high pressure turbine nozzle assembly of a preferred embodiment of the present invention; FIG. 2 is a flow chart of a multi-stage vacuum brazing process for a high pressure turbine nozzle assembly in accordance with a preferred embodiment of the present invention.
As shown in fig. 2, the multistage vacuum brazing processing method for the high-pressure turbine guider component in the embodiment includes a turbine casing, a guider blade and a perforated plate ring, wherein a vane hole penetrating through a side wall of the turbine casing along a radial direction is formed in the turbine casing, the vane hole is arranged close to an air inlet of the turbine casing, a plurality of vane holes are uniformly distributed at intervals along a circumferential direction of the turbine casing, the guider blade and the vane hole are distributed in a one-to-one correspondence manner, the guider blade is inserted into the corresponding vane hole from an inner side of the turbine casing, and the perforated plate ring is sleeved on a circumferential outer wall surface of the turbine casing, and includes the following steps: s10, performing first-stage vacuum brazing, namely welding the guide vane and the turbine casing in a vacuum brazing furnace by adopting first-stage brazing filler metal with a solid-liquid line of 1080-1135 ℃ and adopting a brazing temperature of 1140-1190 ℃; and S20, performing second-stage vacuum brazing, namely connecting an inner ring assembly formed by welding the turbine casing and the guide vane with an orifice plate ring in a vacuum brazing furnace at a brazing temperature of 1040-1070 ℃ by using a second-stage brazing filler metal with a solid-liquid line of 970-1000 ℃, wherein the brazing time of the second-stage brazing is less than or equal to that of the first-stage brazing.
The invention discloses a multistage vacuum brazing processing method of a high-pressure turbine guide component. Welding the guide vane and the turbine casing by first-stage vacuum brazing, and simultaneously welding the circumferential outer wall surfaces of the guide vanes in the vane holes; welding the turbine casing and the orifice plate ring through second-stage vacuum brazing to enable the orifice plate ring to be welded on an inner ring assembly formed by combining the turbine casing and the guide vane, and further completing assembly of the turbine casing assembly; because the solid-liquid line of the first-stage brazing filler metal used for the first-stage vacuum brazing is 1080-1135 ℃, the temperature of the first-stage vacuum brazing is 1140-1190 ℃, the solid-liquid line of the second-stage brazing filler metal is 970-1000 ℃, the brazing temperature during the second-stage vacuum brazing is 1040-1070 ℃, the temperature of the second-stage vacuum brazing does not exceed the solidus line of the first-stage brazing filler metal used for the first-stage vacuum brazing, the brazing time length of the second-stage brazing is less than or equal to that of the first-stage brazing, when the inner ring combination is connected with the perforated plate ring through the second-stage vacuum brazing, the influence on the first-stage brazing seam is small, and the first-stage brazing seam cannot be melted; the method has the advantages that the first-stage vacuum brazing is carried out after the first-stage brazing filler metal is filled in the welding seam to be welded, the second-stage vacuum brazing is carried out after the second-stage brazing filler metal is filled in the welding seam to be welded, the welding technical requirements of the guide vane, the turbine casing and the orifice plate ring are met, the process flow is reasonable, the operation is convenient, the engineering application of the welding process is realized, the welding seam is well formed, the welding qualification rate is high, and the air tightness of the combined high-pressure turbine guide assembly is good.
As can be understood, the first-stage brazing filler metal comprises a mixed paste brazing filler metal prepared by mixing BNi71CrSi brazing filler metal and nickel powder, BNi71CrSi paste brazing filler metal and BNi71CrSi adhesive tape brazing filler metal rings; the second-stage brazing filler metal comprises a BNi82CrSiB paste brazing filler metal, a BNi82CrSiB amorphous brazing filler metal ring and a BNi82CrSiB adhesive tape brazing filler metal ring.
It is understood that the number of the leaf-shaped holes in the present invention is plural, and may be two, three, ten or other numbers. Specifically, the number of the blade-shaped holes is 19, the guide vane and the turbine casing are welded by adopting first-stage vacuum brazing, the 19 guide vane can be welded and fixed on the turbine casing at the same time, the inner ring assembly is connected with the orifice plate ring by adopting second-stage vacuum brazing, the orifice plate ring can be welded and fixed on the turbine casing from each circumferential position of the turbine casing by single welding, the influence of the structure and the processing technology of the high-pressure turbine guide vane assembly is small, and the operation is convenient.
Further, the outer side wall of the turbine casing is provided with a feeding groove for placing brazing filler metal inwards in the radial direction, the feeding groove and the blade-shaped hole are arranged in a one-to-one correspondence mode, the feeding groove is arranged in the circumferential direction of the blade-shaped hole and is close to the outer edge of the blade-shaped hole, and the step S10 is preceded by the following steps: s101, carrying out laser spot welding positioning, positioning all the guide vanes on corresponding vane-shaped holes in a preset position, enabling the circumferential position difference of all the guide vanes along the axial direction of the turbine casing to be not more than 0.2 mm, S102, removing an oxide film on the periphery of a laser positioning point, S103, adding a first-stage brazing filler metal into a feeding groove from the outer side of the turbine casing, and enabling part of the first-stage brazing filler metal to be filled in a gap to be welded between each guide vane and the turbine casing through the feeding groove; filling a first-stage brazing filler metal in a gap to be welded between a guide vane and a turbine casing from the inner side of the turbine casing, and S104, brushing a flow-resisting agent on the outer wall surface of the turbine casing for protection, so that the first-stage brazing filler metal on the outer wall surface of the turbine casing is enclosed in a flow-resisting ring formed by the flow-resisting agent, and the first-stage brazing filler metal close to the outer wall surface of the turbine casing is prevented from overflowing in the first-stage brazing process; brushing a flow resisting agent on the inner wall surface of the turbine casing for protection, so that a first stage on the inner wall surface of the turbine casing is enclosed in a flow resisting ring formed by the flow resisting agent ring, the first stage brazing filler metal close to the inner wall surface of the turbine casing is prevented from overflowing in the first stage brazing process, a first part body is obtained, S105, the first part body is placed into an oven, and the first part body is baked at the temperature of 100-120 ℃ to remove moisture in the first stage brazing filler metal. The turbine casing has a certain wall thickness, so that first-stage brazing filler metal is filled into gaps to be welded between the turbine blades and the turbine casing from the inner side and the outer side of the turbine casing respectively, the sealing performance of connection between the guide vane and the turbine casing is improved, and the force bearing performance of the inner ring assembly is ensured; by brushing a flow resisting agent on the periphery of the first-stage brazing filler metal, the first-stage brazing filler metal is prevented from overflowing to a non-welding part in the first-stage brazing process to influence the welding quality. The feeding groove is arranged to store the first-stage brazing filler metal, so that enough first-stage brazing filler metal is filled into a gap to be welded between the guide vane and the blade profile hole in the first-stage brazing process, and the compactness of a first-stage brazing welding line is guaranteed. In order to ensure the assembly requirement, the height difference of all the guide vanes along the axial direction is not more than 0.2 mm when the spot welding positioning is carried out.
Preferably, when the laser spot welding is positioned, the laser positioning welding parameters are as follows: the pulse width is 15ms, the energy is 20-30J, the defocusing amount is 10 +/-1 mm, and the distance between two adjacent welding points is 5-15 mm. The method is characterized in that laser spot welding positioning is carried out by using parameters of 20-30J of energy to complete pre-positioning of the guide vane and the turbine casing, so that the positioning strength is guaranteed on the basis of not damaging a part base body, if the energy is less than 20J, the guide vane and a blade-shaped hole of the turbine casing are not firmly positioned, the guide vane is easy to fall off, and if the energy is more than 30J, the diameter of a positioning welding spot is increased due to overlarge energy, and the quality of a vacuum brazing welding seam is influenced.
Preferably, a grinding machine is adopted to remove the oxide film on the periphery of the laser positioning point; brushing a flow resisting agent at a position 1 mm away from the corresponding first-stage brazing filler metal on the outer wall surface of the turbine casing for protection, and brushing the flow resisting agent at a position 1 mm away from the corresponding first-stage brazing filler metal on the inner wall surface of the turbine casing for protection, so that the first-stage brazing filler metal is prevented from overflowing at a non-welding part in the first-stage brazing process to influence the welding quality; and (3) placing the part body brushed with the flow resisting agent into an oven, and baking for 20-30 minutes at 100-120 ℃ so as to completely volatilize the water in the first-stage brazing filler metal.
Further, first order brazing filler metal includes mixed paste brazing filler metal and BNi71CrSi paste brazing filler metal that BNi71CrSi brazing filler metal and nickel powder were mixed and were made one by one, add first order brazing filler metal in the charge tank from the outside of turbine case in step S103 to make part first order brazing filler metal fill in the clearance between director blade and turbine case through the charge tank, specifically include: penetrating the mixed paste-shaped brazing filler metal through a feeding groove from the outer side of the turbine casing and filling the mixed paste-shaped brazing filler metal into a target gap, wherein the target gap is a single-side gap between a guide vane and a corresponding vane-shaped hole and is 0.1-0.15 mm; and adding the BNi71CrSi paste solder into the feed tank from the outer side of the turbine casing, so that the BNi71CrSi paste solder covers the to-be-welded outer wall surface of the guide vane along the circumferential direction of the guide vane. In the invention, a large-gap (namely, the target gap is more than 0.1 mm) vacuum brazing technology is adopted, namely BNi71CrSi brazing filler metal with a lower melting point and nickel powder with a higher melting point are brazed according to the ratio of 3: 2, mixing the materials into paste to form mixed paste solder, and adding the mixed paste solder into a target gap, so that the welding quality of the target gap is guaranteed, and the bearing property and the sealing property of the inner ring assembly are improved; the BNi71CrSi paste brazing filler metal is added from the side face of the turbine case to the outer wall face to be welded of the guide vane, the BNi71CrSi paste brazing filler metal is not easy to hold and is easy to fall off, the charging groove is arranged on the turbine case at the position of the vane-shaped hole in contact with the side face of the guide vane, the shape of the charging groove is consistent with the profile of the vane, and when the BNi71CrSi paste brazing filler metal is added from the outer side of the turbine case, the BNi71CrSi paste brazing filler metal is added into the charging groove, and the BNi71CrSi paste brazing filler metal is not easy to fall off.
More preferably, the depth of the feeding groove is 2 mm, the ring diameter of the feeding groove is 2 mm, the BNi71CrSi paste solder is added into the feeding groove, the added BNi71CrSi paste solder exceeds 20% of the volume of the feeding groove, enough BNi71CrSi paste solder is ensured to enter a gap between the guide vane and the vane hole, and the compactness of a welding seam of the guide vane and the turbine casing is ensured.
Further, the guide vane includes a large arc area, a medium arc area, and a small arc area that are sequentially distributed from the tip toward the tail along the bending direction thereof, and the brazing filler metal is filled in the gap between the guide vane and the turbine casing from the inner side of the turbine casing in step S103, specifically including: a first-stage brazing filler metal with the diameter of 1.0-1.4 mm is added into a gap between a large-radian area of a guide vane and a turbine casing from the inner side of the turbine casing, and a first-stage brazing filler metal with the particle size of 0.4-0.6 mm is added into a gap between a medium-radian area of the guide vane and the turbine casing from the inner side of the turbine casing. It is understood that in this embodiment, BNi71CrSi paste solder having a diameter of 1.2 mm is added from the inside of the turbine casing in the gap between the large camber area of the guide vane and the turbine casing, and BNi71CrSi paste solder having a diameter of 0.5 mm is added from the inside of the turbine casing in the gap between the medium camber area of the guide vane and the turbine casing. Preferably, in order to ensure the compactness of the welding seam and further avoid the overflow of the first-stage brazing and ensure that the brazing angle in the flow channel cannot exceed R1, the requirement of the brazing angle in the flow channel is ensured by controlling the feeding amount of the BNi71CrSi paste brazing filler metal. Specifically, sectional feeding is carried out, and BNi71CrSi paste solder with the diameter of 1.2 mm is added on the back surfaces of the leaf basin and the leaf within the range of about 5 mm at the tip end of the leaf; adding a BNi71CrSi paste solder with the diameter of 0.5 mm on the back of the leaf basin and the back of the leaf within the range of 5-10 mm at the middle position of the side surface of the leaf; BNi71CrSi paste brazing filler metal is not added at the tail part of the blade, the blade basin surface and the blade back surface, meanwhile, during first brazing, a turbine case is vertically placed in a vacuum brazing furnace, an air inlet of the turbine case is positioned above an air outlet, the BNi71CrSi paste brazing filler metal above flows down under the action of gravity, the defects of the BNi71CrSi paste brazing filler metal below are filled, the requirement that a fillet of a welding seam is smaller than R1 after first-stage brazing is ensured, and the quality problems of brazing filler metal overflowing and the like cannot occur at the position of the welding seam below.
Further, step S10 specifically includes: the method comprises the following steps of performing first-stage vacuum brazing, vertically placing a turbine casing in a vacuum brazing furnace, enabling an air inlet of the turbine casing to be located above an air outlet, adopting a first-stage brazing filler metal with a solid-liquid line of 1080-1135 ℃, adopting a brazing temperature of 1140 ℃ and 1190 ℃, and welding the turbine casing and a guide vane for 8-20 minutes. Specifically, in the present embodiment, the first stage vacuum brazing of the turbine casing and the 19 high pressure turbine nozzle vanes has a solidus line of 1080 ℃ to 1135 ℃, and the brazing temperature: 1170 ℃, time: and 15 min.
Further, the following steps are included before step S101: trial combination is carried out on the guide vane and the turbine casing, all the guide vane can be ensured to be arranged in the corresponding blade profile hole, and the single-side gap between the guide vane and the corresponding blade profile hole is not more than 0.15 mm; separating the pilot blade and the turbine casing after the pilot assembly; cleaning an oxide layer on the to-be-welded outer wall surface of the guider blade, cleaning an oxide layer on the to-be-welded inner wall surface of the blade-shaped hole, cleaning the to-be-welded outer wall surface of the guider blade and the to-be-welded inner wall surface of the blade-shaped hole, and removing oil stains and impurities on the surface of a welding part of the to-be-welded guider blade and the to-be-welded surface of the blade-shaped hole; brushing nickel plating is carried out on the outer wall surface to be welded of the guide vane, and brushing nickel plating is carried out on the inner wall surface to be welded of the vane-shaped hole; a layer of BNi71CrSi sticky tape brazing filler metal ring is arranged on the to-be-welded outer wall surface of the guide vane along the circumferential direction of the guide vane; the guide vanes with BNi71CrSi sticky tape brazing ring are assembled on the corresponding profile holes of the turbine casing through a clamp, and the axial position difference of all the guide vanes along the turbine casing is not more than 0.2 mm. Optionally, the unilateral clearance between the positioned guider blade and the corresponding blade profile hole is not more than 0.15 mm, the smaller the brazing clearance is, the higher the weld strength is, and the better the weld quality is; the method comprises the following steps of penetrating sand paper into a blade-shaped hole of a turbine casing, polishing and removing an oxide layer on the inner wall surface to be welded of the blade-shaped hole, cleaning an oxide layer on the outer wall surface to be welded of a guide vane by using the sand paper, and cleaning the surfaces to be welded of the turbine casing and the guide vane by using acetone to remove oil stains and impurities on the surface of a part to be welded; the thickness of the nickel layer is 0.002-0.02 mm to improve the brazing performance, when the thickness of the nickel layer is less than 0.002 mm, the brazing filler metal cannot be spread, and when the thickness of the nickel layer exceeds 0.02 mm, the nickel layer is easy to peel, so that the nickel layer drives the brazing filler metal to fall off together; the thickness of the BNi71CrSi adhesive tape solder ring is 0.15 mm, the thickness of the adhesive tape solder is 0.15 mm because the gap of a welding seam is less than or equal to 0.15 mm, the adhesive tape solder is extruded after being pasted, and the thickness of the adhesive tape solder can be in the range of 0.05-0.10 mm.
Further, after step S10, the following steps are added: cleaning up redundant brazing filler metal and residual flow resisting agent; and (4) carrying out leakage detection by using kerosene, checking whether the kerosene leakage of the inner ring assembly is qualified or not, and entering the next step after the kerosene leakage is qualified. Specifically, a grinding machine is adopted to grind redundant brazing filler metal, a clean rag is used to clean up residual flow resisting agent, and clean compressed air is used to blow off the redundant materials on the surface of the part; performing kerosene leakage inspection on the welding seams, and keeping that no kerosene leakage exists within 30 minutes, so that the kerosene leakage of the inner ring assembly is qualified; and (4) carrying out appearance inspection on the inner ring assembly, wherein the welding line is continuous and consistent, the brazing filler metal with the maximum defect not more than 3 mm is allowed to be not filled, and the other surfaces cannot have redundant brazing filler metal.
Further, before step S20, the following steps are added: s201, trial combination is carried out on the orifice plate ring and the inner ring assembly, a gap between the inner wall surface of the to-be-welded circumference of the orifice plate ring and the outer wall surface of the to-be-welded circumference of the turbine casing is ensured to be 0.05-0.08 mm, S202, brushing nickel on the inner wall surface of the circumference to be welded of the orifice ring, brushing nickel on the outer wall surface of the circumference to be welded of the turbine case, S203, arranging a layer of BNi82CrSiB amorphous brazing ring on the to-be-welded circumferential outer wall surface of the turbine casing, 204, assembling and sleeving the orifice plate ring on the turbine casing, welding the orifice plate ring on the turbine casing by adopting laser spot welding positioning, S205, filling a second-stage brazing filler metal in a gap to be welded between the orifice plate ring and the turbine casing to form a second part body, placing the second part body formed by assembly into an oven, baking at the temperature of 100-120 ℃ to remove moisture in the second-stage brazing filler metal, and filling a layer of BNi82CrSiB sticky ring for pressing the second-stage brazing filler metal at a to-be-welded position between the orifice plate ring and the turbine casing; and S206, brushing a flow resisting agent at the position close to the outer edge of the second-stage brazing filler metal, so that the second-stage brazing filler metal on the inner wall surface of the turbine casing is enclosed in a flow resisting ring formed by the flow resisting agent, and the second-stage brazing filler metal is prevented from overflowing in the second-stage brazing process. Understandably, the perforated plate ring and the turbine casing are combined in a test mode, the gap of a welding seam is controlled to be 0.05-0.08 mm after the combination, amorphous brazing filler metal with the thickness of 0.04 mm can be added, and the requirement of a vacuum brazing gap is met; the thickness of the nickel layer is 0.002-0.02 mm to improve the brazing performance, when the thickness of the nickel layer is less than 0.002 mm, the brazing filler metal cannot be spread, and when the thickness of the nickel layer exceeds 0.02 mm, the nickel layer is easy to peel, so that the nickel layer drives the brazing filler metal to fall off together; the thickness of the BNi82CrSiB amorphous solder is 0.04 mm, specifically, two ends of the BNi82CrSiB amorphous solder are cut by 30 degrees to form a circle around a turbine casing after being spliced, the two ends are positioned by using energy storage spot welding, the solder is butt-jointed at the interface position by shearing 30 degrees and butt-jointing along the axial direction by 90 degrees, and the axial penetrability defect is not easy to form after brazing; the machining parameters of the energy storage spot welding are as follows: the voltage is 30V-80V, the distance between two adjacent welding spots is 5-10 mm, the voltage is less than 30V, the spot welding is easy, the spot welding voltage is more than 80V, and the amorphous brazing filler metal is easy to be fixed and penetrated; the laser electric welding positioning parameters are as follows: pulse width: the energy is 10-15J, the defocusing amount is 10 +/-1 mm, the distance between two adjacent welding spots is 10-20 mm, the energy is less than 10J, the spot welding is easy, the energy is more than 15J, and the ring point of the hole plate is easy to penetrate; adding BNi82CrSiB paste solder with the diameter of 0.5 mm, baking the mixture in an oven for 20 to 30 minutes at the temperature of between 100 and 120 ℃, covering the BNi82CrSiB paste solder with a BNi82CrSiB adhesive tape solder ring, and sealing the opening.
Further, step S20 specifically includes: and (2) second-stage vacuum brazing, vertically placing the turbine casing in a vacuum brazing furnace, enabling the air inlet of the turbine casing to be positioned above the air outlet, adopting a second-stage brazing filler metal with a solid-liquid line of 970-1000 ℃, and connecting an inner ring assembly formed by welding the turbine casing and the guide vane with the orifice plate ring in the vacuum brazing furnace at the brazing temperature of 1040-1070 ℃. More preferably, the brazing temperature: 1040 deg.C for 8 min.
Further, after step S20, the following steps are added: and performing leakage detection by using kerosene, checking whether the high-pressure turbine guide assembly formed after the second-stage brazing has kerosene leakage or not, and judging that the welding of the high-pressure turbine guide assembly is qualified under the condition of no kerosene leakage.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The high-pressure turbine guider component comprises a turbine casing, guider blades and a hole plate ring, wherein the turbine casing is provided with blade-shaped holes which radially penetrate through the side wall of the turbine casing, the blade-shaped holes are close to an air inlet of the turbine casing, the blade-shaped holes are uniformly distributed at intervals along the circumferential direction of the turbine casing, the guider blades are distributed in one-to-one correspondence with the blade-shaped holes, the guider blades are inserted into the corresponding blade-shaped holes from the inner side of the turbine casing, and the hole plate ring is sleeved on the circumferential outer wall surface of the turbine casing.
S10, performing first-stage vacuum brazing, namely welding the guide vane and the turbine casing in a vacuum brazing furnace by adopting first-stage brazing filler metal with a solid-liquid line of 1080-1135 ℃ and adopting a brazing temperature of 1140-1190 ℃;
and S20, performing second-stage vacuum brazing, namely connecting an inner ring assembly formed by welding the turbine casing and the guide vane with an orifice plate ring in a vacuum brazing furnace at a brazing temperature of 1040-1070 ℃ by using a second-stage brazing filler metal with a solid-liquid line of 970-1000 ℃, wherein the brazing time of the second-stage brazing is less than or equal to that of the first-stage brazing.
2. The high pressure turbine nozzle assembly multi-stage vacuum brazing process of claim 1,
the outer side wall of the turbine casing is inwards provided with feed tanks for placing brazing filler metal along the radial direction, the feed tanks and the blade-shaped holes are correspondingly arranged one by one, the feed tanks are arranged along the circumferential direction of the blade-shaped holes and are close to the outer edges of the blade-shaped holes,
the following steps are included before step S10:
s101, carrying out laser spot welding positioning, pre-positioning all the guide vanes on corresponding vane-shaped holes, enabling the axial position difference of all the guide vanes along the turbine casing to be not more than 0.2 mm,
s102, removing the oxide film around the laser positioning point,
s103, vertically placing a turbine casing to enable an air inlet of the turbine casing to be positioned below an air outlet; adding a first-stage brazing filler metal into a feeding groove from the outer side of the turbine casing, and filling part of the first-stage brazing filler metal into a gap to be welded between the guide vane and the turbine casing through the feeding groove; first-stage brazing filler metal is filled in a gap to be welded between a guide vane and a turbine casing from the inside of the turbine casing,
s104, brushing a flow resisting agent on the outer wall surface of the turbine casing for protection, so that the first-stage brazing filler metal on the outer wall surface of the turbine casing is enclosed in a flow resisting ring formed by the flow resisting agent, and the first-stage brazing filler metal close to the outer wall surface of the turbine casing is prevented from overflowing in the first-stage brazing process; brushing a flow resisting agent on the inner wall surface of the turbine casing for protection, so that the first-stage brazing filler metal on the inner wall surface of the turbine casing is enclosed in a flow resisting ring formed by a flow resisting agent ring, the first-stage brazing filler metal close to the inner wall surface of the turbine casing is prevented from overflowing in the first-stage brazing process, and a first part body is obtained,
s105, placing the first part body into an oven, and baking at the temperature of 100-120 ℃ to remove moisture in the first-stage brazing filler metal.
3. The high pressure turbine nozzle assembly multi-stage vacuum brazing process of claim 2,
the first-stage brazing filler metal comprises a mixed paste brazing filler metal prepared by mixing BNi71CrSi brazing filler metal and nickel powder and BNi71CrSi paste brazing filler metal,
in step S103, adding the first-stage brazing filler metal into the feed tank from the outer side of the turbine casing, and filling a part of the first-stage brazing filler metal into the gap between the vane and the turbine casing through the feed tank, specifically including:
penetrating the mixed paste-shaped brazing filler metal through a feeding groove from the outer side of the turbine casing and filling the mixed paste-shaped brazing filler metal into a target gap, wherein the target gap is a gap of which the single-side gap between a guide vane and a corresponding blade-shaped hole is 0.1-0.15 mm;
and adding the BNi71CrSi paste solder into the feed tank from the outer side of the turbine casing, so that the BNi71CrSi paste solder covers the to-be-welded outer wall surface of the guide vane along the circumferential direction of the guide vane.
4. The high pressure turbine nozzle assembly multi-stage vacuum brazing process according to any one of claims 1 to 3,
the guide vane comprises a large radian area, a middle radian area and a small radian area which are sequentially distributed from the head of the vane to the tail of the vane along the bending direction of the guide vane,
in step S103, filling brazing filler metal in the gap between the guide vane and the turbine casing from the inside of the turbine casing specifically includes:
adding a first-stage brazing filler metal with the diameter of 1.0-1.4 mm into a gap between a large-radian area of a guide vane and a turbine casing from the inner side of the turbine casing,
and adding a first-stage brazing filler metal with the diameter of 0.4-0.6 mm into a gap between the middle radian area of the guide vane and the turbine casing from the inner side of the turbine casing.
5. The high pressure turbine nozzle assembly multi-stage vacuum brazing process of claim 4,
step S10 specifically includes:
the method comprises the following steps of performing first-stage vacuum brazing, vertically placing a turbine casing in a vacuum brazing furnace, enabling an air inlet of the turbine casing to be located above an air outlet, adopting a first-stage brazing filler metal with a solid-liquid line of 1080-1135 ℃, adopting a brazing temperature of 1140-1190 ℃, and welding the turbine casing and a guide vane for 10-20 minutes.
6. The high pressure turbine nozzle assembly multi-stage vacuum brazing process of claim 5,
the following steps are included before step S101:
trial combination is carried out on the guide vane and the turbine casing, all the guide vane can be ensured to be arranged in the corresponding blade profile hole, and the single-side gap between the guide vane and the corresponding blade profile hole is not more than 0.15 mm;
separating the pilot blade and the turbine casing after the pilot assembly;
cleaning an oxide layer on the to-be-welded outer wall surface of the guider blade, cleaning an oxide layer on the to-be-welded inner wall surface of the blade-shaped hole, cleaning the to-be-welded outer wall surface of the guider blade and the to-be-welded inner wall surface of the blade-shaped hole, and removing oil stains and impurities on the to-be-welded surface of the guider blade and the to-be-welded surface of the blade-shaped hole;
brushing nickel plating is carried out on the outer wall surface to be welded of the guide vane, and brushing nickel plating is carried out on the inner wall surface to be welded of the vane-shaped hole;
a layer of BNi71CrSi sticky tape brazing filler metal ring is arranged on the to-be-welded outer wall surface of the guide vane along the circumferential direction of the guide vane;
the guide vanes with BNi71CrSi sticky tape brazing ring are assembled on the corresponding profile holes of the turbine casing through a clamp, and the axial position difference of all the guide vanes along the turbine casing is not more than 0.2 mm.
7. The high pressure turbine nozzle assembly multi-stage vacuum brazing process of claim 5,
the following steps are added after step S10:
cleaning up redundant brazing filler metal and residual flow resisting agent;
and (4) carrying out leakage detection by using kerosene, checking whether the kerosene leakage of the inner ring assembly is qualified or not, and entering the next step after the kerosene leakage is qualified.
8. The high pressure turbine nozzle assembly multi-stage vacuum brazing process of claim 1,
before step S20, the following steps are added:
s201, trial combination is carried out on the orifice plate ring and the inner ring assembly, and a single-side gap between the inner wall surface of the to-be-welded circumference of the orifice plate ring and the outer wall surface of the to-be-welded circumference of the turbine casing is ensured to be 0.05-0.08 mm;
s202, brushing nickel on the inner wall surface of the to-be-welded circumference of the orifice plate ring, and brushing nickel on the outer wall surface of the to-be-welded circumference of the turbine casing;
s203, arranging a layer of BNi82CrSiB amorphous solder ring on the to-be-welded circumferential outer wall surface of the turbine casing;
s204, assembling and sleeving the orifice plate ring on the turbine casing, and welding the orifice plate ring on the turbine casing by adopting laser spot welding positioning;
s205, filling a second-stage brazing filler metal in a gap to be welded between the orifice plate ring and the turbine casing to form a second part body, placing the second part body into an oven, baking at the temperature of 100-120 ℃ to remove water in the second-stage brazing filler metal,
arranging a layer of BNi82CrSiB sticky belt ring for pressing the second-stage brazing filler metal on the second-stage brazing filler metal between the orifice plate ring and the turbine casing;
and S206, brushing a flow resisting agent at the position close to the outer edge of the second-stage brazing filler metal, so that the second-stage brazing filler metal on the inner wall surface of the turbine casing is enclosed in a flow resisting ring formed by the flow resisting agent, and the second-stage brazing filler metal is prevented from overflowing in the second-stage brazing process.
9. The high pressure turbine nozzle assembly multi-stage vacuum brazing process of claim 8,
step S20 specifically includes:
and (2) performing second-stage vacuum brazing, vertically placing the turbine casing in a vacuum brazing furnace, enabling the air inlet of the turbine casing to be positioned above the air outlet, adopting a second-stage brazing filler metal with a solid-liquid line of 970-1000 ℃, adopting a brazing temperature of 1040-1070 ℃ for 5-10 minutes, and connecting an inner ring assembly formed by welding the turbine casing and the guide vane with the orifice plate ring in the vacuum brazing furnace.
10. The high pressure turbine nozzle assembly multi-stage vacuum brazing process of claim 9,
after step S20, the following steps are added:
using kerosene to carry out leakage detection, checking whether the high-pressure turbine guide assembly formed after the second-stage brazing has kerosene leakage,
and under the condition of no kerosene leakage, judging that the high-pressure turbine guider component is welded to be qualified.
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