CN114888387B - Vacuum brazing device and method for turbine working blade process holes - Google Patents
Vacuum brazing device and method for turbine working blade process holes Download PDFInfo
- Publication number
- CN114888387B CN114888387B CN202210753124.1A CN202210753124A CN114888387B CN 114888387 B CN114888387 B CN 114888387B CN 202210753124 A CN202210753124 A CN 202210753124A CN 114888387 B CN114888387 B CN 114888387B
- Authority
- CN
- China
- Prior art keywords
- blade
- turbine
- filler metal
- base
- brazing
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000005219 brazing Methods 0.000 title claims abstract description 72
- 238000000034 method Methods 0.000 title claims abstract description 41
- 239000002184 metal Substances 0.000 claims abstract description 37
- 239000000945 filler Substances 0.000 claims abstract description 34
- 239000000919 ceramic Substances 0.000 claims abstract description 11
- 229910000679 solder Inorganic materials 0.000 claims description 19
- 238000003892 spreading Methods 0.000 claims description 6
- 239000010953 base metal Substances 0.000 claims description 5
- 238000003466 welding Methods 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 2
- 238000009792 diffusion process Methods 0.000 abstract description 3
- 238000005266 casting Methods 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000002981 blocking agent Substances 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
Classifications
-
- 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
- B23K1/0018—Brazing of turbine parts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A vacuum brazing device and method for a turbine working blade process hole comprises a base, a follower sink, a boss and a counter bore; the upper surface of base sets up the retinue heavy groove, and the bottom is provided with the boss in the retinue heavy groove, is provided with a plurality of counter bores on the boss, and counter bore number is the same with turbine blade apron technology hole number. The invention aims to provide a vacuum brazing device for a blade tip cover plate of a turbine working blade of an engine, which utilizes the principle that ceramic and brazing filler metal do not generate capillary action to carry out diffusion reaction, and the ceramic temperature is far higher than the brazing temperature of parts.
Description
Technical Field
The invention relates to the technical field of auxiliary vacuum brazing tools for process holes of blade tip cover plates of turbine working blades of aeroengines, in particular to a device and a method for vacuum brazing of process holes of turbine working blades.
Background
At present, in order to effectively position ceramic type turbine blades of a novel aeroengine in the casting process and ensure that ceramic cores of the blades can be fully taken out later, 3-5 phi 1.2-phi 2.0mm process holes are reserved in a blade tip cover plate of the turbine blade, and the process holes are subjected to vacuum brazing blocking by using brazing filler metal in order to consider factors such as air flow after casting is finished; the larger the size of the process hole, the less easily the brazing filler metal is controlled in the process of forming the brazing seam, thereby causing great difficulty in vacuum brazing.
Disclosure of Invention
The invention aims to provide a vacuum brazing device and method for a turbine working blade process hole, which are used for solving the problem that the larger the size of the process hole is, the more difficult the brazing filler metal is to be controlled in the process of forming a brazing seam, so that the difficulty of vacuum brazing is high.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
A vacuum brazing device for a turbine working blade process hole comprises a base, a follow-up sink, a boss and a counter bore; the upper surface of base sets up the retinue heavy groove, and the bottom is provided with the boss in the retinue heavy groove, is provided with a plurality of counter bores on the boss, and counter bore number is the same with turbine blade apron technology hole number.
Further, the base is a ceramic base.
Further, the shape of the follower sink is matched with the tip of the turbine blade.
Further, when the blade tips of the turbine blades are inserted into the follower sink, the turbine blade cover plates fall on the bosses, and the process holes in the turbine blade cover plates are in one-to-one correspondence with the counter bores in the bosses.
Further, the number of counter bores is four.
Further, the depth of the counter bore was 0.2mm.
Further, the brazing process requires that the brazing filler metal coating height is not more than 0.3mm of the height of the blade tip cover plate.
Furthermore, the solder adopts paste solder.
Further, the weight of the brazing filler metal is g, the force formed by spreading the brazing filler metal and the blade base metal due to interfacial tension under the macroscopic condition is F ', the acting force of the auxiliary clamp on the brazing filler metal is F, and the requirement of F' +F > g is met.
Further, a vacuum brazing method for the process holes of the turbine working blade comprises the following steps:
A base corresponding to the accompanying sink groove is selected according to the shape of the blade;
Injecting solder into the counter bore of the boss, controlling the quantity of the solder to meet F '+F > g, wherein the weight of the solder is g, setting the force formed by spreading the solder and the blade parent metal under macroscopic view due to interfacial tension as F', and setting the acting force of the auxiliary clamp on the solder as F;
and clamping the blade in the base within 10-30 minutes after the brazing filler metal is coated, and positioning the boss end surface of the inner cavity of the base in contact with the blade cover plate to finish welding.
Compared with the prior art, the invention has the following technical effects:
The invention aims to provide a vacuum brazing device for a blade tip cover plate of a turbine working blade of an engine, which utilizes the principle that ceramic and brazing filler metal do not generate capillary action to carry out diffusion reaction, and the ceramic temperature is far higher than the brazing temperature of parts.
The weight of the brazing filler metal is controlled to ensure that the brazing filler metal does not fall off during brazing, and the device is simple and convenient to operate; the problem that the blade tip cover plate process holes of the turbine working blades of different types are difficult to braze due to large pore diameter during vacuum brazing can be solved.
Drawings
FIG. 1 is a top view of the device;
FIG. 2 is a front view of the device;
FIG. 3 is a turbine blade cover plate process hole diagram;
FIG. 4 is a schematic illustration of a turbine blade tip cover plate process hole being solder-coated;
FIG. 5 is an illustration of the device assembled with a blade;
FIG. 6 is a simplified diagram of solder force;
Wherein:
the device comprises a base 1, a follow-up sink 2, a boss 3 and a counter bore 4.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
Referring to fig. 1 to 5, a vacuum brazing device for a turbine working blade process hole comprises a base 1, a follower sink 2, a boss 3 and a counter bore 4; the upper surface of base 1 sets up the retinue heavy groove 2, and the bottom is provided with boss 3 in the retinue heavy groove 2, is provided with a plurality of counter bores on the boss 3, and 4 numbers of counter bores are the same with turbine blade apron technology hole number.
The invention aims to provide a vacuum brazing device for a blade tip cover plate of a turbine working blade of an engine, which utilizes the principle that ceramic and brazing filler metal do not have capillary action to carry out diffusion reaction (if necessary, a blocking agent can be coated on the ceramic), the ceramic temperature is far higher than the part brazing temperature, and the device can coat brazing filler metal at the process hole of the cover plate with a certain acting force during vacuum brazing, so that the brazing filler metal does not fall off due to the action of gravity during vacuum brazing and can completely seal the process hole.
The device is made of ceramic materials according to the following type of the blade tip area, the whole device is of a square structure, the lower end of the device is of a large plane, the upper end of the device is made into a die according to the following type of the blade tip area, the boss end face of the inner cavity of the device is in contact with the blade cover plate, the inner wall of the device is used for assisting in positioning the blade profile, four small pits are formed in the contact area of the boss end face and the process hole, and the height dimension of each small pit is 0.2mm, as shown in fig. 1 and 2; when in brazing, the coating and injecting height of the brazing filler metal is required to be not more than 0.3mm of the height of the blade tip cover plate, as shown in fig. 3 and 4, the blade is clamped in the device within 10-30 minutes after the brazing filler metal is coated and injected, and the long-time solidification of the paste brazing filler metal is prevented from affecting positioning, and the device is bonded in a time period.
The technical hole of the turbine blade cover plate is generally plugged by adopting paste brazing filler metal, the weight of the paste brazing filler metal is g, the brazing filler metal and the interfacial tension of the blade base metal are spread during brazing under a microcosmic condition, the brazing filler metal reacts with the blade base metal, the force formed by the brazing filler metal and the blade base metal due to the spreading of the interfacial tension under a macroscopic condition is F ', the acting force of an auxiliary clamp on the brazing filler metal is F, namely F' +F > g, and the brazing filler metal can be prevented from falling during brazing, as shown in fig. 5.
A vacuum brazing method for a turbine working blade process hole comprises the following steps:
A base corresponding to the accompanying sink groove is selected according to the shape of the blade;
Injecting solder into the counter bore of the boss, controlling the quantity of the solder to meet F '+F > g, wherein the weight of the solder is g, setting the force formed by spreading the solder and the blade parent metal under macroscopic view due to interfacial tension as F', and setting the acting force of the auxiliary clamp on the solder as F;
and clamping the blade in the base within 10-30 minutes after the brazing filler metal is coated, and positioning the boss end surface of the inner cavity of the base in contact with the blade cover plate to finish welding.
All the relevant matters of the steps involved in the foregoing embodiments of a method for vacuum brazing a process hole of a turbine rotor blade can be cited in the functional description of the functional module corresponding to a device for vacuum brazing a process hole of a turbine rotor blade in the embodiments of the present invention.
Finally, it should be noted that: the above embodiments are only for illustrating the technical aspects of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the above embodiments, it should be understood by those of ordinary skill in the art that: modifications and equivalents may be made to the specific embodiments of the invention without departing from the spirit and scope of the invention, which is intended to be covered by the claims.
Claims (6)
1. The vacuum brazing device for the turbine working blade process hole is characterized by comprising a base (1), a follower sink (2), a boss (3) and a counter bore (4); the upper surface of the base (1) is provided with a follow-up sinking groove (2), a boss (3) is arranged at the inner bottom of the follow-up sinking groove (2), a plurality of counter bores are arranged on the boss (3), and the number of the counter bores (4) is the same as the number of the process holes of the turbine blade cover plate;
the base (1) is a ceramic base;
the shape of the accompanying sink groove (2) is matched with the tip of the turbine blade;
When the blade tips of the turbine blades are inserted into the accompanying sink (2), the turbine blade cover plates fall on the bosses (3), and the process holes on the turbine blade cover plates correspond to counter bores on the bosses (3) one by one;
The weight of the brazing filler metal is g, the force formed by spreading the brazing filler metal and the blade base metal under macroscopic view due to interfacial tension is F ', the acting force of the auxiliary clamp on the brazing filler metal is F, and the gravity of the brazing filler metal with the weight of F' +F > g is satisfied.
2. A vacuum brazing apparatus for a turbine rotor blade process bore according to claim 1, wherein the number of counter bores (4) is four.
3. A vacuum brazing apparatus for a turbine rotor blade tooling hole according to claim 1 wherein the counterbore depth is 0.2mm.
4. A vacuum brazing apparatus for a process hole for a turbine rotor blade according to claim 1, wherein the brazing filler metal is required to be filled to a height of not more than 0.3mm of the height of the tip cover plate.
5. A vacuum brazing apparatus for producing a process hole for a turbine rotor blade according to claim 1, wherein the brazing filler metal is paste brazing filler metal.
6. A method of vacuum brazing a turbine rotor blade tooling hole, characterized in that a vacuum brazing apparatus based on a turbine rotor blade tooling hole according to any one of claims 1 to 5, comprises the steps of:
A base corresponding to the accompanying sink groove is selected according to the shape of the blade;
Injecting solder into the counter bore of the boss, controlling the weight of the solder to meet the weight of the solder with the weight of F '+F > being g, setting the force formed by spreading the solder and the blade parent metal due to interfacial tension as F' under macroscopic condition, and setting the acting force of the auxiliary clamp on the solder as F;
and clamping the blade in the base within 10-30 minutes after the brazing filler metal is coated, and positioning the boss end surface of the inner cavity of the base in contact with the blade cover plate to finish welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210753124.1A CN114888387B (en) | 2022-06-29 | 2022-06-29 | Vacuum brazing device and method for turbine working blade process holes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210753124.1A CN114888387B (en) | 2022-06-29 | 2022-06-29 | Vacuum brazing device and method for turbine working blade process holes |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114888387A CN114888387A (en) | 2022-08-12 |
| CN114888387B true CN114888387B (en) | 2024-10-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210753124.1A Active CN114888387B (en) | 2022-06-29 | 2022-06-29 | Vacuum brazing device and method for turbine working blade process holes |
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| Country | Link |
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| CN (1) | CN114888387B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115722656A (en) * | 2022-11-02 | 2023-03-03 | 中国航发沈阳黎明航空发动机有限责任公司 | A method for plugging holes in the core removal process of hollow cast blades |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101108434A (en) * | 2007-09-04 | 2008-01-23 | 重庆圣马田机械制造有限责任公司 | Braze welding method of grease suction filter |
| CN103128389A (en) * | 2013-01-18 | 2013-06-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Welding method for process blocking of mixed gas channel of swirler |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1079309C (en) * | 1999-11-24 | 2002-02-20 | 上海交通大学 | Machining process of high-accuracy and great-depth small hole |
| US9227278B2 (en) * | 2005-10-13 | 2016-01-05 | United Technologies Corporation | Bolt hole repair technique |
| US9057271B2 (en) * | 2011-11-04 | 2015-06-16 | Siemens Energy, Inc. | Splice insert repair for superalloy turbine blades |
| CN105397223A (en) * | 2015-12-25 | 2016-03-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Production method of adsorption type hollow stator blade |
| CN113909610B (en) * | 2021-10-27 | 2023-03-10 | 中国航发沈阳黎明航空发动机有限责任公司 | High-performance brazing method for third-generation single crystal high-temperature alloy |
| CN113927126B (en) * | 2021-12-17 | 2022-05-17 | 成都和鸿科技股份有限公司 | Tool for plugging blade fabrication hole and plugging method thereof |
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2022
- 2022-06-29 CN CN202210753124.1A patent/CN114888387B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101108434A (en) * | 2007-09-04 | 2008-01-23 | 重庆圣马田机械制造有限责任公司 | Braze welding method of grease suction filter |
| CN103128389A (en) * | 2013-01-18 | 2013-06-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Welding method for process blocking of mixed gas channel of swirler |
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| CN114888387A (en) | 2022-08-12 |
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