CN111926151A - CFD (computational fluid dynamics) -assisted laser solid solution strengthening method for turbine blade - Google Patents
CFD (computational fluid dynamics) -assisted laser solid solution strengthening method for turbine blade Download PDFInfo
- Publication number
- CN111926151A CN111926151A CN202010832800.5A CN202010832800A CN111926151A CN 111926151 A CN111926151 A CN 111926151A CN 202010832800 A CN202010832800 A CN 202010832800A CN 111926151 A CN111926151 A CN 111926151A
- Authority
- CN
- China
- Prior art keywords
- solid solution
- laser
- blade
- solution strengthening
- cfd
- Prior art date
- 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.)
- Pending
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/06—Surface hardening
- C21D1/09—Surface hardening by direct application of electrical or wave energy; by particle radiation
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Laser Beam Processing (AREA)
- Heat Treatment Of Articles (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A laser solid solution strengthening method for a turbine blade based on CFD assistance relates to a laser solid solution strengthening method for a turbine blade. The problem that the last-stage blade of the low-pressure cylinder is prone to breaking and damage after water erosion is solved. The method comprises the following steps: performing pneumatic calculation on the last-stage blade of the low-pressure cylinder by using ANSYS CFX software, and confirming a solid solution area on the last-stage blade of the low-pressure cylinder; cleaning a solid solution area, assembling the blade on a fixed clamp, carrying out laser solid solution strengthening in the solid solution area, and finally carrying out aging heat treatment. The method judges the laser solid solution area according to the low-load operation condition, can improve the strength, toughness, corrosion resistance and oxidation resistance of the last-stage blade after the laser solid solution, reduces the vicious accidents of blade fracture and the like caused by water erosion, and has simpler and more convenient process. The invention is suitable for laser solid solution strengthening of the turbine blade.
Description
Technical Field
The invention relates to a laser solid solution strengthening method for a turbine blade.
Background
With the implementation of the national deep peak regulation policy, the high-power steam turbine is often set with regenerative steam extraction to meet various industrial requirements, and a large amount of steam extraction leads to a severe working environment of the last-stage blade of the low-pressure cylinder. The flowing water drops contained in the steam impact the last-stage blade, so that the last-stage blade is subjected to severe water erosion, and the severe water erosion of the blade can cause the blade to break and damage, so that the unit is subjected to strong vibration. In general, in order to increase the erosion resistance, wear resistance, etc. of the last stage blade, the erosion and erosion resistance of the last stage blade is often enhanced by laser solid solution strengthening. With the increase of low-load operation conditions of the steam turbine, it is difficult to accurately determine the laser solid solution area of the last-stage blade only by manpower, and meanwhile, the last-stage blade of the low-pressure cylinder is treated by adopting more effective measures to realize the water erosion resistance.
Disclosure of Invention
The invention provides a CFD (circulating fluid dynamics) assistance-based laser solid solution strengthening method for a turbine blade, aiming at solving the problem that a last-stage blade of a low-pressure cylinder is easy to break and destroy after being subjected to water erosion.
The invention relates to a CFD (computational fluid dynamics) -assisted laser solid solution strengthening method for a turbine blade, which is carried out according to the following steps:
firstly, carrying out pneumatic calculation on a low-pressure cylinder final-stage blade by using ANSYS CFX software, and confirming a solid solution area on the low-pressure cylinder final-stage blade;
secondly, cleaning a solid solution area, assembling the blade on a fixed clamp, and carrying out laser solid solution strengthening in the solid solution area;
thirdly, aging heat treatment:
the blade root of the last-stage blade of the low-pressure cylinder after laser solution treatment is vertically placed downwards, and the distance between steam inlet edges of the solid solution areas of the last-stage blades of the adjacent low-pressure cylinders is not less than 20mm so as to ensure that the solid solution areas are uniformly heated; the aging heat treatment temperature is 475-485 ℃, and the heat preservation time is 3.5-4.5 h;
the invention has the following principle and the following beneficial effects:
the invention provides a method for determining laser solid solution strengthening parameters of a turbine blade based on CFD (computational fluid dynamics) analysis, which can judge a laser solid solution area according to a low-load operation condition, improve the strength, toughness, corrosion resistance and oxidation resistance of a last-stage blade after laser solid solution, and reduce severe accidents such as blade fracture and the like caused by water erosion, thereby prolonging the service life of the blade, prolonging the operation life of the whole unit, being beneficial to reducing the operation cost and improving the economy of the whole unit. The invention determines the laser solid solution strengthening area, the laser solid solution strength and the aging heat treatment through CFD calculation, and realizes integration from design to processing, so that the whole process is simpler and more convenient.
Detailed Description
The technical scheme of the invention is not limited to the specific embodiments listed below, and any reasonable combination of the specific embodiments is included.
The first embodiment is as follows: the laser solid solution strengthening method for the turbine blade based on CFD assistance in the embodiment is carried out according to the following steps:
firstly, carrying out pneumatic calculation on a low-pressure cylinder final-stage blade by using ANSYS CFX software, and confirming a solid solution area on the low-pressure cylinder final-stage blade;
secondly, cleaning a solid solution area, assembling the blade on a fixed clamp, and carrying out laser solid solution strengthening in the solid solution area;
thirdly, aging heat treatment:
the blade root of the last-stage blade of the low-pressure cylinder after laser solution treatment is vertically placed downwards, and the distance between steam inlet edges of the solid solution areas of the last-stage blades of the adjacent low-pressure cylinders is not less than 20mm so as to ensure that the solid solution areas are uniformly heated; the aging heat treatment temperature is 475-485 ℃, and the heat preservation time is 3.5-4.5 h.
The embodiment provides a method for determining laser solid solution strengthening parameters of a turbine blade based on CFD (computational fluid dynamics) analysis, which can judge a laser solid solution area according to a low-load operation condition, improve the strength, toughness, corrosion resistance and oxidation resistance of a last-stage blade after laser solid solution, and reduce severe accidents such as blade fracture and the like caused by water erosion, thereby prolonging the service life of the blade, prolonging the operation life of the whole unit, being beneficial to reducing the operation cost and improving the economy of the whole unit. In the embodiment, the laser solid solution strengthening area, the laser solid solution strength and the aging heat treatment are determined by CFD calculation and are a whole set of standard operation, and integration is realized from design to processing, so that the whole process is simpler and more convenient.
The second embodiment is as follows: the first difference between the present embodiment and the specific embodiment is: step one, the material of the last stage blade of the low-pressure cylinder is 05Cr17Ni4Cu4Nb (17-4 PH).
The third concrete implementation mode: the present embodiment differs from the first or second embodiment in that: step two, the solid solution area cleaning method comprises the following steps: and dipping clean wiping cloth into alcohol, and wiping the laser solid solution area of the part to remove oil stains and dirt in the solid solution area.
The fourth concrete implementation mode: the difference between this embodiment mode and one of the first to third embodiment modes is: and secondly, the scanning speed during the laser solid solution strengthening is 1.5-2.5 m/s.
The fifth concrete implementation mode: the difference between this embodiment and one of the first to fourth embodiments is: and step two, when the laser is subjected to solid solution strengthening, the power of the laser beam in the solid solution area is 640-660W, and the power of the laser beam at the edge of the solid solution area is 690-710W.
The sixth specific implementation mode: the difference between this embodiment and one of the first to fifth embodiments is: and cooling the obtained product to 200 ℃ along with the furnace after the third aging heat treatment, taking out the obtained product, and naturally cooling the obtained product in the air.
Example 1:
the laser solid solution strengthening method for the turbine blade based on CFD assistance in the embodiment is carried out according to the following steps: the material of the final stage blade of the low pressure cylinder is 05Cr17Ni4Cu4 Nb;
firstly, carrying out pneumatic calculation on a low-pressure cylinder final-stage blade by using ANSYS CFX software, and confirming a solid solution area on the low-pressure cylinder final-stage blade;
secondly, cleaning a solid solution area, assembling the blade on a fixed clamp, and carrying out laser solid solution strengthening in the solid solution area;
the solid solution area cleaning method comprises the following steps: dipping clean wiping cloth into alcohol, and wiping the laser solid solution area of the part to remove oil stains and dirt in the solid solution area;
the scanning speed is 2m/s during the laser solid solution strengthening;
the laser beam power in the solid solution area is 650W and the laser beam power at the edge of the solid solution area is 700W during the laser solid solution strengthening;
when the blade is assembled on a fixed clamp, the blade is not collided; and closing a laser solid solution chamber door during laser solid solution strengthening, confirming a laser power number and a program path of a solid solution area, wearing laser protective glasses, operating a program to carry out laser solid solution, closing a laser and taking down the blade after the program is checked to be qualified.
Thirdly, aging heat treatment:
the blade root of the last-stage blade of the low-pressure cylinder after laser solution treatment is vertically placed downwards, and the distance between steam inlet edges of the solid solution areas of the last-stage blades of the adjacent low-pressure cylinders is not less than 20mm so as to ensure that the solid solution areas are uniformly heated; the aging heat treatment temperature is 480 ℃, and the heat preservation time is 4 h;
cooling the obtained product to 200 ℃ along with the furnace after the third aging heat treatment, taking out the obtained product, and naturally cooling the obtained product in the air;
the embodiment provides a method for determining laser solid solution strengthening parameters of a turbine blade based on CFD (computational fluid dynamics) analysis, which can judge a laser solid solution region according to a low-load operation condition, improve the strength, toughness, corrosion resistance and oxidation resistance of a last-stage blade after laser solid solution, and reduce severe accidents such as blade fracture and the like caused by water erosion, thereby prolonging the service life of the blade, prolonging the operation life of the whole unit, being beneficial to reducing the operation cost and improving the economy of the whole unit. In the embodiment, the laser solid solution strengthening area, the laser solid solution strength and the aging heat treatment are determined by CFD calculation and are a whole set of standard operation, and integration is realized from design to processing, so that the whole process is simpler and more convenient.
Claims (6)
1. A laser solid solution strengthening method for a turbine blade based on CFD assistance is characterized by comprising the following steps: the method comprises the following steps:
firstly, carrying out pneumatic calculation on a low-pressure cylinder final-stage blade by using ANSYS CFX software, and confirming a solid solution area on the low-pressure cylinder final-stage blade;
secondly, cleaning a solid solution area, assembling the blade on a fixed clamp, and carrying out laser solid solution strengthening in the solid solution area;
thirdly, aging heat treatment:
the blade root of the last-stage blade of the low-pressure cylinder after laser solution treatment is vertically placed downwards, and the distance between steam inlet edges of the solid solution areas of the last-stage blades of the adjacent low-pressure cylinders is not less than 20mm so as to ensure that the solid solution areas are uniformly heated; the aging heat treatment temperature is 475-485 ℃, and the heat preservation time is 3.5-4.5 h.
2. The CFD assistance-based steam turbine blade laser solid solution strengthening method according to claim 1, wherein the method comprises the following steps: step one, the material of the last stage blade of the low-pressure cylinder is 05Cr17Ni4Cu4 Nb.
3. The CFD assistance-based steam turbine blade laser solid solution strengthening method according to claim 1, wherein the method comprises the following steps: step two, the solid solution area cleaning method comprises the following steps: and dipping clean wiping cloth into alcohol, and wiping the laser solid solution area of the part to remove oil stains and dirt in the solid solution area.
4. The CFD assistance-based steam turbine blade laser solid solution strengthening method according to claim 1, wherein the method comprises the following steps: and secondly, the scanning speed during the laser solid solution strengthening is 1.5-2.5 m/s.
5. The CFD assistance-based steam turbine blade laser solid solution strengthening method according to claim 1, wherein the method comprises the following steps: and step two, when the laser is subjected to solid solution strengthening, the power of the laser beam in the solid solution area is 640-660W, and the power of the laser beam at the edge of the solid solution area is 690-710W.
6. The CFD assistance-based steam turbine blade laser solid solution strengthening method according to claim 1, wherein the method comprises the following steps: and cooling the obtained product to 200 ℃ along with the furnace after the third aging heat treatment, taking out the obtained product, and naturally cooling the obtained product in the air.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010832800.5A CN111926151A (en) | 2020-08-18 | 2020-08-18 | CFD (computational fluid dynamics) -assisted laser solid solution strengthening method for turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010832800.5A CN111926151A (en) | 2020-08-18 | 2020-08-18 | CFD (computational fluid dynamics) -assisted laser solid solution strengthening method for turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111926151A true CN111926151A (en) | 2020-11-13 |
Family
ID=73304581
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010832800.5A Pending CN111926151A (en) | 2020-08-18 | 2020-08-18 | CFD (computational fluid dynamics) -assisted laser solid solution strengthening method for turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111926151A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114790507A (en) * | 2021-01-25 | 2022-07-26 | 大族激光科技产业集团股份有限公司 | Steam turbine blade and method of strengthening the same |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040146402A1 (en) * | 2003-01-27 | 2004-07-29 | Mitsubishi Heavy Industries, Ltd. | Turbine moving blade and gas turbine |
| CN101333584A (en) * | 2008-07-30 | 2008-12-31 | 无锡透平叶片有限公司 | Laser heat treatment vulcanized process for leading edge of blade |
| CN109355490A (en) * | 2018-10-17 | 2019-02-19 | 广东工业大学 | The processing method that a kind of laser shock in oblique angle strengthens complex parts |
-
2020
- 2020-08-18 CN CN202010832800.5A patent/CN111926151A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040146402A1 (en) * | 2003-01-27 | 2004-07-29 | Mitsubishi Heavy Industries, Ltd. | Turbine moving blade and gas turbine |
| CN101333584A (en) * | 2008-07-30 | 2008-12-31 | 无锡透平叶片有限公司 | Laser heat treatment vulcanized process for leading edge of blade |
| CN109355490A (en) * | 2018-10-17 | 2019-02-19 | 广东工业大学 | The processing method that a kind of laser shock in oblique angle strengthens complex parts |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114790507A (en) * | 2021-01-25 | 2022-07-26 | 大族激光科技产业集团股份有限公司 | Steam turbine blade and method of strengthening the same |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106756253B (en) | Brush seal high-performance high-temperature nickel-base alloy brush filament material | |
| CN104060191B (en) | A kind of turbine blade and production technique thereof improving impact toughness | |
| CN111926151A (en) | CFD (computational fluid dynamics) -assisted laser solid solution strengthening method for turbine blade | |
| CN108220851A (en) | A kind of hardware and its processing method | |
| CN111823063B (en) | Surface treatment method and application of high-temperature alloy return | |
| CN104060192B (en) | A kind of turbine blade and production technique thereof improving water erosion resistent ability | |
| CN104032236A (en) | Turbine blade capable of improving thermal cracking resistance and production process thereof | |
| CN104032239B (en) | A kind of corrosion-resistant turbine blade and production technique thereof | |
| CN100417743C (en) | Boronizing treatment and heat treatment process of martensitic stainless steel for steam turbine nozzle set | |
| BRPI1107069A2 (en) | process for machining, especially for mechanical machining, of at least one exhaust gas conductive surface region of an internal combustion engine component or sump as well as internal combustion engine sump and cylinder liner | |
| CN101629296B (en) | Remover composite for removing nickel-chromium-aluminum-yttrium coating and method thereof | |
| CN104046919B (en) | A kind of high life turbine blade and production technique thereof | |
| CN103602791A (en) | Grooved-roller laser surface treatment method | |
| CN110977354A (en) | Production process of fuel tank hoop | |
| CN105177602A (en) | Alloy surface derusting technique | |
| CN1603052A (en) | Laser strengthening process for metal leaf | |
| CN102269668B (en) | Testing method for performing rapid water quenching on compression test sample | |
| CN105834670A (en) | Technological method for preventing delayed cracks of idler wheel | |
| CN211005487U (en) | Gear ring high-frequency quenching machine with steam prevention function | |
| CN104419883A (en) | Method for intensifying plasma beam on surface of combustion chamber of aluminum piston of internal combustion engine | |
| KR0149700B1 (en) | Method for manufacturing dove tail for turbine blade | |
| CN102764959B (en) | Manufacturing technique of 150-300mm thick low-alloy high-strength steel plate | |
| CN110293379A (en) | A kind of processing method of martensite steel inlet valve discone antenna surface | |
| CN101892362A (en) | Hardening and tempering method in pump body manufacturing | |
| CN113231585B (en) | Forging process for stainless steel gasoline 500bar high-pressure oil rail |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20201113 |
|
| RJ01 | Rejection of invention patent application after publication |