CN113859764A - Protection device for guide blade cavity of turbine guide assembly and preparation method - Google Patents
Protection device for guide blade cavity of turbine guide assembly and preparation method Download PDFInfo
- Publication number
- CN113859764A CN113859764A CN202111156403.1A CN202111156403A CN113859764A CN 113859764 A CN113859764 A CN 113859764A CN 202111156403 A CN202111156403 A CN 202111156403A CN 113859764 A CN113859764 A CN 113859764A
- Authority
- CN
- China
- Prior art keywords
- cavity
- core
- guide
- protection
- mold
- 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.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D81/00—Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents
- B65D81/02—Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents specially adapted to protect contents from mechanical damage
- B65D81/05—Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents specially adapted to protect contents from mechanical damage maintaining contents at spaced relation from package walls, or from other contents
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C39/00—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor
- B29C39/02—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C39/00—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor
- B29C39/22—Component parts, details or accessories; Auxiliary operations
- B29C39/26—Moulds or cores
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D25/00—Details of other kinds or types of rigid or semi-rigid containers
- B65D25/02—Internal fittings
- B65D25/04—Partitions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D25/00—Details of other kinds or types of rigid or semi-rigid containers
- B65D25/38—Devices for discharging contents
- B65D25/52—Devices for discharging successive articles or portions of contents
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
Abstract
The invention provides a protection device for a guide blade cavity of a turbine guide assembly and a preparation method thereof, which can prevent a turbine guide from cutting and entering the cavity in the turning and grinding processes, have wide application range, can be produced in large quantities in batches, and have low cost and can be repeatedly used. Comprises a protective core and a turnover cover; the protective core is made of industrial silica gel, is used for filling a cavity of the guide blade and is in tight fit with the inner shape of the cavity; the protective core is fixed in the middle of one side of the turnover cover. The protection device provided by the invention can be suitable for protecting any open type complex cavity part, and has a wide application range.
Description
Technical Field
The invention belongs to the technical field of turbine guide device protection, and particularly relates to a protection device for a guide blade cavity of a turbine guide device assembly and a preparation method of the protection device.
Background
The low-pressure turbine guider is a core component of an aircraft engine, and for better cooling effect, guide vanes which are important parts of the low-pressure turbine guider are precisely cast into a complex hollow cavity, and particularly, the shape of the cavity is more complex after a guide pipe is installed; the low-pressure turbine guider is easy to enter the hollow cavity of the guide blade during the cutting generated in the machining processes of turning, grinding and the like, although the low-pressure turbine guider is a static part, the working condition is quite bad, the low-pressure turbine guider is still in the surrounding of high-temperature gas besides larger aerodynamic force and unstable pulsating load, and the cutting can block a gas film hole under the pulse load of the working state of the low-pressure guider, so that the cooling effect and the gas flow of the low-pressure turbine guider are seriously influenced, and the low-pressure turbine guider is fatigue cracked and broken even under the impact of the load, thereby further causing the failure and even scrapping of an aero-engine.
In the prior art, the low-pressure turbine guider has corresponding protective measures in the turnover and transportation processes, and the low-pressure turbine guider is protected by adopting a foam protective box mode, however, at present, the low-pressure turbine guider does not adopt any protective measures in the machining process, so that cutting and the like generated in machining are prevented from entering the interior of the low-pressure turbine guider, impurities mixed in the interior of the turbine guider can influence the working efficiency and the working quality of the turbine guider, and the normal operation of an aero-engine is influenced.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides the protection device for the guide blade cavity of the turbine guide assembly and the preparation method thereof, which can prevent the turbine guide from cutting into the cavity in the turning and grinding processes, have wide application range, can be produced in large quantities in batches, have low cost and can be repeatedly used.
The invention is realized by the following technical scheme:
a protective device for a guide blade cavity of a turbine guide assembly comprises a protective core and a turnover cover;
the protective core is made of industrial silica gel, is used for filling a cavity of the guide blade and is in tight fit with the inner shape of the cavity;
the protective core is fixed in the middle of one side of the turnover cover.
Furthermore, the shape of protection core is aircraft wing, including up end, lower terminal surface to and the side that leading edge, trailing edge, pressure surface and suction surface enclose, the lower terminal surface and flip one side fixed connection of protection core.
Further, the sectional area of the protective core is gradually reduced along the lower end face to the upper end face.
Furthermore, one side of the pressure surface of the protective core is perpendicular to the turnover cover, and one side of the suction surface is obliquely arranged from the lower end surface to the upper end surface towards one side of the pressure surface.
Further, the area of the turnover cover is not smaller than the area of the outer end face of the guide vane, and the turnover cover is used for being attached and sealed with the outer end face of the guide vane.
Furthermore, the shape of the turnover cover is consistent with that of the outer end face of the guide blade and comprises a front edge, a rear edge, an upper edge and a lower edge, wherein the front edge and the front edge of the protective core are positioned on the same side, and the upper edge and the suction surface of the protective core are positioned on the same side;
the direction from the lower edge to the upper edge of the rear edge is sequentially divided into a first plane section, an inclined section and a second plane section, the radian of the inclined section is consistent with that of a section of the suction surface of the protective core, which is close to the tail edge, and the first plane section and the second plane section are arranged in parallel with the front edge.
A preparation method of a protective device for a guide vane cavity of a turbine guide assembly comprises the following steps:
s1, filling sample paste into the cavity of the guide vane;
s2, taking out the sample paste after solidification to form a mold core;
s3, pouring the melted industrial wax into a part box;
s4, placing the mold core into solid-solution industrial wax, and taking out the mold core after the industrial wax is solidified to form a mold;
and S5, pouring the liquid industrial silica gel into the mold, taking out after solidification, and finishing the preparation of the protective device.
Further, the manufactured first protection device serves as a mold core to manufacture a next mold in the part box, the operations are repeated, the molds are manufactured in the order of 2 to the power of N, and the industrial silica gel is poured into the matrix mold group to prepare the protection device in batches.
Further, the matrix mold groups are separated by vertically and horizontally arranging separation plates.
Furthermore, after the mold core and the protection device are manufactured, the redundant parts of the mold core and the protection device are trimmed.
Compared with the prior art, the invention has the following beneficial technical effects:
according to the invention, the protective core is arranged in the cavity between the complex and special-shaped guide blades, the window of the complex cavity of the part is filled, so that the complex cavity of the part is completely closed, the protective core and the cavity of the guide blades are consistent in shape and are tightly attached, a gap is not generated between the protective core and the cavity, the possibility of cutting into the cavity is greatly reduced, and the problem possibly caused by the turbine guide is avoided as much as possible; and the turnover cover connected with the protection core is arranged, the turnover cover can serve as a handle of the protection core, the protection core is convenient to take in the using process, and the operation is convenient. The protective device provided by the invention can prevent the low-pressure turbine guider from cutting and entering a complex cavity in the turning and grinding processes, the turbine guider can normally run in the working process, the air film hole cannot be cut and blocked, the working quality of the turbine guider is ensured, the working efficiency of the turbine guider is improved, and the long-term stable operation of an aero-engine is maintained. The protection device provided by the invention can be suitable for protecting any open type complex cavity part, and has a wide application range.
The protective device is formed by pouring industrial silica gel, the silica gel has good flexibility and deformability, can be tightly attached to a complex profile window of a part, and cannot scratch the part; in addition, the industrial silica gel protective device can not react with the cutting fluid in the part processing process; and the industrial silica gel protection device can be repeatedly used, so that the cost is saved.
According to the invention, by arranging the rectangular die set, a plurality of silica gel forming protection devices can be manufactured in batch at one time, the protection requirements of a plurality of guide blade cavities of the turbine guide are met, the preparation efficiency is high, the prepared protection devices can meet the protection requirements of the same guide blade, the protection devices of guide blades in different shapes can be manufactured in batch at the same time, and the adaptability is good.
Drawings
FIG. 1 is a schematic perspective view of a protective device according to the present invention;
FIG. 2 is a left side view of the guard of the present invention;
FIG. 3 is a rear view of the guard of the present invention;
FIG. 4 is a schematic perspective view of the parts box of the present invention;
FIG. 5 is a top view of a matrix die set of the present invention;
FIG. 6 is a simplified illustration of the assembly of the guard of the present invention with the guide vane cavity in the turbine nozzle.
In the figure: the device comprises a protective core 1, a turnover cover 2, a part box 3, a partition plate 4, a matrix mold group 5, industrial wax 6, a mold 7, guide blades 8, a protective device 9 and guide blade outer end faces 10.
Detailed Description
The present invention will now be described in further detail with reference to the attached drawings, which are illustrative, but not limiting, of the present invention.
As shown in fig. 1-3, the protection device for the guide vane cavity of the turbine guide assembly comprises a protection core 1 and a turnover cover 2; the protective core 1 is made of industrial silica gel and is used for filling a cavity of the guide vane 8 and is in tight fit with the inner shape of the cavity; the protective core 1 is fixed in the middle of one side of the flip cover 2.
According to the invention, the protective core 1 is arranged in the cavity between the complex and special-shaped guide blades 8, the window of the complex cavity of the part is filled, so that the complex cavity of the part is completely closed, the protective core 1 and the cavity of the guide blades 8 are consistent in shape and are tightly attached, a gap is not generated between the protective core 1 and the cavity, the possibility of cutting into the cavity is greatly reduced, and the problem possibly caused by the turbine guide is avoided as much as possible; and be provided with flip 2 of being connected with protection core 1, flip 2 can act as the handle of protection core 1, is convenient for take in the protection core 1 use, convenient operation. The protection device 9 can prevent the low-pressure turbine guider from cutting and entering a complex cavity in the turning and grinding processes, the turbine guider can normally run in the working process, the air film hole cannot be cut and blocked, the working quality of the turbine guider is ensured, the working efficiency of the turbine guider is improved, and the long-term stable operation of the aero-engine is maintained. The protection device 9 provided by the invention can be suitable for protecting any open type complex cavity part, and has a wide application range.
The protective device 9 is formed by pouring industrial silica gel, the silica gel has good flexibility and deformability, can be tightly attached to a complex profile window of a part, and cannot scratch the part; in addition, the industrial silica gel protective device 9 can not react with the cutting fluid in the part processing process; and industrial silica gel protector 9 can used repeatedly, practices thrift the cost.
Further, as shown in fig. 1, the protective core 1 is shaped like an airplane wing, and includes an upper end surface, a lower end surface, and a side surface surrounded by a front edge, a tail edge, a pressure surface and a suction surface, and the lower end surface of the protective core 1 is fixedly connected with one side of the flip cover 2.
Further, the sectional area of the shield core 1 is gradually reduced along the lower end surface to the upper end surface.
Further, the pressure surface side of the protection core 1 is perpendicular to the flip cover 2, and the suction surface side is inclined from the lower end surface to the upper end surface toward the pressure surface side.
Further, the area of the flip cover 2 is not smaller than the area of the outer end face 10 of the guide blade, and the flip cover is used for being attached and sealed with the outer end face 10 of the guide blade, so that the protection capability of the protection device 9 can be further improved, and the sealing performance is enhanced.
Further, the shape of the turnover cover 2 is consistent with that of the outer end face 10 of the guide blade, and the turnover cover comprises a front edge, a rear edge, an upper edge and a lower edge, wherein the front edge and the front edge of the protection core 1 are positioned on the same side, and the upper edge and the suction surface of the protection core 1 are positioned on the same side;
the rear edge is sequentially divided into a first plane section, an inclined section and a second plane section along the direction from the lower end surface to the upper end surface, the radian of the inclined section is consistent with that of a section of the suction surface of the protective core 1, which is close to the tail edge, and the first plane section and the second plane section are arranged in parallel with the front edge.
The protective device 9 according to the invention is also suitable for use in hollow cavities in the inner skirt part of guide vanes.
As shown in fig. 4 and 5, a method for preparing a protection device of a turbine guide cavity comprises the following steps:
s1, filling sample paste into the cavity of the guide vane 8;
s2, taking out the sample paste after solidification to form a mold core;
s3, pouring the melted industrial wax 6 into a part box 3;
s4, placing the mold core into the solid-solution industrial wax 6, and taking out the mold core after the industrial wax 6 is solidified to form a mold (7);
and S5, pouring the liquid industrial silica gel into the mold 7, taking out after solidification, and finishing the preparation of the protection device 9.
Further, the manufactured first protection device 9 serves as a mold core to manufacture the next mold 7 in the part box 3, the operations are repeated, the molds 7 are manufactured in a 2N power mode sequentially, the industrial silica gel batch preparation protection devices 9 are poured after the matrix mold group 5 is formed, the protection devices 9 manufactured by the manufacturing method provided by the invention are strong in uniformity, the protection requirements of the same guide blade can be met, the protection devices 9 of the guide blades in different shapes can be manufactured in batches at the same time, the manufacturing efficiency is high, and the adaptability is good.
Further, after the mold core and the protector 9 are manufactured, the redundant parts of the mold core and the protector are trimmed.
Further, the matrix mold group 5 is partitioned by the partition plates 4 arranged vertically and horizontally, so that mutual influence between a plurality of protective devices 9 manufactured at the same time is avoided.
Because the turbine guider comprises a plurality of guide blades 8, a plurality of silica gel forming protective devices 9 can be manufactured in batches at one time by arranging a plurality of groups of matrix mould groups 5, the protective requirements of cavities of the guide blades 8 of the turbine guider are met, and the preparation efficiency is improved.
Further, the shape and the size of the part boxes 3 are the same, the manufacturing uniformity of the protective mold 7 can be ensured as much as possible, the problem that the prepared protective device 9 is not adaptive is avoided, and the resource waste is reduced as much as possible.
Further, as shown in fig. 6, before machining processes such as turning and grinding, the protecting device 9 is plugged into the cavity of the guide vane 8 and tightly attached to completely seal the cavity of the guide vane 8, and the using method of the protecting device for the turbine guide cavity is simple to operate and convenient to use.
Claims (10)
1. The protection device for the guide blade cavity of the turbine guide assembly is characterized by comprising a protection core (1) and a turnover cover (2);
the protective core (1) is made of industrial silica gel, is used for filling a cavity of the guide blade (8), and is in tight fit with the inner shape of the cavity;
the protective core (1) is fixed in the middle of one side of the flip cover (2).
2. The protection device for the guide blade cavity of the turbine guide assembly according to claim 1, wherein the protection core (1) is in the shape of an airplane wing and comprises an upper end surface, a lower end surface and a side surface enclosed by a front edge, a tail edge, a pressure surface and a suction surface, and the lower end surface of the protection core (1) is fixedly connected with one side of the flip cover (2).
3. The device for shielding the cavity of the guide vane of the turbine guide assembly as claimed in claim 2, wherein the cross-sectional area of the shielding core (1) is gradually reduced from the lower end surface to the upper end surface.
4. The protection device for the guide blade cavity of the turbine guide assembly according to claim 2, wherein the pressure surface side of the protection core (1) is arranged perpendicular to the flip cover (2), and the suction surface side is arranged obliquely from the lower end surface to the upper end surface towards the pressure surface side.
5. The protection device for the guide vane cavity of the turbine guide vane component is characterized in that the area of the turnover cover (2) is not less than that of the outer end face (10) of the guide vane, and the turnover cover is used for being in fit sealing with the outer end face (10) of the guide vane.
6. The protection device of the guide vane cavity of the turbine guide vane component is characterized in that the flip cover (2) is in the same shape with the outer end surface (10) of the guide vane and comprises a front edge, a rear edge, an upper edge and a lower edge, wherein the front edge and the front edge of the protection core (1) are positioned on the same side, and the upper edge and the suction surface of the protection core (1) are positioned on the same side;
the direction from the lower edge to the upper edge of the rear edge is sequentially divided into a first plane section, an inclined section and a second plane section, the radian of the inclined section is consistent with that of a section of the suction surface of the protective core (1) close to the tail edge, and the first plane section and the second plane section are arranged in parallel with the front edge.
7. A method for preparing a protection device based on a turbine guide assembly guide vane cavity of any one of the claims 1-6, which is characterized by comprising the following steps:
s1, filling sample paste into the cavity of the guide vane (8);
s2, taking out the sample paste after solidification to form a mold core;
s3, pouring the melted industrial wax (6) into a part box (3);
s4, putting the mold core into the solid-solution industrial wax (6), and taking out the mold core after the industrial wax (6) is solidified to form a mold (7);
s5, pouring the liquid industrial silica gel into the mold (7), taking out after solidification, and finishing the preparation of the protective device (9).
8. The method for preparing the protective device of the guide blade cavity of the turbine guide assembly is characterized in that the manufactured first protective device (9) is used as a mold core to manufacture the next mold (7) in the part box (3), the operations are repeated, the molds (7) are manufactured in the power of 2N in sequence, and the industrial silica gel batch preparation protective device (9) is poured after the matrix mold group (5) is formed.
9. The method for preparing a protection device of a turbine guide assembly guide vane cavity according to claim 7, wherein the matrix mold set (5) is divided by arranging partition plates (4) in a longitudinal and transverse direction.
10. The method for preparing a device for protecting a cavity of a guide blade of a turbine guide assembly according to claim 7, wherein after the mold core and the protecting device (9) are manufactured, the excess parts of the mold core and the protecting device are trimmed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111156403.1A CN113859764B (en) | 2021-09-29 | 2021-09-29 | Protection device for guide blade cavity of turbine guide assembly and preparation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111156403.1A CN113859764B (en) | 2021-09-29 | 2021-09-29 | Protection device for guide blade cavity of turbine guide assembly and preparation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113859764A true CN113859764A (en) | 2021-12-31 |
| CN113859764B CN113859764B (en) | 2023-04-07 |
Family
ID=79000960
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111156403.1A Active CN113859764B (en) | 2021-09-29 | 2021-09-29 | Protection device for guide blade cavity of turbine guide assembly and preparation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113859764B (en) |
Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB440296A (en) * | 1934-12-03 | 1935-12-24 | Erik Gustaf Akerlund | Improvements in and relating to methods of casting |
| US4247508A (en) * | 1979-12-03 | 1981-01-27 | Hico Western Products Co. | Molding process |
| GB2150875A (en) * | 1983-12-07 | 1985-07-10 | Rolls Royce | Investment casting |
| US5232610A (en) * | 1989-09-15 | 1993-08-03 | Mclaughlin Timothy M | Mold element construction |
| CN1270859A (en) * | 2000-04-29 | 2000-10-25 | 华中理工大学 | Fast metal mold producing technology |
| US20040247442A1 (en) * | 2003-06-04 | 2004-12-09 | Ishikawajima-Harima Heavy Industries Co., Ltd. | Turbine blade |
| CN1718326A (en) * | 2004-07-06 | 2006-01-11 | 通用电气公司 | Casting method using a synthetic model |
| EP1889680A1 (en) * | 2006-08-16 | 2008-02-20 | Siemens Aktiengesellschaft | Process of welding of turbine components using a ceramic core introduced in an hollow part of the turbine component |
| CN103801655A (en) * | 2012-11-14 | 2014-05-21 | 深圳市金宝盈珠宝首饰有限公司 | Technology for fabricating precision casting wax metal mold |
| CN106142414A (en) * | 2016-07-29 | 2016-11-23 | 柳州快速制造工程技术有限公司 | A kind of method utilizing silica gel mould manufactured parts |
| CN205821480U (en) * | 2016-06-30 | 2016-12-21 | 龚典局 | Al alloy parts screwed hole protection plug in anode oxidation process |
| US20170217065A1 (en) * | 2016-02-01 | 2017-08-03 | A. Finkl & Sons Co. | Economical Plastic tooling cores for mold & die sets |
| CN107568308A (en) * | 2017-10-12 | 2018-01-12 | 江苏雨润肉食品有限公司 | A kind of square ham batch mould |
| CN107838372A (en) * | 2017-10-25 | 2018-03-27 | 中国航发航空动力股份有限公司 | One kind is without surplus essence casting turborotor dimension control method |
| CN209999546U (en) * | 2019-05-29 | 2020-01-31 | 江苏润德医用材料有限公司 | medicinal rubber plug mould |
| KR20200029837A (en) * | 2018-09-11 | 2020-03-19 | 두산중공업 주식회사 | Turbine blade, method for manufacturing turbine blade and gas turbine |
| CN111702351A (en) * | 2020-06-30 | 2020-09-25 | 中国航发动力股份有限公司 | Integrated manufacturing method of turbine blade air film hole based on ceramic core |
| CN112622132A (en) * | 2020-11-30 | 2021-04-09 | 中南大学 | Silica gel cavity lost foam casting mold and method |
| CN112797922A (en) * | 2019-11-13 | 2021-05-14 | 中国航发南方工业有限公司 | Use method of measuring needle for measuring angle of small micropore of blade |
| CN113320670A (en) * | 2021-08-03 | 2021-08-31 | 深之蓝海洋科技股份有限公司 | Propeller and manufacturing method thereof |
| CN214111175U (en) * | 2020-10-28 | 2021-09-03 | 上海亮黑科技有限公司 | A mould for making silica gel stopper |
-
2021
- 2021-09-29 CN CN202111156403.1A patent/CN113859764B/en active Active
Patent Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB440296A (en) * | 1934-12-03 | 1935-12-24 | Erik Gustaf Akerlund | Improvements in and relating to methods of casting |
| US4247508A (en) * | 1979-12-03 | 1981-01-27 | Hico Western Products Co. | Molding process |
| US4247508B1 (en) * | 1979-12-03 | 1996-10-01 | Dtm Corp | Molding process |
| GB2150875A (en) * | 1983-12-07 | 1985-07-10 | Rolls Royce | Investment casting |
| US5232610A (en) * | 1989-09-15 | 1993-08-03 | Mclaughlin Timothy M | Mold element construction |
| CN1270859A (en) * | 2000-04-29 | 2000-10-25 | 华中理工大学 | Fast metal mold producing technology |
| US20040247442A1 (en) * | 2003-06-04 | 2004-12-09 | Ishikawajima-Harima Heavy Industries Co., Ltd. | Turbine blade |
| CN1718326A (en) * | 2004-07-06 | 2006-01-11 | 通用电气公司 | Casting method using a synthetic model |
| EP1889680A1 (en) * | 2006-08-16 | 2008-02-20 | Siemens Aktiengesellschaft | Process of welding of turbine components using a ceramic core introduced in an hollow part of the turbine component |
| CN103801655A (en) * | 2012-11-14 | 2014-05-21 | 深圳市金宝盈珠宝首饰有限公司 | Technology for fabricating precision casting wax metal mold |
| US20170217065A1 (en) * | 2016-02-01 | 2017-08-03 | A. Finkl & Sons Co. | Economical Plastic tooling cores for mold & die sets |
| CN205821480U (en) * | 2016-06-30 | 2016-12-21 | 龚典局 | Al alloy parts screwed hole protection plug in anode oxidation process |
| CN106142414A (en) * | 2016-07-29 | 2016-11-23 | 柳州快速制造工程技术有限公司 | A kind of method utilizing silica gel mould manufactured parts |
| CN107568308A (en) * | 2017-10-12 | 2018-01-12 | 江苏雨润肉食品有限公司 | A kind of square ham batch mould |
| CN107838372A (en) * | 2017-10-25 | 2018-03-27 | 中国航发航空动力股份有限公司 | One kind is without surplus essence casting turborotor dimension control method |
| KR20200029837A (en) * | 2018-09-11 | 2020-03-19 | 두산중공업 주식회사 | Turbine blade, method for manufacturing turbine blade and gas turbine |
| CN209999546U (en) * | 2019-05-29 | 2020-01-31 | 江苏润德医用材料有限公司 | medicinal rubber plug mould |
| CN112797922A (en) * | 2019-11-13 | 2021-05-14 | 中国航发南方工业有限公司 | Use method of measuring needle for measuring angle of small micropore of blade |
| CN111702351A (en) * | 2020-06-30 | 2020-09-25 | 中国航发动力股份有限公司 | Integrated manufacturing method of turbine blade air film hole based on ceramic core |
| CN214111175U (en) * | 2020-10-28 | 2021-09-03 | 上海亮黑科技有限公司 | A mould for making silica gel stopper |
| CN112622132A (en) * | 2020-11-30 | 2021-04-09 | 中南大学 | Silica gel cavity lost foam casting mold and method |
| CN113320670A (en) * | 2021-08-03 | 2021-08-31 | 深之蓝海洋科技股份有限公司 | Propeller and manufacturing method thereof |
Non-Patent Citations (3)
| Title |
|---|
| 何爱杰;李世峰;李万福;刘强军;孙飞;: "世界航空发动机高压涡轮导向器研究综述" * |
| 徐亚亚等: "改善某机涡轮叶片荧光渗透检测背景过度的试验", 《无损检测》 * |
| 李剑白等: "紧凑式多功能低压涡轮导向器设计", 《燃气涡轮试验与研究》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113859764B (en) | 2023-04-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111496187B (en) | Precision investment casting method for single crystal duplex hollow guide blade | |
| US4422229A (en) | Method of making an airfoil member for a gas turbine engine | |
| US4417381A (en) | Method of making gas turbine engine blades | |
| US7993106B2 (en) | Core for use in a casting mould | |
| US5609470A (en) | Turbomachine aerofoil with concave surface irregularities | |
| CN109483183B (en) | Manufacturing method of metal reinforcing edge of composite fan blade of aero-engine | |
| CN113859764B (en) | Protection device for guide blade cavity of turbine guide assembly and preparation method | |
| US3866448A (en) | Apparatus for constructing air cooled turbomachinery blading | |
| GB2542882A (en) | Core for the moulding of a blade having superimposed cavities and including a de-dusting hole traversing a cavity from end to end | |
| CN104690229B (en) | A kind of turbojet engine tail sprays foundry engieering | |
| CN204357771U (en) | A kind of metal stiffened edge, fan blade and turbogenerator | |
| CN110328359A (en) | Narrow interval, distortion, multiple-blade dense distribution leaf grating class part manufacturing process | |
| US20150202702A1 (en) | Gas turbine engine cast structure method for finishing | |
| CN111659856B (en) | Concatemer solid blade pouring system and pouring method | |
| CN204164033U (en) | Hollow fan blade for aircraft engine | |
| CN113422124A (en) | Uniform-temperature liquid cooling plate and manufacturing method thereof | |
| EP2551456B1 (en) | Platform interconnected with mid-body core interface for molding airfoil platforms | |
| CN217373560U (en) | Hot-proof lid RTM fills mould | |
| CN217701238U (en) | Gating system of high-voltage switch aluminum casting | |
| CN217831774U (en) | Piston mould with exhaust structure | |
| CN109353024A (en) | A kind of multiple material forming method of aircraft aileron J-type rib | |
| CN211803746U (en) | Rotor cast aluminum die of explosion-proof three-phase asynchronous motor | |
| CN213063682U (en) | Turbine disc structure with three inner ring cavities | |
| CN216505830U (en) | Ceramic mold convenient to disassemble | |
| CN212634281U (en) | Core removal system and core removal tool thereof |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |