CN112981304A - Thermal spraying sealing method - Google Patents
Thermal spraying sealing method Download PDFInfo
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- CN112981304A CN112981304A CN202110205792.6A CN202110205792A CN112981304A CN 112981304 A CN112981304 A CN 112981304A CN 202110205792 A CN202110205792 A CN 202110205792A CN 112981304 A CN112981304 A CN 112981304A
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- Prior art keywords
- spraying
- sealing
- nickel
- sand blasting
- coating
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/129—Flame spraying
Abstract
The invention discloses a thermal spraying sealing method, relates to the field of engines, and aims to solve the problems of large through-flow gap and low unit efficiency caused by relative scraping and abrasion of a grate tooth and a sealing ring of a gas turbine or an aero-engine. The method of the invention is to seal and coat an abradable seal coating on the stator sealing ring and seal and coat a wear-resistant coating on the corresponding labyrinth. The abradable seal coating obtained by the atmosphere plasma spraying method has excellent abradability, and the nickel-chromium carbide or tungsten carbide-cobalt coating obtained by the supersonic flame spraying method has excellent wear resistance. Under the cooperation of the two, the scraping abrasion during high-speed rotation can be reduced to the greatest extent, and the efficiency of the unit is improved. The invention is applied to the field of gas path sealing of gas turbines and aero-engines.
Description
Technical Field
The invention relates to the field of engines, in particular to a thermal spraying sealing method.
Background
The labyrinth seal structure is a common non-contact seal structure on a gas turbine and an aeroengine, and a seal structure is formed by a seal ring on a stator and a seal labyrinth on a rotor. In order to reduce gas leakage, the clearance between the grate and the sealing ring is controlled to be small, and the grate and the sealing ring are easily abraded and scraped under the high state of a gas turbine or an aero-engine, so that the abrasion is caused, the through-flow clearance is enlarged, and the unit efficiency is reduced.
Disclosure of Invention
The invention provides a thermal spraying sealing method, aiming at solving the problems that the through-flow clearance is enlarged and the unit efficiency is reduced due to the relative scraping and abrasion of a gas turbine or an aero-engine labyrinth and a sealing ring.
The invention relates to a thermal spraying sealing method, which is characterized in that an abradable sealing coating is sealed on a stator sealing ring of a gas turbine or an aeroengine, and a wear-resistant coating is sealed on a corresponding labyrinth; the specific operation is as follows:
step one, sealing and coating a stator sealing ring of a gas turbine or an aeroengine
(1) Protection: carrying out sand blasting prevention and spraying protection on the non-spraying area of the stator sealing ring;
(2) sand blasting: carrying out sand blasting coarsening on the surface spraying area of the stator sealing ring by using 20-40 meshes of white corundum sand, wherein the sand blasting pressure is 0.4-0.6 MPa;
(3) spraying a bottom layer: spraying nickel-aluminum powder on the surface of the sealing ring by adopting an atmospheric plasma spraying mode to form a nickel-aluminum bottom layer with the thickness of 0.10-0.15 mm;
(4) spraying a surface layer: spraying aluminum-silicon-polyphenyl ester powder on the surface of the nickel-aluminum bottom layer in an atmospheric plasma spraying mode to form an aluminum-silicon-polyphenyl ester surface layer with the thickness of 1.8-2.8 mm, wherein the nickel-aluminum bottom layer and the aluminum-silicon-polyphenyl ester surface layer jointly form an abradable seal coating;
step two, sealing and coating wear-resistant coating on corresponding grid teeth
(5) Protection: carrying out sand blasting prevention and spraying protection on the non-spraying area of the grate;
(6) sand blasting: carrying out sand blasting coarsening on the spraying area on the surface of the comb tooth by using 20-40 meshes of white corundum sand, wherein the sand blasting pressure is 0.4-0.6 MPa;
(7) spraying: spraying nickel-chromium carbide or tungsten carbide-cobalt powder on the surface of the comb tooth by adopting a supersonic flame spraying mode to form a nickel-chromium carbide or tungsten carbide-cobalt wear-resistant coating with the thickness of 0.10-0.20 mm;
and (5) completing the thermal spraying sealing method through the operations of the first step and the second step.
The invention has the beneficial effects that:
the abradable seal coating obtained by the atmospheric plasma spraying mode has excellent abradability, and the nickel-chromium carbide or tungsten carbide-cobalt coating obtained by the supersonic flame spraying mode has excellent wear resistance. Under the cooperation of the two, the scraping abrasion during high-speed rotation can be reduced to the greatest extent, and the efficiency of the unit is improved.
Drawings
FIG. 1 is a schematic diagram of a thermal spray sealing method of the present invention.
Detailed Description
It will be understood by those of ordinary skill in the art that the foregoing embodiments are specific examples for carrying out the invention, and that various changes in form and details may be made therein without departing from the spirit and scope of the invention in practice.
To make the objects, aspects and advantages of the embodiments of the present invention more apparent, the following detailed description clearly illustrates the spirit of the disclosure, and any person skilled in the art, after understanding the embodiments of the disclosure, may make changes and modifications to the technology taught by the disclosure without departing from the spirit and scope of the disclosure.
The exemplary embodiments of the present invention and the description thereof are provided to explain the present invention and not to limit the present invention.
The first embodiment is as follows: the embodiment is described with reference to fig. 1, and the thermal spraying sealing method of the embodiment is to seal an abradable sealing coating on a stator sealing ring of a gas turbine or an aircraft engine and seal an abrasion-resistant coating on a corresponding labyrinth; the specific operation is as follows:
step one, sealing and coating a stator sealing ring of a gas turbine or an aeroengine
(1) Protection: carrying out sand blasting prevention and spraying protection on the non-spraying area of the stator sealing ring;
(2) sand blasting: carrying out sand blasting coarsening on the surface spraying area of the stator sealing ring by using 20-40 meshes of white corundum sand, wherein the sand blasting pressure is 0.4-0.6 MPa;
(3) spraying a bottom layer: spraying nickel-aluminum powder on the surface of the sealing ring by adopting an atmospheric plasma spraying mode to form a nickel-aluminum bottom layer with the thickness of 0.10-0.15 mm;
(4) spraying a surface layer: spraying aluminum-silicon-polyphenyl ester powder on the surface of the nickel-aluminum bottom layer in an atmospheric plasma spraying mode to form an aluminum-silicon-polyphenyl ester surface layer with the thickness of 1.8-2.8 mm, wherein the nickel-aluminum bottom layer and the aluminum-silicon-polyphenyl ester surface layer jointly form an abradable seal coating;
step two, sealing and coating wear-resistant coating on corresponding grid teeth
(5) Protection: carrying out sand blasting prevention and spraying protection on the non-spraying area of the grate;
(6) sand blasting: carrying out sand blasting coarsening on the spraying area on the surface of the comb tooth by using 20-40 meshes of white corundum sand, wherein the sand blasting pressure is 0.4-0.6 MPa;
(7) spraying: spraying nickel-chromium carbide or tungsten carbide-cobalt powder on the surface of the comb tooth by adopting a supersonic flame spraying mode to form a nickel-chromium carbide or tungsten carbide-cobalt wear-resistant coating with the thickness of 0.10-0.20 mm;
and (5) completing the thermal spraying sealing method through the operations of the first step and the second step.
The second embodiment is as follows: the present embodiment is described with reference to fig. 1, and is different from the specific embodiment in that: the hot spraying sealing is to seal and coat an abradable sealing coating 2 on a stator sealing ring 1 of a gas turbine or an aeroengine, and seal and coat a wear-resistant coating 4 on a corresponding labyrinth 3.
The rest is the same as the first embodiment.
The third concrete implementation mode: the present embodiment is described with reference to fig. 1, and is different from the specific embodiment in that: the sand blasting pressure of the first step and the second step is 0.5 MPa.
The rest is the same as the first embodiment.
The fourth concrete implementation mode: the present embodiment is described with reference to fig. 1, and is different from the specific embodiment in that: the thickness of the nickel-aluminum bottom layer in the step one is 0.12-0.14 mm.
The rest is the same as the first embodiment.
The fifth concrete implementation mode: the present embodiment is described with reference to fig. 1, and is different from the specific embodiment in that: the thickness of the aluminum silicon-polyphenyl ester surface layer in the step one is 2.0-2.5 mm.
The rest is the same as the first embodiment.
The sixth specific implementation mode: the present embodiment is described with reference to fig. 1, and is different from the specific embodiment in that: and the thickness of the nickel-chromium carbide or tungsten carbide-cobalt wear-resistant coating in the second step is 0.15-0.18 mm.
The rest is the same as the first embodiment.
The invention is not limited to the above embodiments, and one or a combination of several embodiments may also achieve the object of the invention.
Example 1
The embodiment of the thermal spraying sealing method is characterized in that an abradable sealing coating is sealed and coated on a stator sealing ring of a gas turbine or an aero-engine, and a wear-resistant coating is sealed and coated on a corresponding labyrinth
For a stator seal ring, the abradable seal coating seal process is as follows:
(1) protecting a non-spraying area: using a tool and a thermal spraying protective adhesive tape to perform sand blasting prevention and spraying protection on a non-spraying area of the sealing ring;
(2) sand blasting treatment: carrying out sand blasting and coarsening on the surface spraying area of the sealing ring, using 20-40 mesh white corundum sand, wherein the sand blasting pressure is 0.5MPa, the surface after sand blasting has no color difference, and the roughness is not lower than Ra 5.0 mu m;
(3) cleaning: cleaning the sand blasting surface by using compressed air and alcohol, removing residual sand grains and floating ash on the surface of the sealing ring, and preparing for spraying;
(4) spraying a bottom layer: spraying nickel-aluminum powder on the surface of the sealing ring spraying area by adopting an atmospheric plasma spraying mode to form a nickel-aluminum bottom layer with the thickness of 0.12 mm;
(5) spraying a surface layer: spraying aluminum silicon-polyphenyl ester powder on the surface of the nickel-aluminum bottom layer by adopting an atmospheric plasma spraying mode to form an aluminum silicon-polyphenyl ester surface layer with the thickness of 2.0mm,
(6) cleaning: removing the spraying protection device, cleaning the surface of the blade by using compressed air and alcohol, and removing residual powder, adhesive tapes and floating ash;
(7) mechanically adding: and (3) processing the abradable seal coating to the size and the roughness required by the drawing by adopting a turning machining mode so as to meet the design requirement.
For the sealing labyrinth, the sealing process of the abradable seal coating is as follows:
(1) protecting a non-spraying area: carrying out sand blasting prevention and spraying protection on the non-spraying area of the sealing comb tooth by using a special tool and a thermal spraying protection adhesive tape;
(2) sand blasting treatment: carrying out sand blasting and coarsening on the spraying area on the surface of the sealing comb tooth, using 20-40 meshes of white corundum sand, wherein the sand blasting pressure is 0.5MPa, the surface has no color difference after sand blasting, and the roughness is not lower than Ra 5.0 mu m;
(3) cleaning: cleaning the sand blasting surface by using compressed air and alcohol, removing residual sand particles and floating ash on the surface of the sealing grid tooth, and preparing for spraying;
(4) spraying: spraying nickel-chromium carbide powder on the surface of the spraying area of the sealed comb tooth by adopting a supersonic flame spraying mode to form a nickel-chromium carbide wear-resistant coating with the thickness of 0.15 mm;
(5) cleaning: and (4) removing the spraying protection device, cleaning the surface of the sealing grid tooth by using compressed air and alcohol, and removing residual powder, adhesive tape and floating ash.
The thermal spraying sealing method can reduce scraping abrasion of the labyrinth sealing structure during high-speed rotation to the maximum extent.
Example 2
The embodiment of the thermal spraying sealing method is characterized in that an abradable sealing coating is sealed and coated on a stator sealing ring of a gas turbine or an aero-engine, and a wear-resistant coating is sealed and coated on a corresponding labyrinth
For a stator seal ring, the abradable seal coating seal process is as follows:
(1) protecting a non-spraying area: using a tool and a thermal spraying protective adhesive tape to perform sand blasting prevention and spraying protection on a non-spraying area of the sealing ring;
(2) sand blasting treatment: carrying out sand blasting and coarsening on the surface spraying area of the sealing ring, using 20-40 mesh white corundum sand, wherein the sand blasting pressure is 0.5MPa, the surface after sand blasting has no color difference, and the roughness is not lower than Ra 5.0 mu m;
(3) cleaning: cleaning the sand blasting surface by using compressed air and alcohol, removing residual sand grains and floating ash on the surface of the sealing ring, and preparing for spraying;
(4) spraying a bottom layer: spraying nickel-aluminum powder on the surface of the sealing ring spraying area by adopting an atmospheric plasma spraying mode to form a nickel-aluminum bottom layer with the thickness of 0.14 mm;
(5) spraying a surface layer: spraying aluminum silicon-polyphenyl ester powder on the surface of the nickel-aluminum bottom layer by adopting an atmospheric plasma spraying mode to form an aluminum silicon-polyphenyl ester surface layer with the thickness of 2.5mm,
(6) cleaning: removing the spraying protection device, cleaning the surface of the blade by using compressed air and alcohol, and removing residual powder, adhesive tapes and floating ash;
(7) mechanically adding: and (3) processing the abradable seal coating to the size and the roughness required by the drawing by adopting a turning machining mode so as to meet the design requirement.
For the sealing labyrinth, the sealing process of the abradable seal coating is as follows:
(1) protecting a non-spraying area: carrying out sand blasting prevention and spraying protection on the non-spraying area of the sealing comb tooth by using a special tool and a thermal spraying protection adhesive tape;
(2) sand blasting treatment: carrying out sand blasting and coarsening on the spraying area on the surface of the sealing comb tooth, using 20-40 meshes of white corundum sand, wherein the sand blasting pressure is 0.5MPa, the surface has no color difference after sand blasting, and the roughness is not lower than Ra 5.0 mu m;
(3) cleaning: cleaning the sand blasting surface by using compressed air and alcohol, removing residual sand particles and floating ash on the surface of the sealing grid tooth, and preparing for spraying;
(4) spraying: spraying tungsten carbide-cobalt powder on the surface of the spraying area of the sealed comb tooth by adopting a supersonic flame spraying mode to form a tungsten carbide-cobalt powder wear-resistant coating with the thickness of 0.18 mm;
(5) cleaning: and (4) removing the spraying protection device, cleaning the surface of the sealing grid tooth by using compressed air and alcohol, and removing residual powder, adhesive tape and floating ash.
The thermal spraying sealing method can reduce scraping abrasion of the labyrinth sealing structure during high-speed rotation to the maximum extent.
Claims (6)
1. A hot spraying sealing method is characterized in that an abradable sealing coating is sealed and coated on a stator sealing ring of a gas turbine or an aeroengine, and a wear-resistant coating is sealed and coated on a corresponding labyrinth; the specific operation is as follows:
step one, sealing and coating a stator sealing ring of a gas turbine or an aeroengine
(1) Protection: carrying out sand blasting prevention and spraying protection on the non-spraying area of the stator sealing ring;
(2) sand blasting: carrying out sand blasting coarsening on the surface spraying area of the stator sealing ring by using 20-40 meshes of white corundum sand, wherein the sand blasting pressure is 0.4-0.6 MPa;
(3) spraying a bottom layer: spraying nickel-aluminum powder on the surface of the sealing ring by adopting an atmospheric plasma spraying mode to form a nickel-aluminum bottom layer with the thickness of 0.10-0.15 mm;
(4) spraying a surface layer: spraying aluminum-silicon-polyphenyl ester powder on the surface of the nickel-aluminum bottom layer in an atmospheric plasma spraying mode to form an aluminum-silicon-polyphenyl ester surface layer with the thickness of 1.8-2.8 mm, wherein the nickel-aluminum bottom layer and the aluminum-silicon-polyphenyl ester surface layer jointly form an abradable seal coating;
step two, sealing and coating wear-resistant coating on corresponding grid teeth
(5) Protection: carrying out sand blasting prevention and spraying protection on the non-spraying area of the grate;
(6) sand blasting: carrying out sand blasting coarsening on the spraying area on the surface of the comb tooth by using 20-40 meshes of white corundum sand, wherein the sand blasting pressure is 0.4-0.6 MPa;
(7) spraying: spraying nickel-chromium carbide or tungsten carbide-cobalt powder on the surface of the comb tooth by adopting a supersonic flame spraying mode to form a nickel-chromium carbide or tungsten carbide-cobalt wear-resistant coating with the thickness of 0.10-0.20 mm;
and (5) completing the thermal spraying sealing method through the operations of the first step and the second step.
2. A thermal spray sealing method according to claim 1, characterized in that the thermal spray sealing is carried out by sealing an abradable sealing coating (2) on a stator sealing ring (1) of a gas turbine or an aero-engine and sealing a wear-resistant coating (4) on the corresponding labyrinth (3).
3. The thermal spray sealing method of claim 1, wherein the blasting pressure in the first and second steps is 0.5 MPa.
4. The thermal spray sealing method according to claim 1, wherein the thickness of the nickel aluminum base layer in the first step is 0.12-0.14 mm.
5. The thermal spraying sealing method according to claim 1, wherein the thickness of the Al-Si-polyphenyl ester surface layer in the step one is 2.0-2.5 mm.
6. The thermal spray sealing method according to claim 1, wherein the thickness of the nickel chromium-chromium carbide or tungsten carbide-cobalt wear-resistant coating in the second step is 0.15-0.18 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110205792.6A CN112981304A (en) | 2021-02-24 | 2021-02-24 | Thermal spraying sealing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110205792.6A CN112981304A (en) | 2021-02-24 | 2021-02-24 | Thermal spraying sealing method |
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| Publication Number | Publication Date |
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| CN112981304A true CN112981304A (en) | 2021-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110205792.6A Pending CN112981304A (en) | 2021-02-24 | 2021-02-24 | Thermal spraying sealing method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115770712A (en) * | 2021-09-07 | 2023-03-10 | 中国航发商用航空发动机有限责任公司 | Spraying method of sealing labyrinth structure |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4466785A (en) * | 1982-11-18 | 1984-08-21 | Ingersoll-Rand Company | Clearance-controlling means comprising abradable layer and abrasive layer |
| US5314304A (en) * | 1991-08-15 | 1994-05-24 | The United States Of America As Represented By The Secretary Of The Air Force | Abradeable labyrinth stator seal |
| US20080008581A1 (en) * | 2006-07-05 | 2008-01-10 | United Technologies Corporation | Rotor for jet turbine engine having both insulation and abrasive material coatings |
| US20080169616A1 (en) * | 2007-01-11 | 2008-07-17 | General Electric Company | Active retractable seal for turbo machinery and related method |
| US20160245110A1 (en) * | 2015-02-25 | 2016-08-25 | United Technologies Corporation | Hard phaseless metallic coating for compressor blade tip |
| CN106756741A (en) * | 2016-12-02 | 2017-05-31 | 哈尔滨东安发动机（集团）有限公司 | The painting method of the anti-deflation seal coating of polybenzoate aluminium silicon |
| CN107503804A (en) * | 2017-06-28 | 2017-12-22 | 哈尔滨汽轮机厂有限责任公司 | Method is obturaged on a kind of vapour road for the through-flow position of steam turbine |
| CN206785431U (en) * | 2017-06-22 | 2017-12-22 | 哈尔滨汽轮机厂有限责任公司 | A kind of through-flow position novel steam road seal structure of steam turbine high pressure |
| CN108486567A (en) * | 2018-04-03 | 2018-09-04 | 江西省科学院应用物理研究所 | A kind of preparation method of single crystal turbine blade blade tip nano-particle reinforcement wear-resistant coating |
-
2021
- 2021-02-24 CN CN202110205792.6A patent/CN112981304A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4466785A (en) * | 1982-11-18 | 1984-08-21 | Ingersoll-Rand Company | Clearance-controlling means comprising abradable layer and abrasive layer |
| US5314304A (en) * | 1991-08-15 | 1994-05-24 | The United States Of America As Represented By The Secretary Of The Air Force | Abradeable labyrinth stator seal |
| US20080008581A1 (en) * | 2006-07-05 | 2008-01-10 | United Technologies Corporation | Rotor for jet turbine engine having both insulation and abrasive material coatings |
| US20080169616A1 (en) * | 2007-01-11 | 2008-07-17 | General Electric Company | Active retractable seal for turbo machinery and related method |
| US20160245110A1 (en) * | 2015-02-25 | 2016-08-25 | United Technologies Corporation | Hard phaseless metallic coating for compressor blade tip |
| CN106756741A (en) * | 2016-12-02 | 2017-05-31 | 哈尔滨东安发动机（集团）有限公司 | The painting method of the anti-deflation seal coating of polybenzoate aluminium silicon |
| CN206785431U (en) * | 2017-06-22 | 2017-12-22 | 哈尔滨汽轮机厂有限责任公司 | A kind of through-flow position novel steam road seal structure of steam turbine high pressure |
| CN107503804A (en) * | 2017-06-28 | 2017-12-22 | 哈尔滨汽轮机厂有限责任公司 | Method is obturaged on a kind of vapour road for the through-flow position of steam turbine |
| CN108486567A (en) * | 2018-04-03 | 2018-09-04 | 江西省科学院应用物理研究所 | A kind of preparation method of single crystal turbine blade blade tip nano-particle reinforcement wear-resistant coating |
Non-Patent Citations (2)
| Title |
|---|
| 吴朝军等: "热喷涂技术在我国航天领域的应用", 《金属加工(热加工)》 * |
| 林琳等: "等离子喷涂铝硅-聚苯酯封严涂层厚度与性能关系研究", 《机械工程师》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115770712A (en) * | 2021-09-07 | 2023-03-10 | 中国航发商用航空发动机有限责任公司 | Spraying method of sealing labyrinth structure |
| CN115770712B (en) * | 2021-09-07 | 2023-09-19 | 中国航发商用航空发动机有限责任公司 | Spraying method of sealing comb tooth structure |
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