GB2397307A - Abradable Coatings - Google Patents
Abradable Coatings Download PDFInfo
- Publication number
- GB2397307A GB2397307A GB0301224A GB0301224A GB2397307A GB 2397307 A GB2397307 A GB 2397307A GB 0301224 A GB0301224 A GB 0301224A GB 0301224 A GB0301224 A GB 0301224A GB 2397307 A GB2397307 A GB 2397307A
- Authority
- GB
- United Kingdom
- Prior art keywords
- coating
- region
- erosion resistance
- abradable
- treated
- 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.)
- Withdrawn
Links
Classifications
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable 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
- C23C4/18—After-treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/312—Layer deposition by plasma spraying
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/12—Light metals
- F05D2300/121—Aluminium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
A method of forming an abradable coating 8 on a substrate, the method comprising applying an abradable coating to the substrate and then treating a region 10 of the coating to alter its erosion resistance. The coating may comprise an AlSi or McrAlY composition. Preferably the coating is applied by plasma spraying, and then subjected to a laser shock peening process followed by heat treatment with a laser. The treatment may result in a densification of the treated region and/or an increase in the inter-particle bond strength in the treated region. The coating may be applied to a shroud ring (6, figure 1) of a gas turbine engine.
Description
1- 2397307
ABRADABLE COATINGS
This invention relates to a method of forming an abradable coating on a substrate, and a component formed by the method. The invention is particularly, although not exclusively, concerned with abradable coatings on gas turbine engine components, such as shroud rings.
The use of abradable coatings in gas turbine engines is well known. For example, US 6358002 discloses an abradable coating applied to the inner surface of a compressor casing. As a rotor rotates within the casing, the rotor blade tips contact the coating and, in effect, machine the coating to form a groove along which the blades of the rotor pass when the engine is at its normal operating temperature and speed. Consequently, gas flow paths between the rotor and casing are minimised, so improving the efficiency of the engine. Also, blade incursions resulting from unbalanced rotation of the rotor or from transient conditions can be accommodated within the abradable coating. This avoids contact between the rotor blades and the alloy substrate of the casing, which contact can cause undesirable wear of the blade tips and the generation of substantial heat.
Known abradable coatings comprise particles which are relatively weakly bonded together so that the coating is easily abraded, for example by passing turbine blades, by breaking of the inter-particle bonds. However, abradable materials also tend to suffer from erosion as a result of the gas flow through the engine. Erosion resistance can be improved by increasing the density of the coating and increasing the inter- particle bond strength, but these measures reduce abradability and so cause increased blade tip wear and possible overheating.
Erosion tends to occur principally at the leading and trailing edges of abradable rotor paths. - 2
According to the present invention there is provided a method of forming an abradable coating on a substrate, the method comprising applying an abradable coating material to the substrate and subsequently treating a region of the applied material to alter its properties, whereby the erosion resistance of the treated region is different from that of an untreated region of the coating.
The abradable coating material is preferably applied in such a way as to achieve a substantially homogeneous coating, at least at the surface region of the coating. The abradable coating material may be applied by plasma spraying.
The subsequent treatment of the applied material may comprise a densification operation, by which the density of the applied material is increased in the treated region. The treatment may additionally, or alternatively, increase the inter-particle bond strength in the treated region.
The treatment may comprise a heat treatment process, in which the treated region is heated to a temperature in excess of a predetermined temperature which depends on the nature of the abradable coating material. Thus, if the coating material comprises a metallic matrix, the predetermined temperature is preferably in excess of 0.75 x Mpt, where Mpt is the melting point, in C, of the metallic matrix. For example, if the abradable coating material comprises an AlSi based material (for example that available under the designation Metco 601 NS from Sulzer Metco), the predetermined temperature may be in excess of 400 C, for example 475 C. Alternatively, the predetermined temperature may be excess of 900 C, for example 950 C, if a MCrAIY, such as NiCrAIY, based material is used (for example the product available under the designation AE2042 from Sulzer Metco.
The heating of the applied material may be achieved by means of a laser, for example a CO2 or YAG laser having a power output of not less than 500 watts. Processing may comprise a single heating stage, but alternatively a laser peening process may be performed on the surface of the abradable material before the heating stage, in order to achieve the desired effect. During the heating stage, the laser beam may be defocused - 3 and may be controlled so as to traverse the region to be treated, for example in a raster or grid pattern. By way of example, the traverse speed of the laser beam over the region being treated may be not less than 20 mm per second and not more than 60 mm per second.
The treatment of the applied material preferably extends for only part of the depth of the coating. For example, the treatment may extend to a depth in the range 0.1 to 0.5 mm.
In a preferred embodiment, the region of the applied material which is treated is an edge region of the coating. For example, the substrate may comprise part of a casing or shroud ring of a gas turbine engine, and the coating may be applied circumferentially of the interior of the casing or shroud ring. In such a component, treatment of the applied material may be confined to axial edge regions of the coating.
According to another aspect of the present invention, there is provided a component having an abradable coating, the erosion resistance of the coating varying over the surface of the coating.
The component may comprise a substrate, for example of metal such as an aluminium or titanium alloy, to which the coating is formed by applying an abradable coating material to the substrate. The coating may be applied by plasma spraying, and may, for example, comprise an AlSi based or an MCrAIY base material.
The coating may comprise a portion having a higher density, at least in the surface region of the coating at that portion, which provides greater erosion resistance than other portions of the coating. Alternatively, or in addition, the portion of the coating having a greater erosion resistance may have inter-particle bonds which are stronger than in other portions of the coating.
The portion of the coating having a higher density or stronger interparticle bonds may extend only partially through the depth of the coating, for example to a depth of 0.1 mm to 0.5 mm. - 4
The component may comprise a casing or shroud ring of a gas turbine engine, and particularly of an axial compressor, the coating then extending circumferentially of an internal surface of the component, the erosion resistance of the coating being greater at the axial edges of the coating than in a region of the coating between the edges.
The present invention may also provide a shroud ring or casing of a gas turbine engine as defined above, within which a rotor is mounted for rotation, the region of the coating adjacent at least one edge of the path of the rotor over the coating having a greater erosion resistance than a region of the coating disposed generally centrally of the rotor path. The rotor path may extend axially into the region of greater erosion resistance.
For a better understanding of the present invention, and to show more clearly how it may be carried into effect, reference will now be made, by way of example, to the accompanying drawings, in which: Figure 1 is a fragmentary axial sectional view through a rotor stage of gas turbine engine; and Figure 2 is a diagrammatic fragmentary view of a rotor blade and an adjacent region of a shroud ring.
As shown in Figure 1, a rotor represented by a single blade 2 is disposed within an engine casing 4 which includes a shroud ring 6. The shroud ring 6 has an abradable coating 8 on its inner surface.
In operation expansion of the blade 2 under thermal or centrifugal effects will cause the tip of the blade 2 to engage the coating 8 and abrade it. Blade incursion into the abradable coating 8 may also arise under conditions which cause unbalanced rotation of the rotor, for example if one or more of the blades 2 are damaged or missing. The coating 8 enables close tolerances to be maintained between the blades 2 of the rotor and the shroud ring 6 while avoiding blade wear and the generation of excessive heat - 5 should the blades 2 contact the coating 8. Abradable coatings are well known and may be formed from many different compositions. They are commonly applied by plasma spraying. A typical abradable coating comprises particles which are bound together by relatively weak inter-particle bonds so that particles break away from one another during blade incursions so enabling the coating to abrade relatively easily. Typical abradable coatings are based on AlSi compositions provided by Sulzer Metco available under the designation Metco 601 NS, or MCrAIY, and in particular NiCrAIY, compositions typified by compositions available from Sulzer Metco under the designation AE2042.
Abradable coatings are subjected to the gas flow through the rotor stage in which they are used. The gas flows at high velocity and at elevated temperatures. This gas flow tends to erode abradable coatings, and this erosion is particularly noticeable at axial edge regions of the coatings, indicated at X in Figures 1 and 2. A compromise consequently has to be struck between a coating structure which is sufficiently weak to avoid blade tip wear and the generation of excessive heat during incursions of the blades 2 into the coating 8, and a coating composition which is sufficiently strong to minimise erosion. This is because, hitherto, abradable coatings have been heterogeneous over their full extent.
In accordance with the present invention, and as shown in Figure 2, the abradable coating 8 is not heterogeneous. Instead, regions 10 of the coating 8, adjacent the axial edges of the path of the rotor blades 2, have a higher erosion resistance, and consequently a higher resistance to abrasion by the blades 2, than the central region 12 of the coating. Consequently, the axial edge regions X of the coating are better able to withstand erosion arising from the gas flow within the rotor stage, without significantly affecting the abradability of the coating 8 during incursions of the blades 2.
To form the coating 8, a suitable coating material is applied in any suitable manner, for example by plasma spraying, and is subsequently treated to provide selective increased erosion resistance in the regions where such increased erosion resistance is required. Thus, with regard to Figure 2, the edge regions 10 are treated. The - 6 treatment causes surface densification of the coating and/or an increase in the interparticle bond strength within the coating.
In a preferred embodiment, surface densification is achieved by heating the surface of the coating in the regions at which increased erosion resistance is required. This heating is achieved by means of a defocused laser beam which is moved over the respective regions of the coating in an appropriate pattern, for example in a raster pattern as diagrammatically shown in Figure 2.
A CO2 or YAG laser may be used, having a power output in excess of 500 watts. The power output of the laser, and its traverse rate over the surface of the coating 8 is controlled to achieve, at the surface region of the coating 8, a temperature sufficient to cause densification and/or an increase in the inter-particle bond strength. For example, a surface temperature in the range 450 C to 500 C (specifically 475 C) has been found to be suitable for AlSi based abradable coatings, and surface temperatures in the range 925 C to 975 C, specifically 950 C, have been found to be suitable for MCrAIY based abradable coatings. The traverse rate of the laser beam may be in the region 20 to 60 mm per second.
The densification of the coating is restricted to the surface region of the coating, for example to a depth of 0.1 to 0.5 mm. In some circumstances, the laser treatment is performed after the final machining of the coating to avoid the machining process being affected by the densified regions, and to avoid removal of the densified regions during the machining process.
However, the densification process may cause shrinkage of the abradable material in the densified region. Consequently, a preferred sequence of steps is to machine the abradable coating to a thickness in excess of the nominal value by the expected value of the shrinkage, for example by 0.1 0.5 mm, more particularly by 0.2 mm, then to perform the densification process, and finally to perform a final machining process to achieve the nominal thickness of the coating. - 7
Additionally, the laser treatment of the coating may be performed in two steps. The first stage may comprise a laser shock peening process, and the second stage may comprise a heating process as described to anneal the peened material.
Laser shock peening is a known technique for generating compressive stresses in the surface of a component using laser energy. A laser shock peening process is disclosed in US 5131957, the disclosure of which is incorporated herein by reference. In a typical laser peening process, the workpiece to be treated is coated first with an opaque layer, such as black paint, and subsequently covered with a transparent layer, which may be water. A pulsed laser beam is directed at the workpiece through the transparent layer.
When the beam strikes the opaque layer, the laser energy vaporises the opaque layer, converting it into plasma and causing an explosive impact to be applied to the surface of the workpiece. The transparent layer provides a reaction element, increasing the force of the explosive impact on the surface of the workpiece.
The impact applied by the vaporised part of the opaque layer causes a shock wave to propagate into the surface of the workpiece. This causes plastic deformation of the material of the workpiece in its surface region, resulting in an induced compressive stress adjacent the surface. This induced compressive stress increases the resistance of the workpiece to crack formation and propagation.
As shown in Figure 2, the treated regions 10 of the coating 8 extend into the path of the blades 2. However, since the bulk of the rotor path is untreated, the net effect of the increased erosion resistance in the regions 10 on the abradability of the coating during blade incursions is minimal, while enhanced resistance to erosion is achieved. - 8
Claims (28)
1. A method of forming an abradable coating on a substrate, the method comprising applying an abradable coating material to the substrate and subsequently treating a region of the applied material to alter its properties, whereby the erosion resistance of the treated region is different from that of an untreated region of the coating.
2. A method as claimed in claim 1, in which the abradable coating material is applied to the substrate by plasma spraying.
3. A method as claimed in claim 1 or 2, in which at least the surface region of the coating before treatment is substantially homogeneous.
4. A method as claimed in any one of the preceding claims, in which the treatment results in densification of the treated region resulting in increased erosion resistance.
5. A method as claimed in any one of the preceding claims, in which the treatment results in an increase of the inter-particle bond strength in the treated region resulting in increased erosion resistance.
6. A method as claimed in any one of the preceding claims, in which the treatment comprises a heat treatment process.
7. A method as claimed in claim 6, in which heat is generated in the coating by means of a laser.
8. A method as claimed in claim 7, in which the laser is operated at a power output which is not less than 500 watts. - 9 -
9. A method as claimed in claim 7 or 8, in which the laser beam is defocused at the point at which the laser beam strikes the surface of the applied material.
10. A method as claimed in any one of claims 7 to 9, in which the laser beam is traversed over the region to be treated.
11. A method as claimed in claim 10, in which the traverse speed of the laser beam is not less than 20 and not greater than 60 mm per second.
12. A method as claimed in claims 10 or 11, in which the laser beam is traversed over the region to be treated in a raster pattern.
13. A method as claimed in any one of claims 6 to 12, in which the treatment comprises a laser shock peening process performed before the heat treatment process.
14. A method as claimed in any one of claims 6 to 13, in which the coating material comprises a metallic matrix and in which the heat treatment includes raising the temperature of at least the surface of the coating in the treated region to a temperature not less than 0.75 x Mpt, where Mpt is the melting point in C of the metallic matrix.
15. A method as claimed in any one of the preceding claims, in which the coating material comprises an AlSi composition, and in which the treatment includes raising the temperature of at least the surface of the coating in the treated region to a temperature not less than 400 C.
16. A method as claimed in any one of claims 1 to 14, in which the coating material comprises an MCrAIY composition, and in which the treatment includes raising the temperature of at least the surface of the coating in the treated region to a temperature not less than 900 C. -
17. A method as claimed in any one of the preceding claims, in which the treated region of the coating comprises an edge region of the coating.
18. A method as claimed in claim 17, in which the substrate comprises a component of a rotor casing of a gas turbine engine, the coating being applied circumferentially of the casing interior, and the treated region comprising at least one of the axial edge regions of the coating.
19. A method of forming an abradable coating on a substrate, the method being in accordance with claim 1 and substantially as described herein.
20. A component having an abradable coating, the erosion resistance of the coating varying over the surface of the coating.
21. A component as claimed in claim 20, in which the coating comprises an AlSi or MCrAIY based composition.
22. A component as claimed in claim 20 or 21, in which the region of the surface of the coating having a higher erosion resistance has a higher density than a region of the surface of the coating having a lower erosion resistance.
23. A component as claimed in any one of claims 20 to 22, in which the region of the surface of the coating having a higher erosion resistance has stronger inter- particle bonding than a region of the surface of the coating having a lower erosion resistance.
24. A component as claimed in claim 22 or 23, in which the region having a higher erosion resistance extends from the surface of the coating to a depth not less than 0.1 mm and not more than 0.5 mm.
25. A component as claimed in any one of claims 20 to 24, in which the component is a shroud ring of a gas turbine engine, the coating extending circumferentially - 11 of the interior of the shroud ring, and at least one of the axial edge regions of the coating having a higher erosion resistance than the region of the coating disposed between the axial edge regions.
26. A gas turbine engine having a shroud ring as claimed in claim 25, and a bladed rotor mounted for rotation within the shroud ring, the region of the coating at at least one edge of the path of the rotor over the coating having a higher erosion resistance than a region of the coating disposed between the edges of the rotor path.
27. A gas turbine engine as claimed in claim 26, in which the rotor path extends into the region having the greater erosion resistance.
28. A component having an abradable coating substantially as described herein with reference to, and as shown, the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0301224A GB2397307A (en) | 2003-01-20 | 2003-01-20 | Abradable Coatings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0301224A GB2397307A (en) | 2003-01-20 | 2003-01-20 | Abradable Coatings |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB0301224D0 GB0301224D0 (en) | 2003-02-19 |
| GB2397307A true GB2397307A (en) | 2004-07-21 |
Family
ID=9951422
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0301224A Withdrawn GB2397307A (en) | 2003-01-20 | 2003-01-20 | Abradable Coatings |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2397307A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006042506A1 (en) * | 2004-10-16 | 2006-04-27 | Mtu Aero Engines Gmbh | Method for producing a component covered with a wear-resistant coating |
| WO2007065403A1 (en) * | 2005-12-07 | 2007-06-14 | Mtu Aero Engines Gmbh | Method for manufacturing a run-in coating |
| EP1932928A1 (en) | 2006-11-30 | 2008-06-18 | United Technologies Corporation | Densification of coating using laser peening |
| GB2448109A (en) * | 2007-04-04 | 2008-10-08 | Alstom Technology Ltd | Enhanced erosion resistance for low pressure steam turbine bl ades |
| US7942638B2 (en) | 2005-06-29 | 2011-05-17 | Mtu Aero Engines Gmbh | Turbomachine blade with a blade tip armor cladding |
| WO2017093648A1 (en) * | 2015-12-03 | 2017-06-08 | Safran Helicopter Engines | Hybrid annular sector with touch-tolerant protective coating |
| CN107532272A (en) * | 2015-04-21 | 2018-01-02 | 东华隆株式会社 | The method for coarsening surface of base material, the surface treatment method of base material, spraying overlay film are coated to part and its manufacture method |
| CN107805775A (en) * | 2017-09-28 | 2018-03-16 | 中国航发动力股份有限公司 | A kind of high-temperature abradable seal coating and preparation method thereof |
| GB2562382A (en) * | 2017-05-12 | 2018-11-14 | Safran Nacelles Ltd | Method of coating a workpiece |
| CN112144005A (en) * | 2020-08-20 | 2020-12-29 | 西安交通大学 | Blade tip cutting coating with interface barrier layer and preparation method thereof |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119307853A (en) * | 2024-12-16 | 2025-01-14 | 季华实验室 | Preparation method of plasma spraying coupling laser strengthening coating |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4422648A (en) * | 1982-06-17 | 1983-12-27 | United Technologies Corporation | Ceramic faced outer air seal for gas turbine engines |
| US4481237A (en) * | 1981-12-14 | 1984-11-06 | United Technologies Corporation | Method of applying ceramic coatings on a metallic substrate |
| US5131957A (en) * | 1990-01-11 | 1992-07-21 | Battelle Memorial Institute | Material properties |
| US6358002B1 (en) * | 1998-06-18 | 2002-03-19 | United Technologies Corporation | Article having durable ceramic coating with localized abradable portion |
-
2003
- 2003-01-20 GB GB0301224A patent/GB2397307A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4481237A (en) * | 1981-12-14 | 1984-11-06 | United Technologies Corporation | Method of applying ceramic coatings on a metallic substrate |
| US4422648A (en) * | 1982-06-17 | 1983-12-27 | United Technologies Corporation | Ceramic faced outer air seal for gas turbine engines |
| US5131957A (en) * | 1990-01-11 | 1992-07-21 | Battelle Memorial Institute | Material properties |
| US6358002B1 (en) * | 1998-06-18 | 2002-03-19 | United Technologies Corporation | Article having durable ceramic coating with localized abradable portion |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006042506A1 (en) * | 2004-10-16 | 2006-04-27 | Mtu Aero Engines Gmbh | Method for producing a component covered with a wear-resistant coating |
| US8920881B2 (en) | 2004-10-16 | 2014-12-30 | MTU Aero Engines AG | Method for producing a component covered with a wear-resistant coating |
| US7942638B2 (en) | 2005-06-29 | 2011-05-17 | Mtu Aero Engines Gmbh | Turbomachine blade with a blade tip armor cladding |
| WO2007065403A1 (en) * | 2005-12-07 | 2007-06-14 | Mtu Aero Engines Gmbh | Method for manufacturing a run-in coating |
| EP1932928A1 (en) | 2006-11-30 | 2008-06-18 | United Technologies Corporation | Densification of coating using laser peening |
| EP1932928B1 (en) | 2006-11-30 | 2015-10-14 | United Technologies Corporation | Densification of coating using laser peening |
| GB2448109A (en) * | 2007-04-04 | 2008-10-08 | Alstom Technology Ltd | Enhanced erosion resistance for low pressure steam turbine bl ades |
| CN107532272B (en) * | 2015-04-21 | 2020-04-17 | 东华隆株式会社 | Method for roughening surface of substrate, method for treating surface of substrate, spray-coated member, and method for producing same |
| CN107532272A (en) * | 2015-04-21 | 2018-01-02 | 东华隆株式会社 | The method for coarsening surface of base material, the surface treatment method of base material, spraying overlay film are coated to part and its manufacture method |
| US11131014B2 (en) | 2015-04-21 | 2021-09-28 | Tocalo Co., Ltd. | Method for roughening surface of substrate, method for treating surface of substrate, method for producing thermal spray-coated member, and thermal spray-coated member |
| FR3044702A1 (en) * | 2015-12-03 | 2017-06-09 | Turbomeca | HYBRID ANNULAR SECTOR WITH TOLERANT TOUCH COATING |
| WO2017093648A1 (en) * | 2015-12-03 | 2017-06-08 | Safran Helicopter Engines | Hybrid annular sector with touch-tolerant protective coating |
| GB2562382A (en) * | 2017-05-12 | 2018-11-14 | Safran Nacelles Ltd | Method of coating a workpiece |
| CN107805775A (en) * | 2017-09-28 | 2018-03-16 | 中国航发动力股份有限公司 | A kind of high-temperature abradable seal coating and preparation method thereof |
| CN112144005A (en) * | 2020-08-20 | 2020-12-29 | 西安交通大学 | Blade tip cutting coating with interface barrier layer and preparation method thereof |
| CN112144005B (en) * | 2020-08-20 | 2021-12-28 | 西安交通大学 | A kind of blade tip cutting coating with interface barrier layer and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0301224D0 (en) | 2003-02-19 |
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