GB2111889A - A method of increasing the reliability of creep loaded components in particular turbine blades - Google Patents
A method of increasing the reliability of creep loaded components in particular turbine blades Download PDFInfo
- Publication number
- GB2111889A GB2111889A GB08232519A GB8232519A GB2111889A GB 2111889 A GB2111889 A GB 2111889A GB 08232519 A GB08232519 A GB 08232519A GB 8232519 A GB8232519 A GB 8232519A GB 2111889 A GB2111889 A GB 2111889A
- Authority
- GB
- United Kingdom
- Prior art keywords
- components
- creep
- hot isostatic
- isostatic pressing
- cracks
- 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
- 238000000034 method Methods 0.000 title claims description 20
- 238000001513 hot isostatic pressing Methods 0.000 claims abstract description 17
- 239000010953 base metal Substances 0.000 claims abstract description 14
- 239000011248 coating agent Substances 0.000 claims abstract description 9
- 238000000576 coating method Methods 0.000 claims abstract description 9
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 8
- 239000000956 alloy Substances 0.000 claims abstract description 8
- 239000011148 porous material Substances 0.000 claims abstract description 7
- 238000010494 dissociation reaction Methods 0.000 claims abstract 2
- 230000005593 dissociations Effects 0.000 claims abstract 2
- 238000000265 homogenisation Methods 0.000 claims abstract 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 16
- 229910052759 nickel Inorganic materials 0.000 claims description 8
- 238000005242 forging Methods 0.000 claims description 5
- 238000009792 diffusion process Methods 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 description 6
- 239000004411 aluminium Substances 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 3
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 239000011651 chromium Substances 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 description 2
- 229910001928 zirconium oxide Inorganic materials 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- -1 cobalt-chromium-aluminium-yttrium Chemical compound 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000000462 isostatic pressing Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F3/00—Changing the physical structure of non-ferrous metals or alloys by special physical methods, e.g. treatment with neutrons
Landscapes
- Chemical & Material Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The reliability of a set of components, e.g. turbine blades or pipe bends, is increased by subjecting the components already creep-loaded to a hot isostatic pressing. Preferably, creep pores and cracks are closed by the hot isostatic pressing. The dissociation behaviour of alloy elements may be altered by the hot isostatic pressing with respect to homogenization and refinement of deposits. In a particular embodiment, a coating is broken by the hot isostatic pressing where outer base metal cracks are not closed in order to locate cracks for the purpose of component rejection.
Description
SPECIFICATION
A method of increasing the reliability of creeploaded components, in particular turbine blades
The present invention relates to a method according to a method of increasing the reliability of creeploaded component, e.g. turbine blades.
Creep-loaded components, usually of metal, undergo changes in their material when used. These are, in particular, the formation of deposits, the coarsening of deposits, the transformation of deposits in accordance with the thermodynamic equilibriums, creep pore formation and crack formation. An accumulation of these effects as a rule leads to the failure of the component as a result of creep rupture.
If it is not possible to examine such components without destroying them, it is usual to make do with an investigation of the structure on a representative random sample. This procedure is unreliable mainly because of the sampling. This procedure is not satisfactory, particularly for estimating the remaining service life of turbine blades since, on account of the large number of blades of a blade ring, the probability of excessive damage or changes in material not detected by the sample cannot be kept as low as desired for economic reasons.
An object of the invention to increase the reliability of such components.
The invention provides a method of increasing the reliability of components already creep-loaded comprising subjecting the components already creeploaded to a hot isostatic pressing.
In order to increase the reliability of the components, changes in material which the creep-loaded components have undergone are eliminated to a large extent by means of the hot isostatic pressing or heat treatment under isostatic pressure, so that these components may be further utilized. In addition, for coated components and likewise to increase the reliability of sets of components, this hot isostatic pressing provides a precondition for an examination or simply performed examination relating to rejection of components from the set, to which reference will be made below in greater detail.
Preferably, the method is such that the creep pores and cracks are closed for an uncoated component if the creep pores and cracks do not extend as far as the surface of the component, and for a coated component, i.e. one having one layer and/or a plurality of superimposed layers, more frequently if the creep pores and cracks extend as far as the surface of the base metal (outer base metal pores and cracks).
By means of this procedure the total service life of the component is increased if hot isostatic pressing is performed, provided that cracks do not reach as far as the surface of the component. This increase often amounts to at least 50%, i.e. in the case of a nickel-based forging alloy which essentially consists, in percentage by weight, of approximately 14% chromium, approximately 1.2% titanium, approximately 5% aluminium, approximately 20% cobalt, approximately 5% molybdenum, approximately 1% silicon, approximately 1% manganese, approximately 2% iron, approximately 0.2% carbon and about 50% nickel.
If the procedure as claimed in claim 3 is followed, preferably at an isostatic pressure over 1250 bar, creep strength depending on time, tensile strength, ductility and fatigue strength under vibrating stresses are increased, in particular where nickel-based forging alloys are concerned. In the case of the above-mentioned nickel-based forging alloy there is an increase in the work of deformation in the notched-bar impact test of 400% with increased tensile strength.
The use of relatively low temperatures as claimed in claim 5 permits the hot isostatic pressing of coated components without the occurrence of unacceptable embrittlement and diffusion effects in the coating and/or in the base metal. Removal of the coating from the base metal before the hot isostatic pressing is unnecessary.
The coating covers the outer cracks of the base metal so that they cannot be located or can only be located with a great deal of effort. They are closed by means of the hot isostatic pressing (see above) or they opened opned by the isostatic pressing, which allows examination for cracks (see the preceding paragraph). This opening, i.e. breaking the coating outside the outer base metal cracks, constitutes a preparation for examination or easily performed examination. Thus the cracks may now be made easily visible under a microscope. Evaluation of the cracks results in rejection or retention of this component from the set. Further use of unacceptably badly damaged components, i.e. the re-insertion of unacceptably badly damaged gas turbine blades, is thus avoided.
Preferably, the parametes of the hot isostatic pressing are as claimed in claim 7. Preferably, the ranges of the magnitude of these parametesfora specific type of base metal with specific types of layers are as claimed in claim 8.
In the case of the above-described nickel-based forging alloy with the given percentages and an aluminium diffusion layer, the temperature preferably is approximately 1050"C, the isostatic pressure is approximately 1300 bar and the pressing time is approximately 1.5 hours.
The said set or ring orturbomachine or turbine blades is primarily one comprising rotor blades, in particular a gas turbine. The aforesaid components may also be, for example, pipe bends or elbows.
The material or base metal of the components is generally a metal or a metal alloy, in particular a nickel-based alloy. The components may, or example, consist of an age-hardened material or base metal, particularly of the components are turbine blades. This may for example, be a nickel-based material.
In the case of coated components as described above, the coating is: for example, an aluminium or chromium diffusion layer: a covering layer, such as for example a cobalt-chromium-aluminium-yttrium layer; a heat insulation layer such as for example a zirconium oxide (Zr2O) layer; or the combination of at least two of these layers, which are then superim posed. Preferably, turbine blades have a coating of this type.
Claims (10)
1. A method of increasing the reliability of components already creep-loaded comprising subjecting the components already creep-loaded to a hot isostatic pressing.
2. A method as claimed in claim 1, wherein the hot isostatic pressing is such as the close creep pores and cracks in the components.
3. A method as claimed in claim 1 or 2, wherein the isostatic pressure is sufficiently high to alter the dissociation behaviour of alloy elements with respect to homogenization and refinement of deposits.
4. A method as claimed in claim 3, wherein the isostatic pressure is over 1250 bar.
5. A method as claimed in any one of claims 1 to 4, wherein the components are coated and the hot isostatic pressing is carried out at a temperature below the solution heat-treatment temperature of the base metal.
6. A method as claimed in claim 1, wherein the coating is broken by the hot isostatic pressing where outer base metal cracks are not closed in order to locate cracks for the purpose of component rejection.
7. A method as claimed in any one of claims 1 to 6, wherein the temperature of the hot isostatic pressing is substantially the same as the coating temperature or less than the solution heat-treatment temperature of the base metal, the isostatic pressure is between substantially 950 bar and 2000 bar and the pressing time is substantially 4 hours.
8. A method as claimed in claim 7, wherein the components having a nickel-based forging alloy as a base metal and a diffusion layer or a covering layer and the said temperature is between substantially 950"C and 11 50 C, said isostatic pressure is between 1200 bar and 1400 bar and the said pressing time is between 1 hour and two hours.
9. A method substantially as herein described with reference to any of the examples given.
10. Creep-loaded components in which the reliability of the components is increased by a method as claimed in any one of the preceding claims.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19813145941 DE3145941C2 (en) | 1981-11-20 | 1981-11-20 | Process for increasing the reliability of coated components of turbomachinery that are already subject to creep stress |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB2111889A true GB2111889A (en) | 1983-07-13 |
| GB2111889B GB2111889B (en) | 1985-10-23 |
Family
ID=6146760
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08232519A Expired GB2111889B (en) | 1981-11-20 | 1982-11-15 | A method of increasing the reliability of creep-loaded components in particular turbine blades |
Country Status (3)
| Country | Link |
|---|---|
| DE (1) | DE3145941C2 (en) |
| FR (1) | FR2516943A1 (en) |
| GB (1) | GB2111889B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110026478A (en) * | 2019-04-30 | 2019-07-19 | 重庆三峡学院 | The method and apparatus of the compound timeliness progressive molding of Vibration Creep based on air pressure-loading |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2620735A1 (en) * | 1987-09-19 | 1989-03-24 | Motoren Turbinen Union | Process for the heat treatment of structural components made of nickel-based foundry alloys |
| US4975124A (en) * | 1989-02-06 | 1990-12-04 | United Technologies Corporation | Process for densifying castings |
| DE19853285C1 (en) * | 1998-11-19 | 2000-06-15 | Karlsruhe Forschzent | Process for producing a protective layer on a martensitic steel and use of the steel provided with the protective layer |
| RU2550055C2 (en) * | 2013-04-30 | 2015-05-10 | Общество с ограниченной ответственностью "Производственное предприятие Турбинаспецсервис" | Reconditioning of gas turbine plant including nozzle blades from nickel or cobalt alloys composed of multibank structure |
| RU2760895C1 (en) * | 2021-03-10 | 2021-12-01 | Акционерное общество "ОДК-Климов" | Method for restoring the cyclic durability of disks of aircraft gas turbine engines |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3758347A (en) * | 1970-12-21 | 1973-09-11 | Gen Electric | Method for improving a metal casting |
-
1981
- 1981-11-20 DE DE19813145941 patent/DE3145941C2/en not_active Expired
-
1982
- 1982-10-25 FR FR8217832A patent/FR2516943A1/en active Granted
- 1982-11-15 GB GB08232519A patent/GB2111889B/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110026478A (en) * | 2019-04-30 | 2019-07-19 | 重庆三峡学院 | The method and apparatus of the compound timeliness progressive molding of Vibration Creep based on air pressure-loading |
| CN110026478B (en) * | 2019-04-30 | 2024-05-03 | 中国民用航空飞行学院 | Method and device for vibration creep composite aging incremental forming based on pneumatic loading |
Also Published As
| Publication number | Publication date |
|---|---|
| DE3145941A1 (en) | 1983-06-01 |
| FR2516943A1 (en) | 1983-05-27 |
| GB2111889B (en) | 1985-10-23 |
| DE3145941C2 (en) | 1983-12-01 |
| FR2516943B3 (en) | 1985-02-15 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 746 | Register noted 'licences of right' (sect. 46/1977) | ||
| PE20 | Patent expired after termination of 20 years |
Effective date: 20021114 |