CN102485934A - Method for preparing hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance - Google Patents
Method for preparing hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance Download PDFInfo
- Publication number
- CN102485934A CN102485934A CN2010105682761A CN201010568276A CN102485934A CN 102485934 A CN102485934 A CN 102485934A CN 2010105682761 A CN2010105682761 A CN 2010105682761A CN 201010568276 A CN201010568276 A CN 201010568276A CN 102485934 A CN102485934 A CN 102485934A
- Authority
- CN
- China
- Prior art keywords
- nickel
- chromium
- powder
- penetration enhancer
- aluminium
- 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
Abstract
The invention provides a method for preparing a hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance, which is characterized by comprising the following steps: preparing a nickel chromium osmolyte and a chromium aluminum osmolyte; calcining the prepared nickel chromium osmolyte at the temperature of 1000-1050 DEG C for 1-2 hours, then sieving by a 60 meshes sieve, filling in a seal container for next application; then calcining the prepared chromium aluminum osmolyte at the temperature of 1100-1150 DEG C for 1-2 hours and calcining at the temperature of 950-1000 DEG C for 1-2 hours, then sieving by the 60 meshes sieve, filling in the seal container for next application; then preparing the hollow blade diffusion layer, raising the work temperature of the nickel base high temperature alloy blade from 900 DEG C to 1050-1100 DEG C, simultaneously preparing the diffusion layer both in the inner chamber and on the external surface of the blade. The high temperature resistance, oxidation resistance and corrosion resistance capabilities of the blade can be substantially enhanced.
Description
Technical field
The present invention relates to alloy surface high temperature corrosion and protection field, the preparation method of a kind of hollow blade inner chamber resistance to high temperature oxidation and corrosion diffusion infiltration layer is provided especially.
Background technology
K465 alloy vane surface in oxidising process has generated the oxide compound of a large amount of non-protectives, and interior oxidation and interior nitrogenize have also appearred in matrix, so this alloy need apply coating protection when high temperature uses.Single calorized coating is to have certain resistance of oxidation 1000 ℃ of oxidations; Coating degradation is serious behind 1100 ℃ of oxidation 300h, loses provide protection.Sputtering NiCr AlY coating is owing to the acting in conjunction of columnar nanometer crystal structure and Cr element, and the surface has formed fine and close α-Al when 1000 ℃ of oxidations
2O
3Protective membrane shows good antioxidant property; But when 1100 ℃ of oxidations, Al
2O
3Protective membrane is because stress cracking and Al consume excessively and can not be kept, and antioxidant property sharply descends.
Existing solid chromaluminizing method and the slip method of oozing can not prepare infiltration layer at the piece surface that has inner chamber; And the gas phase method of oozing needs complicated frock clamp, up to the present, can not satisfy the requirement of inner chamber infiltration layer.
Summary of the invention
The object of the present invention is to provide the preparation method of a kind of hollow blade inner chamber resistance to high temperature oxidation and corrosion diffusion infiltration layer, to solve in the past the problem that can't prepare infiltration layer and resistance to high temperature oxidation, corrosive nature difference at the piece surface that has inner chamber.
Metal is unsettled when the work of room temperature or hot environment, and they are all being corroded to some extent, are not in room temperature water solution, to be corroded, and are exactly again oxidized under the high temperature, thereby is destroyed or rotten.The present invention infiltrates element nickel chromium triangle, chromium aluminium on the alloy vane surface, and under high-temperature work environment, the surface forms Cr
2O
3, Al
2O
3Dense film, opposing is at the corrosion and the oxidation behavior of working process more than 1000 ℃, and is especially more obvious for the nickel base superalloy effect, preferred K465 nickel base superalloy.
The invention provides the preparation method of a kind of hollow blade inner chamber resistance to high temperature oxidation and corrosion diffusion infiltration layer, it is characterized in that: concrete preparation process is following,
---the preparation penetration enhancer:
(1), preparation nickel chromium triangle penetration enhancer: chromium powder, nickel powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with the nickel chromium triangle penetration enhancer according to following weight ratio;
Chromium powder 7% ~ 10%; Nickel powder 24% ~ 27%;
Aluminium oxide powder 60% ~ 62%; Nickel-yittrium alloy powder 3% ~ 5%;
The ammonium chloride surplus;
Wherein, chromium powder, nickel powder, nickel-yittrium alloy powder are the penetration enhancer material, can form infiltration layer; Aluminium oxide powder is a weighting agent, and its buffer action prevents that other are powder sintered; Ammonium chloride is acvator.
(2), preparation chromium aluminium penetration enhancer: chromium powder, aluminium powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with chromium aluminium penetration enhancer according to following weight ratio;
Chromium powder 38% ~ 40%; Aluminium powder 4% ~ 6%;
Aluminium oxide powder 51% ~ 53%; Nickel-yittrium alloy powder 3% ~ 5%;
The ammonium chloride surplus;
Wherein, chromium powder, aluminium powder, nickel-yittrium alloy powder are the penetration enhancer material, can form infiltration layer; Aluminium sesquioxide is a weighting agent, and its buffer action prevents that other are powder sintered; Ammonium chloride is acvator.
---the roasting penetration enhancer:
(3), with nickel chromium triangle penetration enhancer of preparation in (1) through 1000 ℃～1050 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
(4), with chromium aluminium penetration enhancer of preparation in (2) through 1100 ℃～1150 ℃/1h ~ 2h and 950 ℃～1000 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
Two kinds of penetration enhancers are carried out its purpose of roasting for being penetration enhancer material formation intermediate compound; Like chromium chloride, aluminum chloride etc.; Make the penetration enhancer activation, have only again ability activation under the certain temperature, decomposite active aluminum and chromium again in the diffusion annealing; These have active aluminium and chromium at high temperature could infiltrate in the alloy, form infiltration layer.
All added nickel-yittrium alloy powder in two kinds of penetration enhancers, made in the infiltration layer of acquisition and contain yttrium, improved infiltration layer antioxidant property and with the bonding force of matrix.
---the preparation infiltration layer:
(5), the nickel chromium triangle penetration enhancer after roasting in (3) is poured in the blade inner chamber, and blade imbedded with the nickel chromium triangle penetration enhancer ooze in the jar, put into the vacuum oven internal heating then; Have the graphite heating element in the said vacuum oven, at first be heated to 400 ℃, insulation 1.5h～2h; Be warming up to 800 ℃ again, insulation 1h, 1000 ℃～1100 ℃ of the outlet temperatures of intensification value again; Insulation 4h～5h cools to the furnace below 200 ℃, comes out of the stove; Wherein, 400 ℃ of stops, its purpose is that the ammonium chloride in the powder is decomposed, and the setting of 1000 ℃～1100 ℃ of outlet temperatures is better to infiltrate the nickel chromium triangle infiltration layer for blade surface.
(6), the nickel chromium triangle penetration enhancer on the blade of coming out of the stove in (5) cleaned out after, again the chromium aluminium penetration enhancer after roasting in (4) is poured in the blade inner chamber, and blade imbedded with chromium aluminium penetration enhancer oozes in the jar, put into the vacuum oven internal heating then; Have the graphite heating element in the said vacuum oven, at first be heated to 400 ℃, insulation 1.5h～2h is warming up to 800 ℃ again; Insulation 1h is warming up to 1000 ℃ again, insulation 2h; Be warming up to 1050 ℃ again, insulation 2h is warming up to 1100 ℃～1200 ℃ of outlet temperatures again; Insulation 1h～1.5h is chilled to below 200 ℃ with stove, comes out of the stove; Wherein, 400 ℃ of stops, its purpose is that the ammonium chloride in the powder is decomposed, and the setting of 1100 ℃～1200 ℃ of outlet temperatures is better to infiltrate chromium aluminium infiltration layer for blade surface, and each temperature of intermediary is for even intensification.
Yet the protective value of infiltration layer depends on the concentration with the thickness and the aluminium of infiltration layer.After infiltration layer stood long-time high temperature action, if other condition is identical, then the maximum level of aluminium was looked the thickness of infiltration layer and is decided in the infiltration layer.Infiltration layer is thick more, and the aluminium storage capacity in the deep layer is many more, and what the concentration of aluminium reduced in the infiltration layer is slow more.But depth of penetration thickening or al concn increase, and infiltration layer becomes fragile, the remarkably influenced fatigue property, and therefore, for spinner blade, infiltration layer should be controlled at 0.04mm and be advisable with interior.
The preparation method of hollow blade inner chamber resistance to high temperature oxidation provided by the invention and corrosion diffusion infiltration layer; Its advantage is: make the working temperature of nickel base superalloy blade bring up to 1050 ℃～1100 ℃ from 900 ℃; Can make blade inner chamber and outside surface prepare infiltration layer simultaneously, and can significantly improve resistance to high temperature oxidation, the corrosive power of blade.
Description of drawings
Fig. 1 is infiltration layer metallographic structure figure.
Embodiment
Embodiment 1
The gas turbine hollow blade is carried out the preparation of resistance to high temperature oxidation and corrosion diffusion infiltration layer, and the material of gas turbine hollow blade is the K465 nickel base superalloy, concrete preparation method is following:
---the preparation penetration enhancer:
(1), preparation nickel chromium triangle penetration enhancer: chromium powder, nickel powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with the nickel chromium triangle penetration enhancer according to following weight ratio;
Chromium powder 7%; Nickel powder 27%;
Aluminium oxide powder 60%; Nickel-yittrium alloy powder 5%;
The ammonium chloride surplus;
(2), preparation chromium aluminium penetration enhancer: chromium powder, aluminium powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with chromium aluminium penetration enhancer according to following weight ratio;
Chromium powder 38%; Aluminium powder 5%;
Aluminium oxide powder 51%; Nickel-yittrium alloy powder 5%;
The ammonium chloride surplus;
---the roasting penetration enhancer:
(3), with nickel chromium triangle penetration enhancer of preparation in (1) through 1000 ℃～1050 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
(4), with chromium aluminium penetration enhancer of preparation in (2) through 1100 ℃～1150 ℃/1h ~ 2h and 950 ℃～1000 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
---the preparation infiltration layer:
(5), the nickel chromium triangle penetration enhancer after roasting in (3) is poured in the blade inner chamber, and blade imbedded with the nickel chromium triangle penetration enhancer ooze in the jar, put into the vacuum oven internal heating then; At first be heated to 400 ℃, insulation 1.5h～2h is warming up to 800 ℃ again; Insulation 1h, 1000 ℃～1100 ℃ of the outlet temperatures of intensification value again, insulation 4h～5h; Cool to the furnace below 200 ℃, come out of the stove.
(6), the nickel chromium triangle penetration enhancer on the blade of coming out of the stove in (5) cleaned out after, again the chromium aluminium penetration enhancer after roasting in (4) is poured in the blade inner chamber, and blade imbedded with chromium aluminium penetration enhancer oozes in the jar, put into the vacuum oven internal heating then; At first be heated to 400 ℃, insulation 1.5h～2h is warming up to 800 ℃ again; Insulation 1h is warming up to 1000 ℃ again, insulation 2h; Be warming up to 1050 ℃ again, insulation 2h is warming up to 1100 ℃～1200 ℃ of outlet temperatures again; Insulation 1h～1.5h is chilled to below 200 ℃ with stove, comes out of the stove.
Finally make the resistance to high temperature oxidation and the corrosion diffusion infiltration layer of gas turbine hollow blade, Fig. 1 is seen in its infiltration layer metallographic structure.Whole infiltration layer two-layerly is made up of inside and outside; Outer also have a spot of strip phase mutually except that the infiltration layer base, and internal layer is distributed alternately mutually by many granular strips and constitutes, the concentration of element analytical results shows that the obvious raising of outer Al concentration has reached more than 20%; Can form β-NiAl phase; Internal layer phase structure more complicated possibly comprise that NiAl phase, γ ' phase and various carbide equate that alloying layer thickness is about 0.02mm～0.035mm.
Comparative Examples 1
Get with gas turbine hollow blade identical among the embodiment 1, material is the K465 nickel base superalloy, but no any infiltration layer on the K465 nickel base superalloy.
Infiltration layer is anti-oxidant, the corrosive nature test:
K465 nickel base superalloy and the K465 nickel base superalloy of no any infiltration layer to oozing behind nickel chromium triangle-chromium aluminium carry out anti-oxidant, corrosion test, and test structure is seen table 1, table 2.With K465 alloy phase ratio, the antioxidant property that oozes the K465 alloy behind nickel chromium triangle-chromium aluminium has improved 1.16 times, and the infiltration layer corrosion resistance has improved 36 times.
Principal element anti-oxidant behind the NiCr-CrAl, that corrosion resistance improves that the K465 alloy oozes be the high NiAl of formation of Al in the infiltration layer, Cr concentration mutually and α-Cr contribution mutually, it is owing to formed the good Al of fine and close protective value on the surface that the aluminide infiltration layer has protective value
2O
3Film.
Table 1: oxidation test result (test conditions: 1050 ℃ of test temperatures, 100h)
| Sample | The K465 alloy | The K465 alloy of band NiCr-CrAl infiltration layer |
| Test period h | 100 | 100 |
| Oxidation rate g/m 2h | 0.028 | 0.024 |
Wherein, the K465 alloy surface is faint yellow, and oxidation comes off less; The K465 alloy of band NiCr-CrAl infiltration layer is complete anti-oxidant level at 1050 ℃.
2:900 ℃/100h of table thermal etching test-results (test conditions: 900 ℃ of test temperatures, oil mass 0.2L/h, salt concn 20 * 10
-5, time 100h)
| Sample | The K465 alloy | The K465 alloy of band NiCr-CrAl infiltration layer |
| Test period h | Weight change g/m 2 | Weight change g/m 2 |
| 0 | 0 | 0 |
| 25 | -79.18 | 2.04 |
| 50 | -313.27 | 2.65 |
| 75 | -821.40 | 3.57 |
| 100 | -1121.94 | -2.55 |
| After the alkali cleaning, oxidation rate | 1.44? g/m 2h | 0.4? g/m 2h |
Wherein, be deep green after the test of K465 alloy, produce the macro-corrosion product, seriously come off; Be light blue after the K465 alloy test of band NiCr-CrAl infiltration layer, corrosion pit appears in the part, has a spot of corrosion product in the hole, slightly comes off.
Embodiment 2
The gas turbine hollow blade is carried out the preparation of resistance to high temperature oxidation and corrosion diffusion infiltration layer, and the material of gas turbine hollow blade is the K465 nickel base superalloy, concrete preparation method is following:
---the preparation penetration enhancer:
(1), preparation nickel chromium triangle penetration enhancer: chromium powder, nickel powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with the nickel chromium triangle penetration enhancer according to following weight ratio;
Chromium powder 10%; Nickel powder 24%;
Aluminium oxide powder 62%; Nickel-yittrium alloy powder 3%;
The ammonium chloride surplus;
(2), preparation chromium aluminium penetration enhancer: chromium powder, aluminium powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with chromium aluminium penetration enhancer according to following weight ratio;
Chromium powder 39.7%; Aluminium powder 4%;
Aluminium oxide powder 53%; Nickel-yittrium alloy powder 3%;
The ammonium chloride surplus;
---the roasting penetration enhancer:
(3), with nickel chromium triangle penetration enhancer of preparation in (1) through 1000 ℃～1050 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
(4), with chromium aluminium penetration enhancer of preparation in (2) through 1100 ℃～1150 ℃/1h ~ 2h and 950 ℃～1000 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
---the preparation infiltration layer:
(5), the nickel chromium triangle penetration enhancer after roasting in (3) is poured in the blade inner chamber, and blade imbedded with the nickel chromium triangle penetration enhancer ooze in the jar, put into the vacuum oven internal heating then; At first be heated to 400 ℃, insulation 1.5h～2h is warming up to 800 ℃ again; Insulation 1h, 1000 ℃～1100 ℃ of the outlet temperatures of intensification value again, insulation 4h～5h; Cool to the furnace below 200 ℃, come out of the stove.
(6), the nickel chromium triangle penetration enhancer on the blade of coming out of the stove in (5) cleaned out after, again the chromium aluminium penetration enhancer after roasting in (4) is poured in the blade inner chamber, and blade imbedded with chromium aluminium penetration enhancer oozes in the jar, put into the vacuum oven internal heating then; At first be heated to 400 ℃, insulation 1.5h～2h is warming up to 800 ℃ again; Insulation 1h is warming up to 1000 ℃ again, insulation 2h; Be warming up to 1050 ℃ again, insulation 2h is warming up to 1100 ℃～1200 ℃ of outlet temperatures again; Insulation 1h～1.5h is chilled to below 200 ℃ with stove, comes out of the stove.
Finally make the resistance to high temperature oxidation and the corrosion diffusion infiltration layer of gas turbine hollow blade; Whole infiltration layer two-layerly is made up of inside and outside; Outer also have a spot of strip phase mutually except that the infiltration layer base, and internal layer is distributed alternately mutually by many granular strips and constitutes, the concentration of element analytical results shows that the obvious raising of outer Al concentration has reached more than 20%; Can form β-NiAl phase; Internal layer phase structure more complicated possibly comprise that NiAl phase, γ ' phase and various carbide equate that alloying layer thickness is about 0.02mm～0.035mm.
Comparative Examples 2
The gas turbine hollow blade is carried out the preparation of Al infiltration layer, and the material of gas turbine hollow blade is the K465 nickel base superalloy, wherein the Al infiltration layer prepares according to the method for routine.
Infiltration layer is anti-oxidant, the corrosive nature test:
K465 alloy to oozing behind the Al carries out anti-oxidant, corrosion test with the K465 alloy that oozes behind nickel chromium triangle-chromium aluminium, and test structure is seen table 3, table 4.With the K465 alloy phase ratio that oozes behind the Al, the antioxidant property and the corrosion resistance that ooze the K465 alloy behind nickel chromium triangle-chromium aluminium all are improved.
Principal element anti-oxidant behind the NiCr-CrAl, that corrosion resistance improves that the K465 alloy oozes be the high NiAl of formation of Al in the infiltration layer, Cr concentration mutually and α-Cr contribution mutually, it is owing to formed the good Al of fine and close protective value on the surface that the aluminide infiltration layer has protective value
2O
3Film.
Table 3: oxidation test result (test conditions: 1050 ℃ of test temperatures, 100h)
| Sample | Band Al infiltration layer | Band NiCr-CrAl infiltration layer |
| Test period h | 100 | 100 |
| Oxidation rate g/m2h | 0.027 | 0.024 |
The hot brine corrosion test-results of 4:950 ℃/100h of table (test conditions: 950 ℃ of test temperatures, 75%Na
2SO
4+ 25%NaCl)
| Sample | Band Al infiltration layer | Band NiCr-CrAl infiltration layer |
| Test period h | Weight change g/m 2 | Weight change g/m 2 |
| 0 | 0 | 0 |
| 25 | 1.16 | 0.12 |
| 50 | -5.72 | 0.56 |
| 75 | -30.80 | -1.60 |
| 100 | -220 | -5.58 |
Wherein, be green after the test of K465 alloy band Al infiltration layer, produce more corrosion product, seriously come off; Be light blue after the K465 alloy test of band NiCr-CrAl infiltration layer, corrosion pit appears in the part, has a spot of corrosion product in the hole, slightly comes off.
Embodiment 3
The gas turbine hollow blade is carried out the preparation of resistance to high temperature oxidation and corrosion diffusion infiltration layer, and the material of gas turbine hollow blade is the K465 nickel base superalloy, concrete preparation method is following:
---the preparation penetration enhancer:
(1), preparation nickel chromium triangle penetration enhancer: chromium powder, nickel powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with the nickel chromium triangle penetration enhancer according to following weight ratio;
Chromium powder 8%; Nickel powder 25%;
Aluminium oxide powder 61%; Nickel-yittrium alloy powder 4%;
The ammonium chloride surplus;
(2), preparation chromium aluminium penetration enhancer: chromium powder, aluminium powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with chromium aluminium penetration enhancer according to following weight ratio;
Chromium powder 39%; Aluminium powder 6%;
Aluminium oxide powder 51%; Nickel-yittrium alloy powder 3%;
The ammonium chloride surplus;
---the roasting penetration enhancer:
(3), with nickel chromium triangle penetration enhancer of preparation in (1) through 1000 ℃～1050 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
(4), with chromium aluminium penetration enhancer of preparation in (2) through 1100 ℃～1150 ℃/1h ~ 2h and 950 ℃～1000 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
---the preparation infiltration layer:
(5), the nickel chromium triangle penetration enhancer after roasting in (3) is poured in the blade inner chamber, and blade imbedded with the nickel chromium triangle penetration enhancer ooze in the jar, put into the vacuum oven internal heating then; At first be heated to 400 ℃, insulation 1.5h～2h is warming up to 800 ℃ again; Insulation 1h, 1000 ℃～1100 ℃ of the outlet temperatures of intensification value again, insulation 4h～5h; Cool to the furnace below 200 ℃, come out of the stove.
(6), the nickel chromium triangle penetration enhancer on the blade of coming out of the stove in (5) cleaned out after, again the chromium aluminium penetration enhancer after roasting in (4) is poured in the blade inner chamber, and blade imbedded with chromium aluminium penetration enhancer oozes in the jar, put into the vacuum oven internal heating then; At first be heated to 400 ℃, insulation 1.5h～2h is warming up to 800 ℃ again; Insulation 1h is warming up to 1000 ℃ again, insulation 2h; Be warming up to 1050 ℃ again, insulation 2h is warming up to 1100 ℃～1200 ℃ of outlet temperatures again; Insulation 1h～1.5h is chilled to below 200 ℃ with stove, comes out of the stove.
Finally make the resistance to high temperature oxidation and the corrosion diffusion infiltration layer of gas turbine hollow blade; Whole infiltration layer two-layerly is made up of inside and outside; Outer also have a spot of strip phase mutually except that the infiltration layer base, and internal layer is distributed alternately mutually by many granular strips and constitutes, the concentration of element analytical results shows that the obvious raising of outer Al concentration has reached more than 20%; Can form β-NiAl phase; Internal layer phase structure more complicated possibly comprise that NiAl phase, γ ' phase and various carbide equate that alloying layer thickness is about 0.02mm～0.035mm.
Comparative Examples 3
The gas turbine hollow blade is carried out the preparation of AlSi infiltration layer, and the material of gas turbine hollow blade is the K465 nickel base superalloy, wherein the AlSi infiltration layer prepares according to the method for routine.
Infiltration layer is anti-oxidant, the corrosive nature test:
K465 alloy to oozing behind the AlSi carries out anti-oxidant, corrosion test with the K465 alloy that oozes behind nickel chromium triangle-chromium aluminium,, test structure is seen table 5, table 6.With the K465 alloy phase ratio that oozes AlSi, the antioxidant property and the corrosion resistance that ooze the K465 alloy behind nickel chromium triangle-chromium aluminium all are improved.
Principal element anti-oxidant behind the NiCr-CrAl, that corrosion resistance improves that the K465 alloy oozes be the high NiAl of formation of Al in the infiltration layer, Cr concentration mutually and α-Cr contribution mutually, it is owing to formed the good Al of fine and close protective value on the surface that the aluminide infiltration layer has protective value
2O
3Film.
Table 5: oxidation test result (test conditions: 1050 ℃ of test temperatures, 100h)
| Sample | Band AlSi infiltration layer | Band NiCr-CrAl infiltration layer |
| Test period h | 100 | 100 |
| Oxidation rate g/m2h | 0.025 | 0.024 |
The hot brine corrosion test-results of 6:950 ℃/100h of table (test conditions: 950 ℃ of test temperatures, 75%Na
2SO
4+ 25%NaCl)
| Sample | Band AlSi infiltration layer | Band NiCr-CrAl infiltration layer |
| Test period h | Weight change g/m 2 | Weight change g/m 2 |
| 0 | 0 | 0 |
| 25 | 1.25 | 0.12 |
| 50 | -4.36 | 0.56 |
| 75 | -16.70 | -1.60 |
| 100 | -74.21 | -5.58 |
Wherein, K465 alloy band AlSi infiltration layer test back mazarine produces corrosion product, local shedding; Be light blue after the K465 alloy test of band NiCr-CrAl infiltration layer, corrosion pit appears in the part, has a spot of corrosion product in the hole, slightly comes off.
Claims (2)
1. the preparation method of hollow blade inner chamber resistance to high temperature oxidation and corrosion diffusion infiltration layer, it is characterized in that: concrete preparation process is following,
---the preparation penetration enhancer:
(1), preparation nickel chromium triangle penetration enhancer: chromium powder, nickel powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with the nickel chromium triangle penetration enhancer according to following weight ratio;
Chromium powder 7% ~ 10%; Nickel powder 24% ~ 27%;
Aluminium oxide powder 60% ~ 62%; Nickel-yittrium alloy powder 3% ~ 5%;
The ammonium chloride surplus;
(2), preparation chromium aluminium penetration enhancer: chromium powder, aluminium powder, aluminium oxide powder, nickel-yittrium alloy powder, ammonium chloride are mixed with chromium aluminium penetration enhancer according to following weight ratio;
Chromium powder 38% ~ 40%; Aluminium powder 4% ~ 6%;
Aluminium oxide powder 51% ~ 53%; Nickel-yittrium alloy powder 3% ~ 5%;
The ammonium chloride surplus;
---the roasting penetration enhancer:
(3), with nickel chromium triangle penetration enhancer of preparation in (1) through 1000 ℃～1050 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
(4), with chromium aluminium penetration enhancer of preparation in (2) through 1100 ℃～1150 ℃/1h ~ 2h and 950 ℃～1000 ℃/1h ~ 2h roasting, sieve with 60 mesh then, for use in the container that seals of packing into;
---the preparation infiltration layer:
(5), the nickel chromium triangle penetration enhancer after roasting in (3) is poured in the blade inner chamber, and blade imbedded with the nickel chromium triangle penetration enhancer ooze in the jar, put into the vacuum oven internal heating then; At first be heated to 400 ℃, insulation 1.5h～2h is warming up to 800 ℃ again; Insulation 1h, 1000 ℃～1100 ℃ of the outlet temperatures of intensification value again, insulation 4h～5h; Cool to the furnace below 200 ℃, come out of the stove.
(6), the nickel chromium triangle penetration enhancer on the blade of coming out of the stove in (5) cleaned out after, again the chromium aluminium penetration enhancer after roasting in (4) is poured in the blade inner chamber, and blade imbedded with chromium aluminium penetration enhancer oozes in the jar, put into the vacuum oven internal heating then; At first be heated to 400 ℃, insulation 1.5h～2h is warming up to 800 ℃ again; Insulation 1h is warming up to 1000 ℃ again, insulation 2h; Be warming up to 1050 ℃ again, insulation 2h is warming up to 1100 ℃～1200 ℃ of outlet temperatures again; Insulation 1h～1.5h is chilled to below 200 ℃ with stove, comes out of the stove.
2. according to the preparation method of claim 1 said hollow blade inner chamber resistance to high temperature oxidation and corrosion diffusion infiltration layer, it is characterized in that: described hollow blade is the nickel base superalloy hollow blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010568276 CN102485934B (en) | 2010-12-01 | 2010-12-01 | Method for preparing hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010568276 CN102485934B (en) | 2010-12-01 | 2010-12-01 | Method for preparing hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102485934A true CN102485934A (en) | 2012-06-06 |
| CN102485934B CN102485934B (en) | 2013-06-05 |
Family
ID=46151508
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010568276 Active CN102485934B (en) | 2010-12-01 | 2010-12-01 | Method for preparing hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102485934B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103628022A (en) * | 2013-12-20 | 2014-03-12 | 攀枝花钢城集团有限公司 | Zinc residue double-vacuum purification charging basket anti-corrosion method |
| CN104745904A (en) * | 2015-04-24 | 2015-07-01 | 陈思 | Oil delivery pump for oil refinery |
| CN104862639A (en) * | 2015-05-29 | 2015-08-26 | 北方民族大学 | Preparation method of high-temperature-resistant, heat-corrosion-resistant and abrasion-resistant coating and penetrating agent |
| CN105385985A (en) * | 2015-11-20 | 2016-03-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for manufacturing penetration layer for improving high-temperature-oxidation resistance of K444 alloy |
| CN105420668A (en) * | 2015-11-20 | 2016-03-23 | 沈阳黎明航空发动机(集团)有限责任公司 | Technological method for cobalt permeating of nickel base alloy |
| CN109628878A (en) * | 2018-11-29 | 2019-04-16 | 中国航发沈阳黎明航空发动机有限责任公司 | A method of improve that turbo blade surface of internal cavity is anti-oxidant and corrosive nature |
| CN111575646A (en) * | 2020-06-11 | 2020-08-25 | 南京国重新金属材料研究院有限公司 | Chromizing and aluminizing process for aero-engine blade |
| CN111876724A (en) * | 2020-07-30 | 2020-11-03 | 西安热工研究院有限公司 | Method for preventing high-temperature bolt threads of steam turbine of thermal power plant from being seized |
| CN113088904A (en) * | 2021-03-01 | 2021-07-09 | 西安交通大学 | Metal Cr coating with nano multilevel structure and preparation method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59205468A (en) * | 1983-05-10 | 1984-11-21 | Natl Res Inst For Metals | High temperature corrosion resistant material |
| JPH09166001A (en) * | 1995-12-15 | 1997-06-24 | Hitachi Ltd | Coated layer forming method of gas turbine blade and internal cooling passage |
| CN1431338A (en) * | 2002-01-10 | 2003-07-23 | 北京航空航天大学 | Method for preparing coat of aluminide with chrome modified for enhancing performance of high heat oxidation resistance of TiAl alloy |
| US20050265851A1 (en) * | 2004-05-26 | 2005-12-01 | Murali Madhava | Active elements modified chromium diffusion patch coating |
| CN101168833A (en) * | 2007-11-29 | 2008-04-30 | 苏州市万泰真空炉研究所有限公司 | Solid chromizing technique |
| CN101348893A (en) * | 2007-07-20 | 2009-01-21 | 通用电气公司 | Aluminizing method for jet engine blade serpentine cooling channel |
-
2010
- 2010-12-01 CN CN 201010568276 patent/CN102485934B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59205468A (en) * | 1983-05-10 | 1984-11-21 | Natl Res Inst For Metals | High temperature corrosion resistant material |
| JPH09166001A (en) * | 1995-12-15 | 1997-06-24 | Hitachi Ltd | Coated layer forming method of gas turbine blade and internal cooling passage |
| CN1431338A (en) * | 2002-01-10 | 2003-07-23 | 北京航空航天大学 | Method for preparing coat of aluminide with chrome modified for enhancing performance of high heat oxidation resistance of TiAl alloy |
| US20050265851A1 (en) * | 2004-05-26 | 2005-12-01 | Murali Madhava | Active elements modified chromium diffusion patch coating |
| CN101348893A (en) * | 2007-07-20 | 2009-01-21 | 通用电气公司 | Aluminizing method for jet engine blade serpentine cooling channel |
| CN101168833A (en) * | 2007-11-29 | 2008-04-30 | 苏州市万泰真空炉研究所有限公司 | Solid chromizing technique |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103628022B (en) * | 2013-12-20 | 2016-08-17 | 攀枝花钢城集团有限公司 | Double-vacuum purification charging basket anti-corrosion method |
| CN103628022A (en) * | 2013-12-20 | 2014-03-12 | 攀枝花钢城集团有限公司 | Zinc residue double-vacuum purification charging basket anti-corrosion method |
| CN104745904A (en) * | 2015-04-24 | 2015-07-01 | 陈思 | Oil delivery pump for oil refinery |
| CN104862639A (en) * | 2015-05-29 | 2015-08-26 | 北方民族大学 | Preparation method of high-temperature-resistant, heat-corrosion-resistant and abrasion-resistant coating and penetrating agent |
| CN104862639B (en) * | 2015-05-29 | 2017-09-12 | 北方民族大学 | The preparation technology and its penetration enhancer of a kind of high temperature resistant heat and corrosion resistant anti-scuff coating |
| CN105385985A (en) * | 2015-11-20 | 2016-03-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for manufacturing penetration layer for improving high-temperature-oxidation resistance of K444 alloy |
| CN105420668A (en) * | 2015-11-20 | 2016-03-23 | 沈阳黎明航空发动机(集团)有限责任公司 | Technological method for cobalt permeating of nickel base alloy |
| CN105385985B (en) * | 2015-11-20 | 2018-07-27 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of infiltration layer preparation method improving K444 alloy high temperature oxidation resistances |
| CN105420668B (en) * | 2015-11-20 | 2018-08-14 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of nickel-base alloy oozes cobalt process |
| CN109628878A (en) * | 2018-11-29 | 2019-04-16 | 中国航发沈阳黎明航空发动机有限责任公司 | A method of improve that turbo blade surface of internal cavity is anti-oxidant and corrosive nature |
| CN111575646A (en) * | 2020-06-11 | 2020-08-25 | 南京国重新金属材料研究院有限公司 | Chromizing and aluminizing process for aero-engine blade |
| CN111876724A (en) * | 2020-07-30 | 2020-11-03 | 西安热工研究院有限公司 | Method for preventing high-temperature bolt threads of steam turbine of thermal power plant from being seized |
| CN113088904A (en) * | 2021-03-01 | 2021-07-09 | 西安交通大学 | Metal Cr coating with nano multilevel structure and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102485934B (en) | 2013-06-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102485934B (en) | Method for preparing hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance | |
| CN101133188B (en) | Layered matrix and system | |
| US4419416A (en) | Overlay coatings for superalloys | |
| US4585481A (en) | Overlays coating for superalloys | |
| Cheng et al. | High-temperature corrosion of Cr–Mo steel in molten LiNO3–NaNO3–KNO3 eutectic salt for thermal energy storage | |
| EP2612951B1 (en) | Method for making a honeycomb seal | |
| USRE32121E (en) | Overlay coatings for superalloys | |
| CN101435066B (en) | Slurry diffusion aluminide coating composition and process | |
| CN103614691B (en) | A kind of slip type aluminising silicon means of defence of DD6 single crystal super alloy blade | |
| CN102181860A (en) | Method for forming Pt-modified NiAl+Ni3Al thermal barrier adhering layer on surface of nickel-based super alloy | |
| Liu et al. | Improved hot corrosion resistance of Y–Ce–Co-modified aluminide coating on nickel base superalloys by pack cementation process | |
| CN105385985B (en) | A kind of infiltration layer preparation method improving K444 alloy high temperature oxidation resistances | |
| JPS6136061B2 (en) | ||
| CN102345122A (en) | Multipurpose low-conductivity ceramic/noble metal lamellar composite thermal barrier coating | |
| US4284688A (en) | Multi-layer, high-temperature corrosion protection coating | |
| CN1948218B (en) | High temperature anti oxidation material and high temperature antioxidation coating layer prepared from same | |
| WO2006076013A2 (en) | Improved chromium diffusion coatings | |
| CN103266298B (en) | Stainless steel low-temperature powder embedding Fe-Al permeation penetration enhancer and pack cementation processing method | |
| Liu et al. | Cyclic oxidation resistance of Ce/Co modified aluminide coatings on nickel base superalloys | |
| Narita et al. | Advanced coatings on high temperature applications | |
| CN102061468B (en) | High-temperature oxidation-resistant material and method for preparing high-temperature oxidation-resistant coating by using same | |
| US20050265851A1 (en) | Active elements modified chromium diffusion patch coating | |
| JP2022522642A (en) | Honeycomb structure containing abradable material | |
| CN104109793B (en) | A kind of alumina-based ceramic metal and application thereof | |
| Jithesh et al. | An investigation on hot corrosion and oxidation behavior of cobalt-based superalloy L605 in the simulated aero-engine environment at various temperatures |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |