CN1621556A - High sintering -resistant thermal barrier coating with high thermal stability and low thermal conductivity - Google Patents
High sintering -resistant thermal barrier coating with high thermal stability and low thermal conductivity Download PDFInfo
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- CN1621556A CN1621556A CN 200410098637 CN200410098637A CN1621556A CN 1621556 A CN1621556 A CN 1621556A CN 200410098637 CN200410098637 CN 200410098637 CN 200410098637 A CN200410098637 A CN 200410098637A CN 1621556 A CN1621556 A CN 1621556A
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Abstract
The thermal barrier coatings with high thermal stability, high sintering temperature and low heat conductivity are formed on nickel-base high temperature alloy base through physical vapor electron beam deposition process and include one adhering material layer and one ceramic material layer. The adhering material is MCrAlY, where M may be Ni alloy element and/or Co alloy element; and the ceramic material is lanthanum cerate La2.0-3.0Ce2O7.0-8.5. The thermal barrier coatings have high smelting point, no phase change, low heat conductivity, chemical stability and thermal expansion matching with nickel-base high temperature alloy base.
Description
Technical field
The present invention relates to a kind of novel thermal barrier coating, specifically, be meant a kind of a kind of novel heat barrier coat material that adopts the electro beam physics vapour deposition method to prepare.
Background technology
Along with aero gas turbine engine develops to high flow capacity ratio, high thrust-weight ratio direction, the turbine engine inlet temperature further improves, and can improve motor efficiency greatly.The design temperature out of 10 grades of aircraft engines of thrust-weight ratio has reached more than the 1850K, and the design temperature out of the aircraft engine of thrust-weight ratio more than 15 grades will be above 2000K.The independent use of existing metallic substance can not be satisfied design and operational requirement.Thermal barrier coating makes it can bear higher use temperature when improving hot-end component resistance to high temperature corrosion ability, and has the working temperature that improves engine, prolongs the hot-end component effect in work-ing life.
In the bilayer structure heat barrier coat material that generally adopts at present, ceramic layer material is 8wt%Y
2O
3-ZrO
2(8YSZ), 8YSZ is acknowledged as a kind of ceramic heat insulating coating material of standard, has higher thermal expansivity, lower thermal conductivity and good thermal-shock resistance, but the life-time service temperature can not be above 1200 ℃.More than 1200 ℃, metastable tetragonal phase converting be the four directions mutually and cube mutually, change the monocline phase then into, produce about 4% volume change, cause disbonding to lose efficacy, make the reduction of thermal barrier coating life-span.
After the major cause that thermal barrier coating lost efficacy was exactly the long term thermal circulation impact, the crack propagation that produces did not cause coating to lose efficacy because stress matches between ceramic layer and the metallic matrix.Therefore need deposit a tack coat between ceramic layer and metallic matrix changes the unmatched problem of stress.Tack coat be for the heat of alleviating ceramic coating and matrix do not match, simultaneously also in order to improve the oxidation-resistance of matrix.Because the tack coat composition has decisive action to rate of oxidation, oxide film composition and integrity and with the factors such as bonding force of matrix, and these factors directly influence the life-span of thermal barrier coating; Simultaneously, tack coat also has important effect to the thermal fatigue life that stops vertical crack expansion, raising matrix.
Summary of the invention
The purpose of this invention is to provide a kind of novel heat barrier coat material, is to adopt the electro beam physics vapour deposition method to plate one deck bonding layer material and ceramic layer material formation at the nickel base superalloy matrix surface.Its ceramic layer material has the high temperature phase stability, the zirconium white partially stabilized with yttrium oxide (8YSZ) compared has lower thermal conductivity and higher thermal expansivity, can alleviate the stress of generation effectively, with the demand of the heat insulation and high temperature oxidation corrosion resistance of the hot-end component that satisfies long service because body material and ceramic layer thermal expansivity do not match.
The present invention is a kind of thermal barrier coating with high thermal stability, high temperature sintering resistant, lower thermal conductivity, constitute by ceramic layer and tack coat, tack coat is located between nickel base superalloy matrix and the ceramic layer, described bonding layer material is MCrAlY, M can be the Ni alloying element, Co alloying element or Ni+Co hybrid alloys element; Described ceramic layer material is lanthanum cerate La
2.0～3.0Ce
2O
7.0～8.5
Described thermal barrier coating, its bonding layer material are NiCrAlY, and the weight percent of component is 55～70% nickel, 22～30% chromium, 8～13% aluminium, 0.5～0.8% yttrium.
Described thermal barrier coating, its bonding layer material are CoCrAlY, and the weight percent of component is 60～75% cobalt, 18～22% chromium, 7～12% aluminium, 0.5～0.8% yttrium.
Described thermal barrier coating, its bonding layer material are NiCoCrAlY, and the weight percent of component is 40～60% nickel, 18～22% cobalt, 19～25% chromium, 7～10% aluminium, 0.5～0.8% yttrium.
Described thermal barrier coating, its ceramic layer material are lanthanum cerate La
2.0～3.0Ce
2O
7.0～8.5
Described thermal barrier coating, its ceramic layer material is compared with the 8YSZ material, and its specific heat reduces by 4%～41%, and thermal diffusivity reduces by 10%～26%, and thermal conductivity reduces by 7%～17%, and thermal expansivity has improved 15%.
The present invention adopts the electro beam physics vapour deposition method to plate one deck bonding layer material and ceramic layer material prepares thermal barrier coating, step of preparation process at the nickel base superalloy matrix surface:
(A) preparation ceramic layer material charge bar:
In proportion with CeO
2And La
2O
3Powder is put into retort furnace after ball milling mixing, coldmoulding, sintering 2～6hrs, and 1400 ℃～1600 ℃ of sintering temperatures make the ceramic charge bar of electro beam physics vapour deposition;
(B) preparation bonding layer material charge bar:
Take by weighing MCrAlY (M can be the Ni alloying element, Co alloying element or Ni+Co hybrid alloys element) alloying element in proportion, 1600 ℃～1800 ℃ of smelting temperatures make electro beam physics vapour deposition bonding layer material metal charge bar through melting;
(C) adopt electro beam physics vapour deposition equipment to prepare coating:
1. above-mentioned (A) and the charge bar that (B) makes are put into first crucible and second crucible of electro beam physics vapour deposition equipment respectively, and the nickel base superalloy matrix is installed on the substrate;
2. be evacuated to required vacuum tightness～10
-4Pa;
3. set the speed of rotation 10～20rpm of rotary plate frame;
Employing electron beam heated substrates to 600～900 ℃, electron-beam voltage 17～19kV;
4. deposit tack coat: prevapourising bonding layer material charge bar, and regulate electronic beam current 1.4～1.8A, charge bar climbing speed 0.8～1.0mm/min, sedimentation rate 1.5～2.0 μ m/min; Draw back baffle plate, the hydatogenesis tack coat begins, and deposits behind deposition 40～60 μ m thickness and finishes;
5. deposited ceramic layer: will be installed on the substrate through the nickel base superalloy matrix after 4. handling, and be adjusted to above second crucible that ceramic charge bar is housed, regulate electronic beam current 1.4～1.8A, charge bar climbing speed 1.2～1.6mm/min, sedimentation rate 2.0～3.0 μ m/min; Draw back baffle plate, the hydatogenesis ceramic layer begins, and takes out after deposition is finished, i.e. thermal barrier coating preparation is finished.
The advantage of heat barrier coat material of the present invention: (1) ceramic layer material has high-melting-point, does not have phase transformation between from the room temperature to the use temperature, and lower thermal conductivity, and chemically stable is with the metallic matrix thermal expansion matching.(2) stupalith La
2Ce
20
7Has higher phase stability at 1400 ℃ of following long term annealings; La
2Ce
2O
7Thermal conductivity than the thermal conductivity of standard 8YSZ approximately low 50%; La
2Ce
2O
7Thermal expansivity than the height of standard 8YSZ.(3) the high speed hydatogenesis prepares tack coat and ceramic layer, the controllable component of each layer.
Description of drawings
Fig. 1 is the cross-sectional view of thermal barrier coating of the present invention.
Fig. 2 is an electro beam physics vapour deposition device structure synoptic diagram.
Fig. 3 (a) is that thermal barrier coating of the present invention prepares attitude surface topography scanned photograph.
Fig. 3 (b) is that thermal barrier coating of the present invention prepares attitude cross-section morphology scanned photograph.
Fig. 3 (c) is that thermal barrier coating of the present invention is through 240 thermal cycling rear surface pattern scanned photograph.
Fig. 3 (d) is thermal barrier coating of the present invention cross-section morphology scanned photograph after 240 thermal cyclings.
Fig. 4 is that the specific heat of ceramic layer material of the present invention and 8YSZ material is with the variation of temperature graph of a relation.
Fig. 5 is the thermal diffusivity and the variation of temperature graph of a relation of ceramic layer material and 8YSZ material.
Fig. 6 is the thermal conductivity and the variation of temperature graph of a relation of ceramic layer material and 8YSZ material.
Fig. 7 is ceramic layer material thermal expansivity and variation of temperature graph of a relation.
Fig. 8 is the XRD figure of ceramic layer material different annealing times under 1400 ℃.
Among the figure: 1. vacuum chamber 2. first crucibles 3. second crucibles
4. tack coat charge bar 5. ceramic layer charge bars 6. baffle plates 7. rotary plate framves 8. electron beam gun
9. electron beam gun 10. substrates 11. ceramic layers 12. tack coats 13. matrixes
Embodiment
The present invention is further illustrated below in conjunction with the drawings and specific embodiments.
In the present invention, the contriver be for prepare a kind of lower than traditional ceramics layer material (8YSZ) thermal conductivity, thermal expansivity is high and the novel heat barrier coat material of the higher use temperature of ability.Adopt the electro beam physics vapour deposition technology, by regulating ceramic layer CeO
2And La
2O
3The original proportioning of two kinds of powder and control hydatogenesis processing parameter obtain identical with the evaporation source material composition and near the coating of chemical dosage ratio.Utilize the characteristics of electro beam physics vapour deposition, prepare thermal barrier coating with columnar crystal structure, distinctive hole perpendicular to ceramic layer and tie-layer interface has further increased the strain tolerance limit of ceramic layer between the column crystal, help improving the work-ing life of thermal barrier coating, satisfy the demand of heat insulation and high temperature oxidation corrosion resistance of the hot-end component of long service.
The present invention is a kind of thermal barrier coating with high thermal stability, high temperature sintering resistant, lower thermal conductivity, is made of ceramic layer and tack coat, and tack coat is located at (as shown in Figure 1) between nickel base superalloy matrix and the ceramic layer.Described bonding layer material is MCrAlY, and M can be the Ni alloying element, Co alloying element or Ni+Co hybrid alloys element; Described ceramic layer material is lanthanum cerate La
2.0～3.0Ce
2O
7.0～8.5The deposit thickness of tack coat and ceramic layer is 1: 1～5.
In the present invention, adopt the method for electro beam physics vapour deposition to prepare the thermal barrier coating with high thermal stability, high temperature sintering resistant, lower thermal conductivity, its technical process is:
(A) preparation ceramic layer material charge bar:
In proportion with CeO
2And La
2O
3Powder is put into retort furnace after ball milling mixing, coldmoulding, sintering 2～6hrs, and 1400 ℃～1600 ℃ of sintering temperatures make the ceramic layer charge bar;
At preparation ceramic layer material lanthanum cerate La
2.0～3.0Ce
2O
7.0～8.5During charge bar, CeO
2With La
2O
3Proportioning be 1: 0.5～0.75, La
2O
3Molar content be 33～43mol%.
(B) preparation bonding layer material charge bar:
Take by weighing MCrAlY (M can be the Ni alloying element, Co alloying element or Ni+Co hybrid alloys element) alloying element in proportion, 1600 ℃～1800 ℃ of smelting temperatures make the tack coat charge bar through melting;
(C) adopt electro beam physics vapour deposition equipment to prepare coating:
1. above-mentioned (A) and the charge bar that (B) makes are put into first crucible 2 and second crucible 3 of electro beam physics vapour deposition equipment respectively, and the nickel base superalloy matrix is installed on the substrate 10;
2. be evacuated to required vacuum tightness～10
-4Pa;
3. set the speed of rotation 10～20rpm of rotary plate frame 7;
Employing electron beam heated substrates to 600～900 ℃, electron-beam voltage 17～19kV;
4. deposit tack coat: prevapourising bonding layer material charge bar, and regulate electronic beam current 1.4～1.8A, charge bar climbing speed 0.8～1.0mm/min, sedimentation rate 1.5～2.0 μ m/min; Draw back baffle plate 6, the hydatogenesis tack coat begins, and takes out after deposition is finished, and puts into vacuum heat treatment furnace and carries out vacuum heat treatment 2～6hrs, 1000～1100 ℃ of thermal treatment temps.
5. deposited ceramic layer: will be installed on the substrate 10 of electro beam physics vapour deposition equipment through the nickel base superalloy matrix after 4. handling, and regulate substrate 10 to second crucible, 3 tops that stupalith is housed, regulate electronic beam current 1.4～1.8A, charge bar climbing speed 1.2～1.6mm/min, sedimentation rate 2.0～3.0 μ m/min; Draw back baffle plate 6, the hydatogenesis ceramic layer begins, and takes out after deposition is finished, i.e. thermal barrier coating preparation is finished.
Fig. 3 is the thermal barrier coating that obtains through above-mentioned process deposits, and the surface topography of deposition attitude is shown in Fig. 3 (a), and the ceramic layer surface has typical columnar crystal structure pattern, and the crystal grain top is pyramid.The cross-section morphology of deposition attitude is shown in Fig. 3 (b), and ceramic layer is made up of the column crystal of densification, and tangible hole is arranged between the column crystal, and this structure has improved the strain tolerance limit of ceramic layer effectively.The thermal barrier coating that deposition is good is incubated 30 minutes in 1050 ℃ of stoves, carried out thermal cycling outside the stove in 5 minutes under the pressurized air cooling conditions, its surface topography is shown in Fig. 3 (c) after 240 thermal cyclings are handled, the column crystal end of ceramic layer becomes smooth, and comparing with the grain-size of deposition attitude does not have considerable change.Its cross-section morphology is shown in Fig. 3 (d) after 240 thermal cyclings are handled, between ceramic layer and tack coat, formed the thermal oxide layer of one deck densification, this is because the metallic element in the tack coat spreads from inside to outside, tie layer surface with spread the oxygen of coming in by the column crystal gap by the external world and react and forms continuous and compact oxide.Thermal oxide layer can stop the further oxidation of tack coat effectively, thereby improves the corrosion and heat resistant of metal parts and the work-ing life of hot-end component.
Concrete material component for tack coat and ceramic layer in each thermal barrier coating of further instruction is elaborated illustrative example below.
Embodiment 1
Body material is the nickel base superalloy matrix, and bonding layer material is NiCrAlY, and the weight percent of component is 68.5% nickel, 23% chromium, 8% aluminium, 0.5% yttrium, and ceramic layer material is La
2Ce
2O
7, thermal barrier coating.Deposit thickness: tack coat 60 μ m, ceramic layer 200 μ m.
Equipment: Ukraine UE205 electro beam physics vapour deposition equipment (device structure as shown in Figure 2)
Preparation technology:
(A) preparation ceramic layer La
2Ce
2O
7Charge bar:
With CeO
2And La
2O
3Powder was by 1: 0.5 proportioning (La
2O
3Molar content be 33mol%), through ball milling mix, coldmoulding is the charge bar of Φ 50 * 200mm, place in the retort furnace, sintering 4hrs, 1400 ℃ of sintering temperatures make La
2Ce
2O
7Charge bar;
In order to test the performance of ceramic layer material, with a part of CeO
2And La
2O
3Powder is the disk shape sample of Φ 10 * 3.0mm through ball milling mixing, coldmoulding, and puts into retort furnace, sintering 4hrs, and 1400 ℃ of sintering temperatures make La
2Ce
2O
7Sample.This sample is used to measure physicalies such as specific heat, thermal diffusivity, density.
(B) preparation tack coat NiCrAlY charge bar:
Be that 68.5% nickel, 23% chromium, 8% aluminium, 0.5% yttrium take by weighing the NiCrAlY alloying element by weight percentage, 1600 ℃ of smelting temperatures make the tack coat charge bar of Φ 50 * 200mm through melting;
(C) adopt electro beam physics vapour deposition equipment to prepare coating:
1. above-mentioned (A) and the charge bar that (B) makes are put into first crucible 2 and second crucible 3 of electro beam physics vapour deposition equipment respectively, and the nickel base superalloy matrix is installed on the substrate 10;
2. be evacuated to required vacuum tightness 5 * 10
-4Pa;
3. set the speed of rotation 15rpm of rotary plate frame 7;
Adopt electron beam heated substrates to 650 ℃, electron-beam voltage 18kV;
4. deposit tack coat: prevapourising tack coat NiCrAlY charge bar, and regulate electronic beam current 1.6A, charge bar climbing speed 0.8mm/min, sedimentation rate 1.4 μ m/min, deposit thickness 60 μ m, depositing time 45min; Draw back baffle plate 6, the hydatogenesis tack coat begins;
Take out after deposition is finished, put into vacuum heat treatment furnace and carry out vacuum heat treatment 2hrs, 1000 ℃ of thermal treatment temps;
5. deposited ceramic layer: will be installed on the substrate 10 of electro beam physics vapour deposition equipment through the nickel base superalloy matrix after 4. handling, and regulate substrate 10 to second crucible, 3 tops that stupalith is housed, regulate electronic beam current 1.8A, charge bar climbing speed 1.4mm/min, sedimentation rate 2.0 μ m/min, deposit thickness 200 μ m, depositing time 100min; Draw back baffle plate 6, the hydatogenesis ceramic layer begins, and takes out after deposition is finished, i.e. thermal barrier coating preparation is finished.
In the present invention, to ceramic layer La
2Ce
2O
7The physicals test related description of material disk shape sample is as follows:
The equipment that specific heat measurement adopts is Netzsch 449 C type differential thermal analyzers, measuring result as shown in Figure 4, La
2Ce
2O
7Specific heat numerical value be increased to 1.84J/gK along with the rising of temperature is also corresponding from 0.42J/gK, compare low by 4%～41% with 8YSZ.
What thermal diffusivity measure to adopt is laser pulse method, and equipment used is Japanese TC-3000H, measuring result as shown in Figure 5, along with the rising of temperature, La
2Ce
2O
7Thermal diffusivity by 0.18 * 10
-2Cm
2/ s drops to 0.12 * 10
-2Cm
2/ s compares low 10%～26% with 8YSZ.
The specific heat of thermal conductivity and sample, density and thermal diffusivity have direct relation, calculate thermal conductivity by following relational expression:
λ＝D
th(T)C
p(T)ρ(T)
λ represents thermal conductivity in the formula, D
Th(T) expression thermal diffusivity, C
p(T) expression specific heat, ρ (T) represents density.
The calculation result of thermal conductivity as shown in Figure 6, along with the rising of temperature, La
2Ce
2O
7Thermal conductivity be increased to 1.12W/mK by 0.73W/mK, compare low by 7%～17% with 8YSZ.Therefore, ceramic layer La of the present invention
2Ce
2O
7Material has the low characteristics of thermal conductivity, can effectively improve effect of heat insulation, alleviates the thermal etching of combustion gas to metal parts, prolongs the work-ing life of metal parts, further improves the turbine engine working efficiency.
Fig. 7 represents La
2Ce
2O
7Thermal expansivity with the variation of temperature graph of a relation, along with temperature is raised to 1200 ℃ from 300 ℃, thermal expansivity is correspondingly by 4.8 * 10
-6K
-1Be increased to 13.4 * 10
-6K
-1, mean thermal expansion coefficients is 12.3 * 10
-6K
-1, than the mean thermal expansion coefficients 10.5～11.5 * 10 of 8YSZ
-6K
-1Approximately high by 15%.Higher thermal expansivity can be alleviated the stress that is not matched and produced by thermal expansion owing between ceramic layer and the metallic matrix, the work-ing life that can further improve the hot side metal parts effectively.
Fig. 8 represents La
2Ce
2O
7XRD figure under different annealing time conditions under 1400 ℃, as can be seen, among the figure, (a) XRD figure during 25 ℃ of temperature of expression, (b) XRD figure behind 1400 ℃ of annealing of expression temperature 96h, (c) XRD figure behind 1400 ℃ of annealing of expression temperature 192h, (d) XRD figure behind 1400 ℃ of annealing of expression temperature 288h, (e) XRD figure behind 1400 ℃ of annealing of expression temperature 384h obtains La by different time annealing contrast
2Ce
2O
7Behind 1400 ℃ of following long term annealings, there is not cenotype to produce, La is described
2Ce
2O
7Material has good phase stability, is suitable for high-temp heat barrier coating.
Embodiment 2
Body material is the nickel base superalloy matrix, and bonding layer material is CoCrAlY, and the weight percent of component is 70.3% cobalt, 20% chromium, 9% aluminium, 0.7% yttrium, and ceramic layer material is La
2.6Ce
2O
7.9, thermal barrier coating.Deposit thickness: tack coat 60 μ m, ceramic layer 200 μ m.
Equipment: Ukraine UE205 electro beam physics vapour deposition equipment
Preparation technology:
(A) preparation ceramic layer La
2.6Ce
2O
7.9Charge bar:
With CeO
2And La
2O
3Powder was by 1: 0.65 proportioning (La
2O
3Molar content be 39mol%), through ball milling mix, the charge bar of coldmoulding Φ 50 * 200mm, place in the retort furnace, sintering 4hrs, 1400 ℃ of sintering temperatures make La
2.6Ce
2O
7.9Charge bar;
(B) preparation tack coat CoCrAlY charge bar:
Be that 70.3% cobalt, 20% chromium, 9% aluminium, 0.7% yttrium take by weighing the CoCrAlY alloying element by weight percentage, 1600 ℃ of smelting temperatures make the tack coat charge bar of Φ 50 * 200mm through melting;
(C) adopt electro beam physics vapour deposition equipment to prepare coating:
1. above-mentioned (A) and the charge bar that (B) makes are put into first crucible 2 and second crucible 3 of electro beam physics vapour deposition equipment respectively, and the nickel base superalloy matrix is installed on the substrate 10;
2. be evacuated to required vacuum tightness 5 * 10
-4Pa;
3. set the speed of rotation 15rpm of rotary plate frame 7;
Adopt electron beam heated substrates to 650 ℃, electron-beam voltage 18kV;
4. deposit tack coat: prevapourising tack coat CoCrAlY charge bar, and regulate electronic beam current 1.6A, charge bar climbing speed 0.8mm/min, sedimentation rate 1.4 μ m/min, deposit thickness 60 μ m, depositing time 45min; Draw back baffle plate 6, the hydatogenesis tack coat begins;
Take out after deposition is finished, put into vacuum heat treatment furnace and carry out vacuum heat treatment 2hrs, 1100 ℃ of thermal treatment temps;
5. deposited ceramic layer: will be installed on the substrate 10 of electro beam physics vapour deposition equipment through the nickel base superalloy after 4. handling, and regulate substrate 10 to second crucible, 3 tops that stupalith is housed, regulate electronic beam current 1.8A, charge bar climbing speed 1.4mm/min, sedimentation rate 2.0 μ m/min, deposit thickness 200 μ m, depositing time 100min; Draw back baffle plate 6, the hydatogenesis ceramic layer begins, and takes out after deposition is finished, i.e. thermal barrier coating preparation is finished.
Embodiment 3
Body material is the nickel base superalloy matrix, and bonding layer material is NiCoCrAlY, and the weight percent of component is 52.5% nickel, 19% cobalt, 20% chromium, 8% aluminium, 0.5% yttrium, and ceramic layer material is La
3Ce
2O
8.5, thermal barrier coating.Deposit thickness: tack coat 60 μ m, ceramic layer 200 μ m.
Equipment: Ukraine UE205 electro beam physics vapour deposition equipment
Preparation technology:
(A) preparation ceramic layer La
3Ce
2O
8.5Charge bar:
With CeO
2And La
2O
3Powder was by 1: 0.75 proportioning (La
2O
3Molar content be 43mol%), through ball milling mix, the charge bar of coldmoulding Φ 50 * 200mm, place in the retort furnace, sintering 4hrs, 1400 ℃ of sintering temperatures make La
3Ce
2O
8.5Charge bar;
(B) preparation tack coat NiCoCrAlY charge bar:
Be that 52.5% nickel, 19% cobalt, 20% chromium, 8% aluminium, 0.5% yttrium take by weighing the NiCoCrAlY alloying element by weight percentage, 1600 ℃ of smelting temperatures make the tack coat charge bar of Φ 50 * 200mm through melting;
(C) adopt electro beam physics vapour deposition equipment to prepare coating:
1. above-mentioned (A) and the charge bar that (B) makes are put into first crucible 2 and second crucible 3 of electro beam physics vapour deposition equipment respectively, and the nickel base superalloy matrix is installed on the substrate 10;
2. be evacuated to required vacuum tightness 5 * 10
-4Pa;
3. set the speed of rotation 15rpm of rotary plate frame 7;
Adopt electron beam heated substrates to 650 ℃, electron-beam voltage 18kV;
4. deposit tack coat: prevapourising tack coat NiCrAlY charge bar, and regulate electronic beam current 1.6A, charge bar climbing speed 0.8mm/min, sedimentation rate 1.4 μ m/min, deposit thickness 60 μ m, depositing time 45min; Draw back baffle plate 6, the hydatogenesis tack coat begins;
Take out after deposition is finished, put into vacuum heat treatment furnace and carry out vacuum heat treatment 2hrs, 1100 ℃ of thermal treatment temps;
5. deposited ceramic layer: will be installed on the substrate 10 of electro beam physics vapour deposition equipment through the nickel base superalloy matrix after 4. handling, and regulate substrate 10 to second crucible, 3 tops that stupalith is housed, regulate electronic beam current 1.8A, charge bar climbing speed 1.4mm/min, sedimentation rate 2.0 μ m/min, deposit thickness 200 μ m, depositing time 100min; Draw back baffle plate 6, the hydatogenesis ceramic layer begins, and takes out after deposition is finished, i.e. thermal barrier coating preparation is finished.
The thermal barrier coating comprehensively above-mentioned, that the ceramic layer of the different components of listed examples of the present invention and tack coat deposition prepare is being selected lanthanum cerate La for use to ceramic layer material
2.0～3.0Ce
2O
7.0～8.5In the test of its physicals of 8YSZ stupalith, thermal barrier coating of the present invention has high-melting-point, does not have phase transformation between from the room temperature to the use temperature, lower thermal conductivity, and chemically stable is with nickel base superalloy matrix thermal expansion matching.
Claims (9)
1. thermal barrier coating with high thermal stability, high temperature sintering resistant, lower thermal conductivity, constitute by ceramic layer and tack coat, tack coat is located between nickel base superalloy matrix and the ceramic layer, it is characterized in that: described bonding layer material is MCrAlY, M can be the Ni alloying element, Co alloying element or Ni+Co hybrid alloys element; Described ceramic layer material is lanthanum cerate La
2.0～3.0Ce
2O
7.0～8.5
2. thermal barrier coating according to claim 1 is characterized in that: described bonding layer material is NiCrAlY, and the weight percent of component is 55～70% nickel, 22～30% chromium, 8～13% aluminium, 0.5～0.8% yttrium.
3. thermal barrier coating according to claim 1 is characterized in that: described bonding layer material is CoCrAlY, and the weight percent of component is 60～75% cobalt, 18～22% chromium, 7～12% aluminium, 0.5～0.8% yttrium.
4. thermal barrier coating according to claim 1 is characterized in that: described bonding layer material is NiCoCrAlY, and the weight percent of component is 40～60% nickel, 18～22% cobalt, 19～25% chromium, 7～10% aluminium, 0.5～0.8% yttrium.
5. thermal barrier coating according to claim 1 is characterized in that: described ceramic layer material is lanthanum cerate La
2Ce
2O
7
6. thermal barrier coating according to claim 1 is characterized in that: adopt the electro beam physics vapour deposition method to plate one deck bonding layer material and ceramic layer material at the nickel base superalloy matrix surface, step of preparation process:
(A) preparation ceramic layer material charge bar:
In proportion with CeO
2And La
2O
3Powder is put into retort furnace after ball milling mixing, coldmoulding, sintering 2～6hrs, and 1400 ℃～1600 ℃ of sintering temperatures make the ceramic charge bar of electro beam physics vapour deposition;
(B) preparation bonding layer material charge bar:
Take by weighing MCrAlY (M can be the Ni alloying element, Co alloying element or Ni+Co hybrid alloys element) alloying element in proportion, 1600 ℃～1800 ℃ of smelting temperatures make electro beam physics vapour deposition bonding layer material metal charge bar through melting;
(C) adopt electro beam physics vapour deposition equipment to prepare coating:
1. above-mentioned (A) and the charge bar that (B) makes are put into first crucible and second crucible of electro beam physics vapour deposition equipment respectively, and the nickel base superalloy matrix is installed on the substrate;
2. be evacuated to required vacuum tightness～10
-4Pa;
3. set the speed of rotation 10～20rpm of rotary plate frame;
Employing electron beam heated substrates to 600～900 ℃, electron-beam voltage 17～19kV;
4. deposit tack coat: prevapourising bonding layer material charge bar, and regulate electronic beam current 1.4～1.8A, charge bar climbing speed 0.8～1.0mm/min, sedimentation rate 1.5～2.0 μ m/min; Draw back baffle plate, the hydatogenesis tack coat begins, and takes out after deposition is finished, and puts into vacuum heat treatment furnace and carries out vacuum heat treatment 2～6hrs, 1000～1100 ℃ of thermal treatment temps;
5. deposited ceramic layer: will be installed on the substrate through the nickel base superalloy matrix after 4. handling, and be adjusted to above second crucible that ceramic charge bar is housed, regulate electronic beam current 1.4～1.8A, charge bar climbing speed 1.2～1.6mm/min, sedimentation rate 2.0～3.0 μ m/min; Draw back baffle plate, the hydatogenesis ceramic layer begins, and takes out after deposition is finished, i.e. thermal barrier coating preparation is finished.
7. method for preparing heat barrier coating according to claim 6 is characterized in that: at preparation ceramic layer material lanthanum cerate La
2.0～3.0Ce
2O
7.0～8.5During charge bar, CeO
2With La
2O
3Proportioning be 1: 0.5～0.75, La
2O
3Molar content be 33～43mol%.
8. method for preparing heat barrier coating according to claim 6 is characterized in that: the deposit thickness of tack coat and ceramic layer is 1: 1～5.
9. thermal barrier coating according to claim 1 or 5, it is characterized in that: described ceramic layer material is compared with the 8YSZ material, and its specific heat reduces by 4%～41%, and thermal diffusivity reduces by 10%～26%, thermal conductivity reduces by 7%～17%, and thermal expansivity has improved 15%.
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