Imparting high-temperature wear resistance to turbine blade Z-notches
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/28
C23C-024/08
B22F-007/06
B23K-035/00
F01D-005/00
F01D-011/12
B23K-035/30
B22F-005/04
출원번호
US-0628912
(2015-02-23)
등록번호
US-10221702
(2019-03-05)
발명자
/ 주소
Dawson, Joel T.
DeWet, Danie
Zheng, Qingjun
출원인 / 주소
KENNAMETAL INC.
대리인 / 주소
Meenan, Larry R.
인용정보
피인용 횟수 :
0인용 특허 :
59
초록▼
A method of imparting wear-resistance to a contact face of a turbine blade Z-notch comprising applying a flexible cladding sheet comprising a Co-based cladding alloy and an organic binder to the contact face of the Z-notch, heating the turbine blade Z-notch with flexible cladding sheet thereon to vo
A method of imparting wear-resistance to a contact face of a turbine blade Z-notch comprising applying a flexible cladding sheet comprising a Co-based cladding alloy and an organic binder to the contact face of the Z-notch, heating the turbine blade Z-notch with flexible cladding sheet thereon to volatilize the organic binder and remove it from the cladding sheet, and further heating the turbine blade Z-notch with flexible cladding sheet thereon to sinter the cladding sheet by liquid phase sintering, thereby cladding the cladding sheet to the contact face to produce a wear-resistant layer thereon.
대표청구항▼
1. A method of imparting wear-resistance to a contact face of a turbine blade Z-notch comprising: applying a flexible cladding sheet comprising a Co-based cladding alloy and an organic binder to the contact face of the Z-notch;heating the turbine blade Z-notch with flexible cladding sheet thereon to
1. A method of imparting wear-resistance to a contact face of a turbine blade Z-notch comprising: applying a flexible cladding sheet comprising a Co-based cladding alloy and an organic binder to the contact face of the Z-notch;heating the turbine blade Z-notch with flexible cladding sheet thereon to volatilize the organic binder and remove it from the cladding sheet;further heating the turbine blade Z-notch with flexible cladding sheet thereon to sinter the cladding sheet by liquid phase sintering, thereby cladding the cladding sheet to the contact face to produce a sintered wear-resistant layer thereon;wherein the turbine blade Z-notch is constructed of a Ni-based superalloy and the Co-based cladding alloy comprises between 5 and 20 wt % Cr, between 22 and 32 wt % Mo, between 1 and 4 wt % Si, between 0.05 and 0.5 wt % B, and balance Co, plus incidental impurities;wherein said further heating to sinter the cladding sheet is to a temperature between about 2100° F. and about 2280° F.;wherein the cladding sheet has a thickness between about 0.01 and about 0.125 inch. 2. The method of claim 1 wherein the sintering temperature is at least about 50° F. below a solidus temperature of the Z-notch Ni-based alloy and at least about 50° F. below a liquidus temperature of the Co-based cladding alloy. 3. The method of claim 1 wherein the sintering temperature is at least about 100° F. below a solidus temperature of the Z-notch Ni-based alloy. 4. The method of claim 1 wherein the cladding sheet thickness is between 0.02 inch and 0.1 inch. 5. The method of claim 1 wherein the flexible cladding sheet comprises about 92 to about 98 vol. % of the Co-based alloy and about 2 to about 8 vol. % of the organic binder. 6. The method of claim 1 wherein the flexible cladding sheet consists essentially of about 92 to about 98 vol. % of the Co-based alloy and about 2 to about 8 vol. % of the organic binder. 7. The method of claim 6 wherein the Ni-based superalloy has a nominal composition by weight %, of 14 Cr, 9.5 Co, 4.9 Ti, 3.8 W, 3 Al, 2.8 Ta, 1.6 Mo, 0.02 Zr, 0.1 C, 0.012 B, and balance Ni. 8. The method of claim 6 wherein the Ni-based superalloy has a composition, by weight %, of about 9.5-10% Cr, about 7-8% Co, about 3.35-3.65% Ti, about 4.1-4.3% Al, about 5.75-6.25% W, about 1.30-1.70 Mo, about 4.60-5.0% Ta, about 0.06-0.1% C, about 0.008-0.010% Zr, about 0.008-0.0105% B, and the balance being Ni and incidental impurities. 9. The method of claim 6 wherein the Ni-based superalloy has a composition, by weight %, of about 9.4% Co, about 8.2% Cr, about 0.5% Mo, about 9.5% W, about 3.2% Ta, about 5.6% Al, about 0.7 percent % Ti, about 1.5% Hf, about 0.1% C, about 0.015% B, balance Ni, and incidental impurities. 10. The method of claim 1 further comprising subjecting the turbine blade Z-notch contact face with sintered wear-resistant layer thereon to one or more heat treatment operations at a temperature between about 1500° F. and about 2300° F. 11. The method of claim 10 wherein the one or more heat treatment operations comprise a solution heat treatment followed by a precipitation heat treatment. 12. The method of claim 10 wherein the one or more heat treatment operations comprise a solution heat treatment at between 2200° F. and 2300° F. followed by a precipitation heat treatment at between 1550° F. and 1650° F. 13. The method of claim 1 wherein the Ni-based superalloy comprises Cr in range of about 5 to 20 wt %, Co in a range of about 5 to 20 wt %, and at least about 55 wt % Ni. 14. The method of claim 1 wherein the Ni-based superalloy comprises Cr in range of about 5 to 20 wt %, Co in a range of about 5 to 20 wt %, and at least about 55 wt % Ni, with other alloying elements and incidental impurities. 15. The method of claim 1 wherein the Ni-based superalloy comprises, by weight %, 10 to 16 Cr, 7 to 12 Co, 3 to 7 Ti, 2 to 5 W, 1 to 4 Al, 1 to 4 Ta, 1 to 2 Mo, up to 0.1 Zr, 0.05 to 0.2 C, up to 0.1 B, and balance Ni. 16. The method of claim 1, wherein the sintered wear resistant layer comprises nodular particles of Co—Mo—Si. 17. The method of claim 1, wherein the sintered wear resistant layer comprises laves phases. 18. The method of claim 1, wherein a heat affected zone is absent on the substrate. 19. The method of claim 1, wherein an interfacial diffusion zone between the substrate and sintered wear resistant layer is absent. 20. The method of claim 14, wherein the sintered wear resistant layer comprises laves phases.
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