Hybrid bonded turbine rotors and methods for manufacturing the same
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B23K-020/00
F01D-005/30
B23K-020/12
B23K-020/22
B23K-020/02
B23K-020/14
B23K-020/08
B23K-009/167
B23K-009/23
B23K-005/14
B23K-005/00
B23K-010/02
B23K-015/00
B23K-026/32
B23K-026/21
F01D-005/08
F01D-005/34
F01D-011/00
B23K-103/08
출원번호
US-0806933
(2015-07-23)
등록번호
US-9951632
(2018-04-24)
발명자
/ 주소
Waldman, David R
Mittendorf, Don
Morris, Mark C.
Vinup, Michael
출원인 / 주소
HONEYWELL INTERNATIONAL INC.
대리인 / 주소
Lorenz & Kopf, LLP
인용정보
피인용 횟수 :
0인용 특허 :
54
초록▼
Hybrid bonded turbine rotors and methods for manufacturing the same are provided. A method for manufacturing a hybrid bonded turbine rotor comprises the steps of providing turbine disk having a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim not
Hybrid bonded turbine rotors and methods for manufacturing the same are provided. A method for manufacturing a hybrid bonded turbine rotor comprises the steps of providing turbine disk having a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with a plurality of raised blade attachment surfaces defining the outer periphery; providing a plurality of turbine blades, each of which comprising an airfoil portion and a shank portion, the shank portion having a base surface; metallurgically bonding a compliant alloy material layer to either or both of the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks; and linear friction welding the plurality of blades to the turbine disk so as to form a bond plane between the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks, the compliant alloy material layer being disposed at the bond plane.
대표청구항▼
1. A method for manufacturing a hybrid bonded turbine rotor comprising the steps of: providing a turbine disk having a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with a plurality
1. A method for manufacturing a hybrid bonded turbine rotor comprising the steps of: providing a turbine disk having a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with a plurality of raised blade attachment surfaces defining the outer periphery, wherein the raised blade attachment surfaces comprise a first metal alloy;providing at least one turbine blade, the at least one turbine blade comprising an airfoil portion and a shank portion, the shank portion having a base surface, wherein the base surface of the blade shank comprises a second metal alloy;metallurgically bonding a compliant alloy material layer to either or both of one or more of the raised blade attachment surfaces of the turbine disk and the base surface of the blade shank, wherein the compliant alloy material layer is bonded only to the one or more of the raised blade attachment surfaces and not any other portion of the turbine disk, only to the base surface of the blade shank and not any other portion of the at least one turbine blade, or only to both the one or more of the raised blade attachment surfaces and the base surface of the blade shank and not any other portion of the turbine disk or the at least one turbine blade, wherein metallurgically bonding is selected from the group consisting of: solid state diffusion bonding with hot iso-static press (HIP), axial load vacuum furnace, transient liquid phase bonding, fusion cladding via tungsten inert gas (TIG) or metal inert gas (MIG), electron beam or laser welding, explosive bonding, high velocity oxygen fuel (HVOF), and plasma spray, and wherein the compliant alloy material layer comprises a third metal alloy; andsubsequent to metallurgically bonding the compliant alloy material layer, linear friction welding the at least one blade to the turbine disk so as to form a bond plane between the one or more of the raised blade attachments surfaces of the turbine disk and the base surface of the blade shank, the compliant alloy material layer being disposed at the bond plane, wherein linear friction welding is performed so as to achieve a linear friction welding temperature at the bond plane that is sufficient to plasticize the third metal alloy,wherein the third metal alloy exhibits a yield strength at the linear friction welding temperature that is relatively closer to a yield strength of a material that is immediately opposite the bond plane from the third metal alloy as compared to a yield strength of the one or both of the first and second metal alloys to which the compliant alloy material layer was metallurgically bonded. 2. The method of claim 1, wherein the compliant alloy material layer is bonded only to the at least one turbine blade and not the turbine disk during the step of metallurgical bonding. 3. The method of claim 2, wherein the third metal alloy comprises a nickel-based or cobalt-based superalloy material. 4. The method of claim 3, wherein the third metal alloy is polycrystalline. 5. The method of claim 1, wherein the compliant alloy material layer is bonded only to the turbine disk and not the at least one turbine blade during the step of metallurgical bonding. 6. The method of claim 5, wherein the third metal alloy comprises a nickel-base superalloy material. 7. The method of claim 6, wherein the third metal alloy is single crystal aligned with a (001) direction of the blade alloy. 8. The method of claim 1, wherein the compliant alloy material layer is bonded to both the at least one turbine blade and to the turbine disk during the step of metallurgical bonding. 9. The method of claim 8, wherein the compliant alloy material layer bonded to the at least one turbine blade and the compliant alloy material layer bonded to the turbine disk both comprise the third metal alloy. 10. The method of claim 8, wherein only one of the compliant alloy material layer bonded to the at least one turbine blade or the compliant alloy material layer bonded to the turbine disk comprises the third metal alloy. 11. The method of claim 1, wherein providing the at least one turbine blade comprises providing a single-crystal nickel-based super-alloy blade. 12. The method of claim 1, wherein providing the turbine disk comprises providing a powder metal nickel-based super-alloy disk. 13. The method of claim 2, wherein the compliant alloy material layer consists of, in its entirety, the third metal alloy.
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