[특허]Bladed gas turbine engine rotors having deposited transition rings and methods for the manufacture thereof

HONEYWELL INTERNATIONAL INC.

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Bladed gas turbine engine rotors having deposited transition rings and methods for the manufacture thereof

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/06 B22F-003/105 B22F-003/15 B23P-015/00 F01D-005/30 F01D-005/34 F01D-005/04 F04D-029/28 F04D-029/32 F04D-029/60 F04D-029/64
출원번호	US-0701262 (2015-04-30)
등록번호	US-9938834 (2018-04-10)
발명자 / 주소	Blumer, Eric Jan, David K. Smoke, Jason Adams, Robbie Joseph Kington, Harry Lester
출원인 / 주소	HONEYWELL INTERNATIONAL INC.
대리인 / 주소	Lorenz & Kopf, LLP
인용정보	피인용 횟수 : 0 인용 특허 : 50

초록
▼

Bladed Gas Turbine Engine (GTE) rotors including deposited transition rings are provided, as are embodiments of methods for manufacturing bladed GTE rotors. In one embodiment, the method includes providing an outer blade ring having an inner circumferential surface defining a central opening, and depositing a deposited transition ring on the inner circumferential surface of the outer blade ring. The outer blade ring can be a full bladed ring or an annular grouping of individually-fabricated bladed pieces. After deposition of the transition ring, a hub disk is inserted into the central opening such that the transition ring extends around an outer circumferential surface of the hub disk. The transition ring is then bonded to the outer circumferential surface of the hub disk utilizing, for example, a hot isostatic pressing technique to join the transition ring and the outer blade ring thereto.

대표
청구항
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1. A method for manufacturing a bladed Gas Turbine Engine (GTE) rotor, the method comprising: providing an outer blade ring having an inner circumferential surface defining a central opening;machining the inner circumferential surface of the outer blade ring;depositing a transition ring on the machined inner circumferential surface of the outer blade ring;after deposition of the transition ring, inserting a hub disk into the central opening such that the transition ring extends around an outer circumferential surface of the hub disk; andbonding the transition ring to the outer circumferential surface of the hub disk to join the transition ring and the outer blade ring thereto. 2. The method of claim 1 wherein depositing the transition ring comprises depositing layers of an alloy material on the inner circumferential surface of the outer blade ring utilizing an additive manufacturing process. 3. The method of claim 1 wherein the depositing the transition ring comprises depositing an alloy material on the inner circumferential surface of the outer blade ring utilizing a high velocity cold spray process. 4. The method of claim 1 wherein depositing the transition ring comprises depositing a plurality of alloy bands extending around the inner circumferential surface of the outer blade ring and substantially coaxial with a rotational axis of the bladed GTE rotor. 5. The method of claim 1 wherein the outer blade ring has a centerline, and wherein the outer blade ring is rotated about the centerline as the transition ring is deposited on the inner circumferential surface. 6. The method of claim 1 further comprising machining an inner circumferential surface of the transition ring after deposition thereof. 7. The method of claim 1 wherein bonding the transition ring to the outer circumferential surface of the hub disk comprises: hermetically sealing a cylindrical interface between the transition ring and the hub disk; andafter hermetically sealing the cylindrical interface, diffusion bonding the transition ring to the hub disk utilizing a Hot Isostatic Pressing (HIP) process. 8. The method of claim 1 further comprising, after bonding the transition ring to the outer circumferential surface of the hub disk, producing a plurality of strain relief features in the bladed GTE rotor extending through the transition ring. 9. The method of claim 1 wherein depositing the transition ring comprises producing the transition ring to have an outer boundary composition at a location radially adjacent the outer blade ring and to have an inner boundary composition at a location radially adjacent the hub disk, the outer boundary composition different than the inner boundary composition. 10. The method of claim 9 further comprising forming the transition ring such that the inner boundary composition contains added grain boundary strengtheners in local regions of recrystallization adjacent the plurality of bladed pieces. 11. The method of claim 1 wherein providing the outer blade ring comprises: obtaining a plurality of bladed pieces; andarranging the plurality of bladed pieces in an annular grouping forming the outer blade ring. 12. The method of claim 11 wherein the transition ring is produced from a material and deposited to a thickness sufficient to bond together the plurality of bladed pieces in the outer blade ring. 13. The method of claim 12 wherein the plurality of bladed pieces remain unbonded until production of the transition ring, and wherein the method further comprises installing tooling around the outer blade ring to maintain the plurality of bladed pieces in their desired position during deposition of the transition ring. 14. A method for manufacturing a bladed Gas Turbine Engine (GTE) component, comprising: arranging a plurality of bladed pieces in a ring formation;machining an inner circumferential surface of the ring formation, while retaining the plurality of bladed pieces in the ring formation utilizing tooling;depositing alloy layers around the machined inner circumferential surface of the ring formation to produce a deposited transition ring bonding the plurality of bladed pieces together;positioning a hub disk in a central opening of the deposited transition ring;sealing a cylindrical interface between the hub disk and the deposited transition ring; andperforming a Hot Isostatic Pressing (HIP) process to diffusion bond the hub disk to the deposited transition ring. 15. The method of claim 14 wherein depositing further comprises varying the composition of one or more alloys deposited during deposition of the alloy layers to impart the deposited transition ring with a radially-graded composition. 16. The method of claim 14 wherein the alloy layers are deposited around the inner circumference of the ring formation utilizing one of the group consisting of an additive manufacturing process and a cold spray deposition process. 17. A method for manufacturing a bladed Gas Turbine Engine (GTE) rotor, the method comprising: providing an outer blade ring having an inner circumferential surface;forming an additively-built transition ring on the inner circumferential surface of the outer blade ring utilizing a three dimensional metal printing process during which multiple alloy bands are deposited by fusing material supplied by at least one superalloy powder source or at least one superalloy wire feed source to gradually build-up the additively-built transition ring in accordance with pre-established three dimensional object data;positioning a hub disk in a central opening of the additively-built transition ring;sealing a cylindrical interface between the hub disk and the additively-built transition ring; andperforming a Hot Isostatic Pressing (HIP) process to diffusion bond the hub disk to the additively-built transition ring. 18. The method of claim 17 wherein providing comprises forming the outer blade ring by arranging a plurality of bladed pieces in an annular grouping, the plurality of bladed pieces each comprising a shank having opposing axial shoulders; wherein the opposing axial shoulders cooperate to define first and second annular tooling contact surfaces when the plurality of bladed pieces is arranged in the annular grouping; andwherein the method further comprises positioning a tooling fixture around the plurality of bladed pieces and in contact with the first and second annular tooling contact surfaces to maintain the plurality of bladed pieces in the annular grouping during deposition of the additively-built transition ring. 19. The method of claim 18 wherein the tooling fixture comprises first and second shrink rings; and wherein the method further comprises positioning the first and second shrink rings around the first and second annular tooling contact surfaces, respectively, to maintain the plurality of bladed pieces in the ring formation during deposition of the additively-built transition ring.

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Bladed gas turbine engine rotors having deposited transition rings and methods for the manufacture thereof

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Bladed gas turbine engine rotors having deposited transition rings and methods for the manufacture thereof

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