Dual alloy turbine rotors and methods for manufacturing the same

Patent metadata

Field	Value
Publication number	US-9724780-B2
Application number	US-201414297406-A
Country	US
Kind code	B2
Filing date	Jun 5, 2014
Priority date	Jun 5, 2014
Publication date	Aug 8, 2017
Grant date	Aug 8, 2017

Abstract

Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.

First claim

What is claimed is:

1. A method for manufacturing a dual alloy turbine rotor, the method comprising the steps of:
positioning a hub within a blade ring to thereby define an interface between the hub and the blade ring, the interface comprising a non-contacting interface or a contacting interface;
enclosing the interface with a pair of diaphragms;
vacuum sealing the interface; and
bonding the blade ring to the hub after the vacuum sealing step,
wherein the step of vacuum sealing the interface comprises brazing the pair of diaphragms to the blade ring and hub respectively using opposing braze gaps spaced away from the interface and configured for receiving braze material.

2. The method of claim 1 , wherein:
the blade ring comprises an assembled blade ring having an inner annular surface and a first coefficient of thermal expansion;
the hub has an outer peripheral surface and a second coefficient of thermal expansion higher than the first coefficient of thermal expansion;
wherein the step of positioning a hub within the blade ring comprises spacing an outer peripheral surface of the hub apart from the inner annular surface of the assembled blade ring to form the non-contacting interface defined by a gap; and wherein the step of vacuum sealing the interface reduces the gap as the assembled blade ring expands less than the hub.

3. The method of claim 1 , wherein:
the blade ring comprises an assembled blade ring having an inner annular surface and a first coefficient of thermal expansion;
the hub has an outer peripheral surface and a second coefficient of thermal expansion less than the first coefficient of thermal expansion; and
wherein the step of positioning a hub within a blade ring comprises positioning the hub within the inner annular surface of the assembled blade ring such that the outer peripheral surface of the hub is in near full or full surface area contact to form the contacting interface; and wherein the step of vacuum sealing the interface forms a gap at the interface as the assembled blade ring expands more than the hub.

4. The method of claim 2 , wherein the step of positioning a hub within a blade ring comprises positioning the hub within the assembled blade ring comprising a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy.

5. The method of claim 1 , wherein the step of positioning a hub within a blade ring comprises positioning the hub within a unitary blade ring integrally cast from an equi-axed alloy.

6. The method of claim 1 , wherein the step of enclosing the interface with a pair of diaphragms comprises selecting a diaphragm from the group consisting of a shim style diaphragm, a substantially U-shaped diaphragm, and a thermal spring diaphragm.

7. A method for manufacturing a dual alloy turbine rotor, the method comprising the steps of:
positioning a hub within a blade ring to thereby define an interface between the hub and the blade ring, the interface comprising a non-contacting interface or a contacting interface;
enclosing the interface with a pair of diaphragms;
vacuum sealing the interface; and
bonding the blade ring to the hub after the vacuum sealing step,
wherein the step of vacuum sealing the interface comprises bonding opposing end portions together of each diaphragm of the pair of diaphragms.

8. A method for manufacturing a dual alloy turbine rotor, the method comprising the steps of:
forming a rotor assembly comprising:
positioning a hub having a centrally formed bore and an outer peripheral surface spaced radially apart from the centrally formed bore within an assembled blade ring, the outer peripheral surface having opposed exterior surfaces, the assembled blade ring having a ring portion with an inner annular surface and a plurality of blades coupled to the ring portion opposite the inner annular surface, the inner annular surface having opposed exterior surfaces, the outer peripheral surface of the hub positioned within the inner annular surface with an interface therebetween, the interface comprising a non-contacting interface if the coefficient of thermal expansion of the hub is greater than that of the assembled blade ring and a contacting interface if the coefficient of thermal expansion of the hub is less than that of the assembled blade ring; and
vacuum sealing the interface by directly bonding a pair of diaphragms to a respective one of the exterior surfaces of the ring portion of the assembled blade ring and a respective one of the exterior surfaces of the outer peripheral surface of the hub so that the pair of diaphragms bridge the interface on opposing sides; and

hot isostatic pressing of the rotor assembly at a hot isostatic pressing temperature and pressure to effect metallurgical bonding of the assembled blade ring to the hub,
wherein the step of vacuum sealing the interface comprises bonding the pair of diaphragms to the assembled blade ring and hub and the step of bonding the pair of diaphragms to the assembled blade ring and hub comprises brazing the pair of diaphragms to the blade ring and hub using opposing braze gaps spaced apart from the interface and configured for receiving braze material.

9. The method of claim 8 , wherein positioning the hub within the assembled blade ring comprises positioning the hub within the assembled blade ring comprising a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy.

10. The method of claim 8 , wherein the step of vacuum sealing the interface comprises bonding the pair of diaphragms to the assembled blade ring, each diaphragm selected from the group consisting of a shim style diaphragm, a substantially U-shaped diaphragm, and a thermal spring diaphragm.

11. The method of claim 8 , further comprising the step of removing the pair of diaphragms.

Assignees

• Honeywell Int Inc

Inventors

• Miner Amandine
• Jan David K
• Mittendorf Don
• Smoke Jason

Classifications

• B23K1/0018

  Brazing of turbine parts · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• B23K1/00

  Soldering, e.g. brazing, or unsoldering (B23K3/00 takes precedence) · CPC title

• F01D5/34

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title

• B23K20/002

  specially adapted for particular articles or work (B23K20/129 takes precedence) · CPC title