Turbine engine hybrid rotor

Patent metadata

Field	Value
Publication number	US-10364677-B2
Application number	US-201414772192-A
Country	US
Kind code	B2
Filing date	Mar 11, 2014
Priority date	Mar 15, 2013
Publication date	Jul 30, 2019
Grant date	Jul 30, 2019

Abstract

A turbine engine rotor component has a Ti-based first member (66) circumscribing an axis (500) and has either a circumferential array of integrally formed airfoils (62) or a circumferential array of blade retention features. A TiB particulate reinforced second member (90) also circumscribes the axis.

First claim

What is claimed is:

1. A turbine engine rotor component comprising:
a Ti-based first member ( 6 ) circumscribing an axis ( 500 ) and having either a circumferential array of integrally-formed airfoils ( 62 ) or a circumferential array of blade retention features; and
a TiB w particulate-reinforced second member ( 90 ) circumscribing the axis.

2. The component of claim 1 wherein:
the second member is diffusion bonded to the first member.

3. The component of claim 1 wherein at 28° C. one to all of:
the second member has higher yield tensile strength than the first member;
the second member has higher ultimate tensile strength than the first member;
the second member has higher modulus than the first member;
the first member is more machinable than the second member; and
the first member has higher fatigue strength than the second member.

4. The component of claim 3 wherein:
the second member is a powder-metallurgical member.

5. The component of claim 4 wherein:
the first member is a non-powder-metallurgical member.

6. The component of claim 5 wherein:
the first member and the second member each account for at least 20% of weight of the turbine engine rotor component.

7. The component of claim 1 wherein one or both of:
the second member has higher boron content than the first member; and
the second member has higher TiB than the first member.

8. The component of claim 1 wherein in axial cross-section:
the first member has a pocket ( 120 ) open either one or more of inboard, outboard, fore, and aft; and
the second member is accommodated in the pocket.

9. The component of claim 1 wherein:
the component lacks a protuberant bore.

10. A method for manufacturing the component of claim 1 , the method comprising:
forming the first member;
forming the second member; and
securing the second member to the first member.

11. The method of claim 10 wherein the securing comprises diffusion bonding.

12. The method of claim 11 wherein:
the forming of the first member comprises a non-powder-metallurgical technique; and
the forming of the second member comprises a powder-metallurgical technique.

13. A turbine engine rotor component comprising:
a Ti-based first member ( 66 ) circumscribing an axis ( 500 ) and having either a circumferential array of integrally-formed airfoils ( 62 ) or a circumferential array of blade retention features; and
a TiB particulate-reinforced second member ( 90 ) circumscribing the axis, wherein one to all of:
the first member has a boron content of less than 0.1% by weight;
the first member has a 28° C. ultimate tensile strength of less than 1.25 GPa;
the second member has a boron content of at least 0.5% by weight; and
the second member has a 28° C. ultimate tensile strength of more than 1.38 GPa.

14. The component of claim 13 wherein one to all of:
the first member has a boron content of less than 0.05% by weight;
the first member has a 28° C. ultimate tensile strength of less than 1.10 GPa;
the second member has a boron content of 0.5-2.0% by weight; and
the second member has a 28° C. ultimate tensile strength of more than 1.17 GPa.

15. A turbine engine ( 20 ) comprising:
an engine case ( 22 ); and
a compressor component comprising:
a Ti-based first member ( 66 ) circumscribing an axis ( 500 ) and having either a circumferential array of integrally-formed airfoils ( 62 ) or a circumferential array of blade retention features; and
a TiB particulate-reinforced second member ( 90 ) circumscribing the axis.

16. The turbine engine of claim 15 wherein:
the compressor component is an integrally-bladed ring.

17. The turbine engine of claim 15 wherein:
the second member is accommodated in a pocket ( 120 ) of the first member and is partially exposed.

18. The turbine engine of claim 15 wherein:
the second member is diffusion bonded to the first member.

19. A turbine engine rotor component comprising:
a Ti-based first member ( 66 ) circumscribing an axis ( 500 ) and having either a circumferential array of integrally-formed airfoils ( 62 ) or a circumferential array of blade retention features; and
a TiB particulate-reinforced second member ( 90 ) circumscribing the axis, wherein in axial cross-section:
the first member has a pocket ( 120 ) open one of fore and aft and closed inboard and outboard; and
the second member is accommodated in the pocket.

20. A turbine engine rotor component comprising:
a Ti-based first member ( 66 ) circumscribing an axis ( 500 ) and having either a circumferential array of integrally-formed airfoils ( 62 ) or a circumferential array of blade retention features; and
a TiB particulate-reinforced second member ( 90 ) circumscribing the axis, wherein:
the first member and the second member each account for at least 20% of weight of the turbine engine rotor component; and
at 28° C. one to all of:
the second member has higher yield tensile strength than the first member;
the second member has higher ultimate tensile strength than the first member;
the second member has higher modulus than the first member;
the first member is more machinable than the second member; and

the first member has higher fatigue strength than the second member.

Assignees

• United Technologies Corp

Inventors

• Hansen James O

Classifications

• C22C1/0458

  Alloys based on titanium, zirconium or hafnium · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/30

  Fixing blades to rotors; Blade roots {; Blade spacers} · 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

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title