BONDED MULTI-PIECE GAS TURBINE ENGINE COMPONENT

• US 20160265363A1
• Filed: 11/05/2014
• Published: 09/15/2016
• Est. Priority Date: 11/08/2013
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: McCaffrey, Michael G., Alvanos, Ioannis, Abbott, Michael G., Cook, Grant O. III
• Granted Patent: US 10,458,249 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 5/14 Form or construction selecting particular materials, measures against erosion or corrosion F01D5/28
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 5/326 Locking of axial insertion type blades by other means
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/236 Diffusion bonding
• CPC Class Codes: F05D 2230/51 in a modular way, e.g. using several identical or complementary parts or features
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.

Claims

1. An airfoil component comprising:

a first segment including a first piece of a mount and a first piece of an airfoil, the first segment formed of a first ceramic-based material; and

a second segment including a second piece of the mount and a second piece of the airfoil, the second segment formed of a second ceramic-based material, the first and second segments being bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.

2. The airfoil component as recited in claim 1, wherein the bond joint includes a refractory interlayer between the first segment and the second segment.

3. The airfoil component as recited in claim 1, wherein the first and second segments define at least one cavity there between.

4. The airfoil component as recited in claim 3, wherein the at least one cavity has a maximum lateral dimension of 0.51 millimeters or less.

5. The airfoil component as recited in claim 3, wherein the at least one cavity has a maximum lateral dimension of 0.26 millimeters or less.

6. The airfoil component as recited in claim 1, wherein at least one of the first ceramic-based material and the second ceramic-based material is a fiber-reinforced ceramic matrix composite.

7. The airfoil component as recited in claim 1, wherein at least one of the first ceramic-based material and the second ceramic-based material is a laminate fiber-reinforced ceramic matrix composite.

8. The airfoil component as recited in claim 1, wherein at least one of the first ceramic-based material and the second ceramic-based material includes at least one of a carbide and a nitride.

9. The airfoil component as recited in claim 1, wherein the airfoil includes a hollow cavity and the mount is solid.

10. The airfoil component as recited in claim 1, wherein the first segment and the second segment include a radially inner end at the mount and a radially outer end at the airfoil that define a radial direction, the bond joint extending in the radial direction.

11. The airfoil component as recited in claim 1, further including a third segment including at least one of a third piece of the mount and a third piece of the airfoil, the third segment being bonded with at least one of the first segment and the second segment along another bond joint.

12. The airfoil component as recited in claim 11, wherein the third segment includes a third piece of the mount and at least a piece of an endwall of the airfoil.

13. The airfoil component as recited in claim 11, wherein the third segment includes at least a piece of a trailing edge of the airfoil.

14. A gas turbine engine comprising:

optionally, a fan;

a compressor section;

a combustor in fluid communication with the compressor section;

a turbine section in fluid communication with the combustor; and

an airfoil in at least one of the optional fan, the compressor section, and the turbine section, the airfoil having a first segment including a first piece of a mount and a first piece of an airfoil, the first segment formed of a first ceramic-based material, and a second segment including a second piece of the mount and a second piece of the airfoil, the second segment formed of a second ceramic-based material, the first and second segments being bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.

15. The gas turbine engine as recited in claim 14, wherein the bond joint includes a refractory interlayer between the first segment and the second segment.

16. The gas turbine engine as recited in claim 14, wherein the first and second segments define at least one cavity there between.

The gas turbine engine as recited in claim 14, wherein at least one of the first ceramic-based material and the second ceramic-based material is a fiber-reinforced ceramic matrix composite.

17. A gas turbine engine component comprising:

a component body configured for use in a gas turbine engine, the component body including a first segment formed of a first ceramic-based material and a second segment formed of a second ceramic-based material, the first and second segments being bonded together along a bond joint.

18. The gas turbine engine component as recited in claim 17, wherein the bond joint includes a refractory interlayer between the first segment and the second segment.

19. The gas turbine engine component as recited in claim 17, wherein the first and second segments define at least one cavity there between.

20. The gas turbine engine component as recited in claim 17, wherein at least one of the first ceramic-based material and the second ceramic-based material is a fiber-reinforced ceramic matrix composite.