Turbine blisk including ceramic matrix composite blades and methods of manufacture

Patent metadata

Field	Value
Publication number	US-10280768-B2
Application number	US-201514937260-A
Country	US
Kind code	B2
Filing date	Nov 10, 2015
Priority date	Nov 12, 2014
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

In some embodiments, an apparatus includes a disk, a coupling member and a set of blades. The coupling member has a first surface and a second surface, and defines a set of openings between the first surface and the second surface. The first surface is configured to be coupled to the outer surface of the disk. A portion of each blade from the set of blades is disposed within an opening from the set of openings when the first surface of the coupling member is coupled to the outer surface of the disk such that the blade is coupled to the disk.

First claim

What is claimed is:

1. A turbine disk assembly adapted for use in a gas turbine engine, the assembly comprising
a disk comprising metallic materials and forming a radially-outermost surface, the radially-outermost surface being a continuous circumferential surface that extends around a central axis that defines an axial direction parallel thereto and a radial direction perpendicular thereto,
a blade comprising ceramic matrix composite materials, the blade including a root with a radially-innermost surface arranged radially outward of the radially-outermost surface formed by the disk and an airfoil extending radially outward from the root, and
a ring coupled to the disk and extending around the radially-outermost surface formed by the disk, the ring formed to include an opening that receives at least a portion of the root included in the blade to couple the blade to the ring while at least a portion of the airfoil included in the blade is arranged outside of the opening radially outward of the ring to interact with gasses radially outward of the ring, wherein the opening and the at least a portion of the root received by the opening are sized to allow for relative motion between the blade and at least one of the ring and the disk so that differing rates of thermal expansion between the blade and the disk can be accounted for.

2. The assembly of claim 1 , wherein the ring is bonded to the disk via a braze joint arranged between the radially-inner surface of the ring and the radially-outermost surface formed by the disk; and the root of the blade is not bonded to the disk.

3. The assembly of claim 1 , wherein the opening formed in the ring extends radially through the ring from a radially-inner surface of the ring to a radially-outer surface of the ring.

4. The assembly of claim 3 , wherein the ring forms a one-piece full hoop extending around the central axis.

5. The assembly of claim 4 , wherein the opening is spaced apart from an axially-forward side and an axially-aft side of the ring.

6. The assembly of claim 4 , wherein the radially-outer surface of the ring provides a flow path defining surface.

7. A turbine disk assembly adapted for use in a gas turbine engine, the assembly comprising
a disk comprising metallic materials and forming an outer surface, the outer surface being a continuous circumferential surface that extends around a central axis that defines an axial direction parallel thereto and a radial direction perpendicular thereto,
a blade comprising ceramic matrix composite materials, the blade including a root arranged radially outward of the outer surface formed by the disk and an airfoil extending radially outward from the root, and
a ring coupled to the disk and extending around the outer surface formed by the disk, the ring formed to include an opening that receives at least a portion of the root included in the blade to couple the blade to the ring while at least a portion of the airfoil included in the blade is arranged outside of the opening radially outward of the ring to interact with gasses radially outward of the ring,
wherein a diameter of the outer surface formed by the disk is greater than a radially-inner surface of the ring when the disk and the ring are at the same temperature so that the disk and the ring are interference fit with one another and wherein an end surface of the root is spaced apart from at least one of the outer surface formed by the disk and the inner surface of the ring by a distance d and wherein the distance d is a distance greater than zero.

8. The assembly of claim 7 , wherein the ring is bonded to the disk via a braze joint arranged between the radially-inner surface of the ring and the outer surface formed by the disk.

9. The assembly of claim 8 , wherein the root of the blade is not bonded to the disk.

10. A turbine disk assembly adapted for use in a gas turbine engine, the assembly comprising
a disk comprising metallic materials and forming an outer surface, the outer surface being a continuous circumferential surface that extends around a central axis that defines an axial direction parallel thereto and a radial direction perpendicular thereto,
a blade comprising ceramic matrix composite materials, the blade including a root arranged radially outward of the outer surface formed by the disk and an airfoil extending radially outward from the root, and
a ring coupled to the disk and extending around the outer surface formed by the disk, the ring formed to include an opening that receives at least a portion of the root included in the blade to couple the blade to the ring while at least a portion of the airfoil included in the blade is arranged outside of the opening radially outward of the ring to interact with gasses radially outward of the ring,
wherein the opening formed in the ring extends radially through the ring from a radially-inner surface of the ring to a radially-outer surface of the ring,
wherein the root of the blade forms a dovetail shape or tapered outward shape and the opening formed in the ring forms a negative shape corresponding to at least a portion of the root, and
wherein the opening and the at least a portion of the root received by the opening are sized to allow for relative motion between the blade and the ring so that differing rates of thermal expansion between the blade and the disk can be accounted for.

11. A turbine disk assembly adapted for use in a gas turbine engine, the assembly comprising
a disk having an outer surface, the outer surface being a continuous circumferential surface;
a coupling member having a first surface and a second surface, and defining a plurality of openings between the first surface and the second surface, the first surface configured to be coupled to the outer surface of the disk; and
a plurality of blades, a portion of a blade from the plurality of blades being disposed within an opening from the plurality of openings when the first surface of the coupling member is coupled to the outer surface of the disk such that the blade is coupled to the disk,
wherein the portion of the blade is a root of the blade, the root having a radially-innermost end surface that is spaced radially apart from the radially-outermost surface of the disk when the first surface of the coupling member is coupled to the outer surface of the disk and wherein relative motion between the blade and one of the ring and the disk is allowed.

12. The assembly of claim 11 , wherein the second surface of the coupling member defines a flow path.

13. The assembly of claim 11 , wherein the blade from the plurality of blades is devoid of a platform.

14. The assembly of claim 11 , wherein the first surface of the coupling member is bonded to the outer surface of the disk.

15. The assembly of claim 11 , wherein the blade from the plurality of blades is constructed from a ceramic matrix composite material.

16. A method of constructing a turbine disk assembly adapted for use in a gas turbine engine, the method comprising
inserting a blade through an opening defined by a ring such that a root of the blade is matingly disposed within the opening,
heating the ring,
cooling a disk,
disposing the ring about the disk, and
equalizing the temperature of the disk and the ring such that an inner surface of the ring is interference fit with an outer surface of the disk and relative motion between the blade and one of the ring and the disk is allowed.

17. The method of claim 16 , further comprising
applying a braze material to at least one of the outer surface of the disk and the inner surface of the ring;

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce High Temperature Composites Inc

Inventors

• Freeman Ted J
• Engel Todd Z

Classifications

• F01D5/16

  for counteracting blade vibration · CPC title

• F01D5/303

  in a circumferential slot · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• B23K20/026

  with diffusion of soldering material · CPC title