Ceramic matrix composite aerofoil with impact reinforcements

Patent metadata

Field	Value
Publication number	US-11060409-B2
Application number	US-201916410467-A
Country	US
Kind code	B2
Filing date	May 13, 2019
Priority date	May 13, 2019
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine includes an airfoil assembly. The airfoil assembly includes an airfoil and at least one reinforcement inset coupled to the airfoil assembly. The reinforcement inset is configured to resist damage to the airfoil assembly due to objects impacting the airfoil assembly.

First claim

What is claimed is:

1. An aerofoil assembly for use in a gas turbine engine, the aerofoil assembly comprising
an aerofoil comprising ceramic matrix composite materials and extending radially relative to an axis, the aerofoil having a leading edge, a trailing edge spaced apart axially from the leading edge, a pressure side interconnecting the leading edge and the trailing edge, and a suction side spaced apart circumferentially from the pressure side and interconnecting the leading edge and the trailing edge, the aerofoil shaped to define an inner surface that forms an internal cavity for receiving cooling air therein and an outermost surface configured to interact with hot gases conducted through the gas turbine engine, and
a first reinforcement inset at least partially located in the suction side of the aerofoil between the inner surface and the outermost surface to resist damage to the aerofoil assembly due to objects impacting the aerofoil assembly, the first reinforcement inset comprising at least one material different than the ceramic matrix composite materials,
wherein the ceramic matrix composite materials of the aerofoil surround the first reinforcement inset such that the entire first reinforcement inset is in direct contact with the ceramic matrix composite materials of the aerofoil to cause the first reinforcement inset to be insulated from the hot gases, and
the aerofoil assembly further comprising a second reinforcement inset located in the leading edge of the aerofoil between the inner surface and the outermost surface to resist damage to the aerofoil assembly due to objects impacting the aerofoil assembly, wherein the ceramic matrix composite materials of the aerofoil surround the second reinforcement inset such that the entire second reinforcement inset is in direct contact with the ceramic matrix composite materials of the aerofoil to cause the second reinforcement inset to be insulated from the hot gases.

2. The aerofoil assembly of claim 1 , wherein the first reinforcement inset is discrete from the second reinforcement inset.

3. The aerofoil assembly of claim 1 , wherein the aerofoil includes a first layer of ceramic matrix composite materials and a second layer of ceramic matrix composite materials arranged around the first layer of ceramic matrix composite materials, the first layer of ceramic matrix composite materials and the second layer of ceramic matrix composite materials are aerofoil shaped, and the first reinforcement insert is located between the first layer of ceramic matrix composite materials and the second layer of ceramic matrix composite materials.

4. The aerofoil assembly of claim 1 , wherein the first reinforcement inset is located in at least one of the suction side, pressure side, and trailing edge of the aerofoil.

5. The aerofoil assembly of claim 4 , wherein the first reinforcement inset includes a first side surface, a second side surface, and a receiver surface, the first side surface and the second side surface converge toward one another and meet adjacent the trailing edge of the aerofoil, and the receiver surface is concave and contacts directly the first side surface and the second side surface to interconnect the first side surface and the second side surface.

6. The aerofoil assembly of claim 1 , wherein the first reinforcement inset comprises at least one of silicon carbide fibre, silicon carbide nitride, a monofilament titanium ceramic matrix composite, a safricon fibre, and a non-oxide ceramic fibre.

7. An aerofoil assembly for use in a gas turbine engine, the aerofoil assembly comprising
an aerofoil comprising ceramic matrix composite materials and extending radially relative to an axis, the aerofoil having a leading edge, a trailing edge spaced apart axially from the leading edge, a pressure side interconnecting the leading edge and the trailing edge, and a suction side spaced apart circumferentially from the pressure side and interconnecting the leading edge and the trailing edge, the aerofoil shaped to define an inner surface that forms an internal cavity for receiving cooling air therein and an outermost surface configured to interact with hot gases conducted through the gas turbine engine, and
a first reinforcement inset at least partially located in the suction side of the aerofoil between the inner surface and the outermost surface to resist damage to the aerofoil assembly due to objects impacting the aerofoil assembly, the first reinforcement inset comprising at least one material different than the ceramic matrix composite materials,
wherein the ceramic matrix composite materials of the aerofoil surround the first reinforcement inset such that the entire first reinforcement inset is in direct contact with the ceramic matrix composite materials of the aerofoil to cause the first reinforcement inset to be insulated from the hot gases,
wherein the entire first reinforcement inset is located in the suction side of the aerofoil,
wherein the first reinforcement inset extends between a first end and a second end and includes a curvilinear outer inset surface and a curvilinear inner inset surface that contact each other to form a first point at the first end and a second point at the second end.

8. An aerofoil assembly comprising
an aerofoil comprising ceramic matrix composite materials, the aerofoil includes a first layer of ceramic matrix composite materials and a second layer of ceramic matrix composite materials arranged around the first layer, the first layer contacts the second layer at a first location and at a second location spaced apart from the first location, and the first layer is spaced apart from the second layer at a third location between the first location and second location to define a inset-receiving space between the first location and the second location, and
a first reinforcement inset located in the inset-receiving space between the first layer and the second layer and engaged with the first layer and the second layer,
wherein the aerofoil has a leading edge, a trailing edge spaced apart axially from the leading edge, a pressure side interconnecting the leading edge and the trailing edge, and a suction side spaced apart circumferentially from the pressure side and interconnecting the leading edge and the trailing edge, and the first reinforcement inset is located in the leading edge of the aerofoil.

9. The aerofoil assembly of claim 8 , wherein the first reinforcement inset contacts directly the first layer and the second layer.

10. The aerofoil assembly of claim 8 , wherein the first reinforcement inset is crescent shaped.

11. The aerofoil assembly of claim 8 , wherein the second layer provides an outermost surface of the aerofoil assembly, the first layer has a first thickness, the second layer has a second thickness, and the first thickness is greater than the second thickness.

12. The aerofoil assembly of claim 8 , further comprising a second reinforcement inset, wherein the second reinforcement inset extends at least partway along the suction side of the aerofoil toward the trailing edge.

Assignees

• Rolls Royce Plc

Inventors

• Jones Edward M
• Whittle Michael J
• Smith James C
• Steedman Emma C
• Edmonds Ian

Classifications

• C04B35/80

  Fibres, filaments, whiskers, platelets, or the like · CPC title

• F01D21/04 Primary

  responsive to undesired position of rotor relative to stator {or to breaking-off of a part of the rotor}, e.g. indicating such position · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• C04B2235/5256

  Two-dimensional, e.g. woven structures · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title