# US 2023/0056767 A1 · Cmc gas turbine engine component with separated fiber plies

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- Number: US 2023/0056767 A1
- Document ID: US20230056767A1
- Status: Published application
- Kind: A1
- Application number: 17/883,937
- Filed: 2022-08-09
- Published: 2023-02-23
- Earliest claimed: 2021-08-19
- Assignees: Raytheon Technologies Corporation
- Applicants: Raytheon Technologies Corporation
- Inventors: Russell Kim
- Web page: https://patentgrep.com/patent/US20230056767A1

## CPC

- F01D 25/005: {Selecting particular materials}
- 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)}
- F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments}
- F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)}
- F05D 2220/32: in gas turbines
- F05D 2240/121: related to the leading edge of a stator vane
- F05D 2240/303: related to the leading edge of a rotor blade
- F05D 2300/6033: Ceramic matrix composites [CMC]
- F05D 2300/6034: Orientation of fibres, weaving, ply angle
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A gas turbine engine component includes a component wall that has an exterior core gaspath side and an opposed interior side. The component wall is formed of a ceramic matrix composite that includes a plurality of fiber plies disposed in a ceramic matrix. The component wall includes a corner that connects first and second wall sections. The fiber plies extend continuously through the first wall section, the corner, and the second wall section. The fiber plies are in a stacked contiguous arrangement in the first and second wall sections and at least some of the fiber plies separate from one another in the corner to define one or more void pockets there between.

## Claims

### Claim 1

A gas turbine engine component comprising:
a component wall that has an exterior core gaspath side and an opposed interior side, the component wall being formed of a ceramic matrix composite that includes a plurality of fiber plies disposed in a ceramic matrix, the component wall including a corner connecting first and second wall sections, the fiber plies extending continuously through the first wall section, the corner, and the second wall section, the fiber plies being in a stacked contiguous arrangement in the first and second wall sections and at least some of the fiber plies separating from one another in the corner to define one or more void pockets there between.

### Claim 2 (depends on 1)

The gas turbine engine component as recited in claim 1, wherein the corner is acute.

### Claim 3 (depends on 1)

The gas turbine engine component as recited in claim 1, wherein there are at least two of the void pockets.

### Claim 4 (depends on 3)

The gas turbine engine component as recited in claim 3, wherein, relative to the exterior core gas path side, a first one of the void pockets is inboard of a second one of the void pockets.

### Claim 5 (depends on 1)

The gas turbine engine component as recited in claim 1, wherein the fiber plies are arranged in groups, each of the groups having at least two of the fiber plies that are contiguous, and at least some of the groups separating from one another in the corner to define the one or more void pockets there between.

### Claim 6 (depends on 5)

The gas turbine engine component as recited in claim 5, wherein each of the groups has at least two of the fiber plies.

### Claim 7 (depends on 5)

The gas turbine engine component as recited in claim 5, wherein there are at least two of the void pockets, and the void pockets are of unequal thickness.

### Claim 8 (depends on 1)

The gas turbine engine component as recited in claim 1, wherein the corner is a leading edge of an airfoil.

### Claim 9 (depends on 8)

The gas turbine engine component as recited in claim 8, wherein the fiber plies are arranged in groups, each of the groups having at least two of the fiber plies that are contiguous, and at least some of the groups separating from one another in the corner to define the one or more void pockets there between.

### Claim 10

A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, the turbine section or the combustor having at least one component including:
a component wall that has an exterior core gaspath side and an opposed interior side, the component wall being formed of a ceramic matrix composite that includes a plurality of fiber plies disposed in a ceramic matrix, the component wall including a corner connecting first and second wall sections, the fiber plies extending continuously through the first wall section, the corner, and the second wall section, the fiber plies being in a stacked contiguous arrangement in the first and second wall sections and at least some of the fiber plies separating from one another in the corner to define one or more void pockets there between.

### Claim 11 (depends on 10)

The gas turbine engine as recited in claim 10, wherein the corner is acute.

### Claim 12 (depends on 10)

The gas turbine engine as recited in claim 10, wherein there are at least two of the void pockets.

### Claim 13 (depends on 12)

The gas turbine engine as recited in claim 12, wherein, relative to the exterior core gas path side, a first one of the void pockets is inboard of a second one of the void pockets.

### Claim 14 (depends on 10)

The gas turbine engine as recited in claim 10, wherein the fiber plies are arranged in groups, each of the groups having at least two of the fiber plies that are contiguous, and at least some of the groups separating from one another in the corner to define the one or more void pockets there between.

### Claim 15 (depends on 14)

The gas turbine engine as recited in claim 14, wherein each of the groups has two of the fiber plies.

### Claim 16 (depends on 14)

The gas turbine engine as recited in claim 14, wherein there are at least two of the void pockets, and the void pockets are of unequal thickness.

### Claim 17 (depends on 10)

The gas turbine engine as recited in claim 10, wherein the corner is a leading edge of an airfoil.

### Claim 18 (depends on 17)

The gas turbine engine as recited in claim 17, wherein the fiber plies are arranged in groups, each of the groups having at least two of the fiber plies that are contiguous, and at least some of the groups separating from one another in the corner to define the one or more void pockets there between.