# US 2014/0154073 A1 · Apparatus having engineered surface feature and method to reduce wear and friction between cmc-to-metal attachment and interface

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- Number: US 2014/0154073 A1
- Document ID: US20140154073A1
- Status: Published application
- Kind: A1
- Application number: 13/693,350
- Filed: 2012-12-04
- Published: 2014-06-05
- Earliest claimed: 2012-12-04
- Assignees: General Electric Company
- Applicants: General Electric Company
- Inventors: Ronald Ralph CAIRO; Jason Robert PAROLINI; John McConnell DELVAUX
- Web page: https://patentgrep.com/patent/US20140154073A1

## CPC

- F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments}
- F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28})
- F01D 5/3007: {of axial insertion type}
- F01D 5/3084: {the blades being made of ceramics}
- F01D 5/3092: {Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers (F01D5/288 takes precedence)}
- 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 5/284: {Selection of ceramic materials}
- F05D 2220/32: in gas turbines
- F05D 2240/24: for turbines
- F05D 2250/711: convex
- F05D 2250/712: concave
- F05D 2300/6033: Ceramic matrix composites [CMC]
- 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

An apparatus having reduced wear and friction between CMC-to-metal attachment and interface of the apparatus, including a CMC component having a surface. The CMC component surface is configured for sliding contact with a surface of a metal component, the sliding contact resulting in formation of debris along the contacting surfaces. The surface of the CMC component has an engineered surface feature formed therein to substantially prevent an accumulation of debris along the contacting surfaces.

## Claims

### Claim 1

A rotor blade for a gas turbine engine comprising:
an airfoil extending between a root having a surface and a tip opposite the root;
a rotor disk including a slot configured to receive the root, the rotor disk having a surface configured to form a sliding contact with the root surface, the sliding contact resulting in formation of debris along the sliding contact surfaces;
the root including engineered surface features formed therein to substantially prevent an accumulation of debris along the surfaces of sliding contact.

### Claim 2

A method to reduce wear and friction between ceramic matrix composite (CMC)-to-metal attachment and interface of an apparatus, comprising:
providing a CMC component having a surface;
providing a metal component having a surface;
arranging the surface of the CMC component in sliding contact with the surface of the metal component, the sliding contact resulting in formation of debris along the sliding contact surfaces;
substantially preventing an accumulation of debris along the sliding contact surfaces of the CMC component relative to the contacting surface of the metal component during operation of the apparatus.

### Claim 3 (depends on 2)

The method of claim 2, wherein substantially preventing an accumulation of debris along the sliding contact surfaces includes forming an engineered surface feature in the surface of the CMC component arranged in sliding contact with a surface of a metal component.

### Claim 4 (depends on 3)

The method of claim 3, wherein forming an engineered surface feature includes removing a portion of an outer layer of matrix material of the CMC component by machining.

### Claim 5 (depends on 3)

The method of claim 3, wherein forming an engineered surface feature includes use of contoured tooling associated with the manufacture of the CMC component.

### Claim 6

An apparatus having reduced wear and friction between CMC-to-metal attachment and interface of the apparatus, comprising:
a CMC component having a surface;
the CMC component surface being configured for sliding contact with a surface of a metal component, the sliding contact resulting in formation of debris along the contacting surfaces;
the surface of the CMC component having an engineered surface feature formed therein to substantially prevent an accumulation of debris along the contacting surfaces.

### Claim 7 (depends on 6)

The apparatus of claim 6, wherein the engineered surface feature is a protrusion.

### Claim 8 (depends on 7)

The apparatus of claim 7, wherein the protrusion is composed of fiber tows.

### Claim 9 (depends on 8)

The apparatus of claim 8, wherein a height of the protrusion is between about 0.05 mm to about 0.10 mm.

### Claim 10 (depends on 8)

The apparatus of claim 8, wherein a height of the protrusion is about 0.08 mm.

### Claim 11 (depends on 8)

The apparatus of claim 8, wherein a width of the protrusion is between about 0.05 mm to about 0.10 mm.

### Claim 12 (depends on 8)

The apparatus of claim 8, wherein a width of the protrusion is about 0.08 mm.

### Claim 13 (depends on 6)

The apparatus of claim 6, wherein the engineered surface feature is generally spaced about one fourth of a contact length from an end of the surface.

### Claim 14 (depends on 6)

The apparatus of claim 6, wherein the engineered surface feature is a recess.

### Claim 15 (depends on 14)

The apparatus of claim 14, wherein a depth of the recess is between about 0.05 mm to about 0.13 mm.

### Claim 16 (depends on 14)

The apparatus of claim 14, wherein a depth of the recess is about 0.08 mm.

### Claim 17 (depends on 14)

The apparatus of claim 14, wherein a width of the recess is between about 0.05 mm to about 0.10 mm.

### Claim 18 (depends on 14)

The apparatus of claim 14, wherein a width of the recess is about 0.08 mm.

### Claim 19 (depends on 14)

The apparatus of claim 14, wherein a profile of the recess is curved.

### Claim 20 (depends on 14)

The apparatus of claim 14, wherein a profile of the recess is substantially U-shaped.