# US 9,039,379 B2 · Retention device for a composite blade of a gas turbine engine

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- Number: US 9,039,379 B2
- Document ID: US9039379B2
- Status: Granted
- Kind: B2
- Application number: 13/427,068
- Filed: 2012-03-22
- Published: 2012-10-11
- Granted: 2015-05-26
- Earliest claimed: 2011-04-11
- Assignees: ROLLS-ROYCE plc
- Applicants: Steven A. Radomski
- Inventors: Steven A. Radomski
- Web page: https://patentgrep.com/patent/US9039379B2

## CPC

- F01D 5/3092: {Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers (F01D5/288 takes precedence)}
- F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments}
- F01D 5/3007: {of axial insertion type}
- F01D 5/323: {Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor}
- F05D 2230/54: by sheet metal manufacturing
- F05D 2300/603: Composites; e.g. fibre-reinforced
- 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

## Abstract

A liner for a composite blade of a gas turbine engine includes a metallic shoe, operable substantially to encase a blade root of a composite blade and defining an inner surface and an outer surface. The liner also includes a retention lug formed on the shoe and has inner and outer keys that project from opposed portions of the inner and outer surfaces. The keys engage corresponding recesses on a dovetail slot and a blade root to resist axial displacement of the composite blade.

## Claims

### Claim 1

A liner for a composite blade of a gas turbine engine, the liner comprising a metallic shoe for at least partially encasing a blade root of a composite blade, the metallic shoe having an inner surface, an outer surface, and a retention lug,
wherein the retention lug comprises an outer key which projects from an outer surface of the retention lug and configured for axial retention of the blade,
wherein the metallic shoe comprises a base portion and opposed flank portions, and
wherein the retention lug is formed on a flank portion.

### Claim 2 (depends on 1)

The liner as claimed in claim 1, wherein the retention lug further comprises an inner key which projects from an inner surface of the retention lug.

### Claim 3 (depends on 2)

The liner as claimed in claim 2, wherein the inner and outer keys are located on opposing portions of the inner and outer surfaces.

### Claim 4 (depends on 2)

The liner as claimed in claim 2, wherein the inner key of the retention lug comprises a stepped projection having at least one change in thickness.

### Claim 5 (depends on 1)

The liner as claimed in claim 1, wherein the liner comprises two retention lugs, each lug formed on an opposed flank portion of the shoe.

### Claim 6 (depends on 1)

The liner as claimed in claim 1, wherein the retention lug is metallic.

### Claim 7 (depends on 1)

The liner as claimed in claim 1, wherein the retention lug is integrally formed with the shoe.

### Claim 8 (depends on 1)

The liner as claimed in claim 1, wherein the retention lug is diffusion bonded to the shoe.

### Claim 9 (depends on 1)

The liner as claimed in claim 1, wherein the outer key of the retention lug comprises a single projection having a constant thickness.

### Claim 10 (depends on 1)

A blade assembly for a gas turbine engine, comprising a composite blade and the liner as claimed in claim 1.

### Claim 11 (depends on 10)

The blade assembly as claimed in claim 10, wherein the liner is attached to the blade root of the composite blade by co-moulding.

### Claim 12 (depends on 10)

The blade assembly as claimed in claim 10, wherein the liner is attached to the blade root of the composite blade by secondary bonding.

### Claim 13 (depends on 10)

The blade assembly as claimed in claim 10, wherein the retention lug further comprises an inner key which projects from an inner surface of the retention lug, and wherein the inner key of the liner retention lug engages a corresponding recess formed on the blade root of the composite blade.