# US 2019/0168295 A1 · Aerofoil joint recess

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- Number: US 2019/0168295 A1
- Document ID: US20190168295A1
- Status: Published application
- Kind: A1
- Application number: 16/196,330
- Filed: 2018-11-20
- Published: 2019-06-06
- Earliest claimed: 2017-12-06
- Assignees: ROLLS-ROYCE plc
- Applicants: ROLLS-ROYCE plc
- Inventors: Adrian L HARDING
- Web page: https://patentgrep.com/patent/US20190168295A1

## CPC

- B22D 19/04: for joining parts
- B22D 25/02: by its peculiarity of shape; of works of art {(cylinders, pistons B22D15/02)}
- F01D 5/187: {Convection cooling}
- F01D 5/288: {Protective coatings for blades}
- F01D 9/044: {permanently, e.g. by welding, brazing, casting or the like}
- F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)}
- F01D 5/186: {Film cooling (F01D5/187 takes precedence)}
- F01D 5/30: Fixing blades to rotors; Blade roots {; Blade spacers}
- F05D 2230/10: by removing material
- F05D 2230/21: by casting
- F05D 2230/23: by permanently joining parts together
- F05D 2230/60: Assembly methods
- F05D 2240/80: Platforms for stationary or moving blades
- B22D: CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES (shaping of plastics or substances in a plastic state B29C; metallurgical processing, selection of substances to be added to metal C21, C22)
- 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

An aerofoil configured to be connected to a second component, the aerofoil comprising a first face including a bi-cast groove for joining the aerofoil to the second component by bi-casting; a second face connected to a main body of the aerofoil; an angled sealing face between the first and second face, the angled sealing face being angled with respect to the second face and configured to provide a sealing interface between the first face and the second face; and a concave face forming a recessed surface at the intersection of the sealing face and the second face.

## Claims

### Claim 1

An aerofoil configured to be connected to a second component, the aerofoil comprising:
a first face including a bi-cast groove for joining the aerofoil to the second component by bi-casting;
a second face connected to a gas path surface of the aerofoil;
an angled sealing face between the first and second face, the angled sealing face being angled with respect to the second face and configured to provide a sealing interface between the first face and the second face; and
a concave face forming a recessed surface at the intersection of the sealing face and the second face.

### Claim 2 (depends on 1)

The aerofoil according to claim 1, further comprising a through-hole, wherein one end of the through-hole opens at the concave face.

### Claim 3 (depends on 1)

The aerofoil according to claim 1, wherein the second face is coated with a thermal barrier coating.

### Claim 4 (depends on 1)

The aerofoil according to claim 1, wherein the angle between the angled sealing face and the second face is an obtuse angle.

### Claim 5 (depends on 1)

The aerofoil according to claim 1, wherein the angle between the angled sealing face and the second face is a right angle.

### Claim 6 (depends on 1)

The aerofoil according to claim 1, wherein the first face is at the root of the aerofoil.

### Claim 7 (depends on 1)

The aerofoil according to claim 1, wherein the first face is at the tip of the aerofoil.

### Claim 8 (depends on 1)

The aerofoil according to claim 1, wherein the aerofoil is a stator vane.

### Claim 9 (depends on 1)

The aerofoil according to claim 1, wherein the aerofoil is a rotor blade.

### Claim 10 (depends on 1)

The aerofoil according to claim 1, wherein the cross-section of the recessed surface is a continuous curve between the angled sealing face and the second face.

### Claim 11 (depends on 1)

The aerofoil according to claim 1, wherein the cross-section of the recessed surface includes a discontinuity.

### Claim 12 (depends on 1)

An assembly comprising the aerofoil according to claim 1, and a second component, wherein the aerofoil and second component are joined by bi-cast metal filling the bi-cast groove of the aerofoil and a corresponding bi-cast groove on the second component.

### Claim 13

A method of manufacturing an aerofoil comprising:
providing an aerofoil with a first face including a bi-cast groove; a second face connected to a main body of the aerofoil; and an angled sealing face between the first and second face, the angled sealing face being angled with respect to the second face and configured to seal the bi-cast groove; and
removing material at the intersection of the angled sealing face and the second face to form a concave face, thus forming a recessed surface.

### Claim 14 (depends on 13)

A method of manufacturing an assembly comprising
manufacturing an aerofoil according to the method of claim 13; and
joining the aerofoil to a second component by filling the bi-cast groove of the aerofoil and a corresponding bi-cast groove on the second component with bi-cast metal.