Method for manufacturing a composite bladed disk or rotor

Patent metadata

Field	Value
Publication number	US-12359571-B2
Application number	US-202418588423-A
Country	US
Kind code	B2
Filing date	Feb 27, 2024
Priority date	Mar 10, 2023
Publication date	Jul 15, 2025
Grant date	Jul 15, 2025

Abstract

A method includes forming a moulded component that is axisymmetric about a component axis; segmenting the moulded component into a plurality of segments, each pair of adjacent segments including a pair of surfaces that is formed during segmentation of the moulded component; providing, via computerised numerical control machining, complementary finger joint profiles on the pair of surfaces of the each pair of adjacent segments; providing a plurality of slots on at least one of the pair of surfaces of the each pair of adjacent segments; positioning a plurality of blades partially within the plurality of slots; mating the complementary finger joint profiles provided on the pair of surfaces of the each pair of adjacent segments; and joining the each pair of adjacent segments to each other, such that the plurality of blades is retained within the plurality of slots.

First claim

I claim:

1. A method for manufacturing a composite bladed disk or rotor for a gas turbine engine, the method comprising the steps of:
forming a moulded component from at least one composite material, wherein the moulded component is axisymmetric about a component axis;
segmenting the moulded component into a plurality of segments disposed adjacent to each other, wherein each pair of adjacent segments from the plurality of segments comprises a pair of surfaces that is formed during segmentation of the moulded component;
providing, via computerised numerical control machining, complementary finger joint profiles on the pair of surfaces of the each pair of adjacent segments;
providing a plurality of slots on at least one of the pair of surfaces of the each pair of adjacent segments, wherein each of the plurality of slots at least partially extends along the component axis and perpendicularly to the component axis;
positioning a plurality of blades partially within the plurality of slots;
mating the complementary finger joint profiles provided on the pair of surfaces of the each pair of adjacent segments; and
joining the each pair of adjacent segments to each other, such that the plurality of blades is retained within the plurality of slots.

2. The method of claim 1 , wherein forming the moulded component comprises depositing the at least one composite material on a mandrel.

3. The method of claim 2 , further comprising removing the mandrel from the moulded component prior to segmenting the moulded component.

4. The method of claim 1 , wherein the moulded component forms a plurality of stages of the composite bladed disk or rotor, and wherein the plurality of blades of the each pair of adjacent segments comprises a corresponding stage from the plurality of stages.

5. The method of claim 1 , wherein the at least one composite material comprises a plurality of composite materials that differ from each other, and wherein each of the plurality of segments comprises a corresponding composite material from the plurality of composite materials.

6. The method of claim 1 , wherein each of the complementary finger joint profiles comprises a plurality of circumferential fingers concentrically spaced apart from each other with respect to the component axis.

7. The method claim 1 , wherein each of the complementary finger joint profiles comprises a plurality of fingers extending perpendicularly to the component axis.

8. The method of claim 1 , wherein each adjacent segment of the each pair of adjacent segments has a section thickness defined perpendicularly to the component axis, wherein each of the complementary finger joint profiles comprises a plurality of fingers, wherein each of the plurality of fingers has a length defined along the component axis, and wherein the length is from 0.5 times to 2 times of the section thickness.

9. The method of claim 1 , wherein each of the plurality of slots is a dovetail slot.

10. The method of claim 1 , further comprising applying a joint adhesive layer on at least one of the complementary finger joint profiles prior to mating the complementary finger joint profiles of the each pair of adjacent segments.

11. The method of claim 10 , wherein joining the each pair of adjacent segments comprises curing the joint adhesive layer.

12. The method of claim 1 , further comprising applying a slot adhesive layer in each of the plurality of slots prior to positioning the plurality of blades partially within the plurality of slots, such that each of the plurality of blades is bonded to at least one of the each pair of adjacent segments.

13. The method of claim 1 , further comprising:
providing an alignment feature on the each pair of adjacent segments; and
aligning the each pair of adjacent segments with each other based on the alignment feature prior to mating the complementary finger joint profiles of the each pair of adjacent segments.

14. The method of claim 1 , further comprising coupling the moulded component to a drive shaft of the gas turbine engine.

15. The composite bladed disk or rotor manufactured by the method of claim 1 .

16. The gas turbine engine that includes a composite bladed disk or rotor of claim 15 .

Assignees

• Rolls Royce Plc

Inventors

• Backhouse Robert C

Classifications

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title

• F05D2230/23

  by permanently joining parts together · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F05D2230/50

  Building or constructing in particular ways · CPC title