Component manufacture

Abstract

A computer-controlled method of component manufacture is disclosed, which includes winding a thread of material around a shaping element to form a first layer formed of adjacent turns of the thread. The winding is repeated to form a second layer of adjacent turns of the thread on top of the first layer. A laser beam is then applied between adjacent turns of each layer to attach them at predetermined points.

Claims

1. A method of component manufacture, comprising acts of: winding a thread of material around a shaping mandrel to form a first layer formed of adjacent turns of said thread; under computer-control, applying a laser beam between adjacent turns of the first layer to attach them at predetermined attachment points; repeating the winding act to form a second layer of adjacent turns of said thread on top of the first layer, wherein the second layer of adjacent turns of the thread of material is oriented differently from that of the first layer; and repeating the laser beam application act to the second layer, wherein the predetermined attachment points between adjacent turns in a given layer and/or between first and second layers are distributed around the shaping mandrel in a non-linear manner, applying the laser beam at selected predetermined points between the first and second layers to attach adjacent turns of one layer to another, and wherein the predetermined attachment points predetermined attachment points between adjacent turns in a given layer and predetermined attachment points between first and second layers at least one of fuse or bond only two turns.

2. The method according to claim 1, wherein the second layer turns are oriented at 90 degrees to the first layer turns.

3. The method according to claim 1, wherein the thread of material is a matrix coated fibre material.

4. The method according to claim 3, wherein the thread of material is Silicon Carbide surrounded by a metal material.

5. The method according to claim 1, further comprising depositing a powdered material between the first and second layers and applying a laser beam to cause melting of the powdered material.

6. The method according to claim 5, wherein the powdered material is metal based.

7. The method according to claim 1, wherein the winding acts each comprise winding a single thread of material around the shaping mandrel.

8. The method according to claim 1, wherein the shaping mandrel is a tubular mandrel.

9. The method according to claim 1, wherein the cross-section of the thread of material includes a non-circular cross-section.

10. The method according to claim 1, wherein at least one winding is between adjacent attachment points in the first layer.

11. The method according to claim 10, wherein at least one winding is between adjacent attachment points in the second layer.

12. A non-transitory computer-readable storage medium having stored thereon computer-readable code, which, when executed by a computing apparatus, causes the computing apparatus to perform a method comprising acts of: winding a thread of material around a shaping mandrel to form a first layer formed of adjacent turns of said thread; applying a laser beam, under computer-control, between adjacent turns of the first layer to attach them at predetermined points; repeating the winding act to form a second layer of adjacent turns of said thread on top of the first layer, wherein the second layer of adjacent turns of the thread of material is oriented differently from that of the first layer; and repeating the laser beam application act to the second layer, wherein the predetermined points between adjacent turns in a given layer and/or between the first and second layers are distributed around the shaping mandrel in a non-linear manner, applying the laser beam at selected predetermined points between the first and second layers to attach adjacent turns of one layer to another, and wherein the predetermined attachment points predetermined points between adjacent turns in a given layer and predetermined points between first and second layers at least one of fuse or bond only two turns.

13. An apparatus comprising: at least one processor and at least one non-transitory memory having computer-readable code stored thereon which when executed control the at least one processor to perform acts of: winding a thread of material around a shaping mandrel to form a first layer formed of adjacent turns of said thread; applying a laser beam, under computer-control, between adjacent turns of each layer to attach them at predetermined attachment points; winding the thread of material around the shaping mandrel to form a second layer of adjacent turns of said thread on top of the first layer, wherein the second layer of adjacent turns of the thread of material is oriented differently from that of the first layer; and applying a laser beam under computer-control between adjacent turns of the second layer to attach them at predetermined attachment points, wherein the predetermined attachment points between adjacent turns in a given layer and/or between first and second layers are distributed around the shaping mandrel in a non-linear manner, applying the laser beam at selected predetermined points between the first and second layers to attach adjacent turns of one layer to another, and wherein the predetermined attachment points predetermined attachment points between adjacent turns in a given layer and predetermined attachment points between first and second layers at least one of fuse or bond only two turns.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The invention will now be described by way of non-limiting example with reference to the accompanying drawings, in which:

(2) FIG. 1 is a schematic block diagram of a computer-controlled manufacturing system according to the invention;

(3) FIG. 2 is a plan-view diagram of a manufacturing system indicated by FIG. 1 following depositing of a first layer of thread material;

(4) FIG. 3 is a partial, sectional-view of the FIG. 2 system;

(5) FIG. 4 is a partial close-up view of the FIG. 2 system;

(6) FIG. 5 is a partial, sectional-view of the FIG. 2 system following depositing of a second layer of material;

(7) FIG. 6 is a partial, sectional-view of the FIG. 2 system following depositing of a second layer of material according to a second embodiment; and

(8) FIG. 7 is a partial, sectional view of the FIG. 2 system in which a powdered material is deposited between the first and second layers.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENT(S)

(9) Embodiments described herein provide a computer-controlled system 1 for part of a component manufacturing process that involves the winding of a thread-like material, in this case matrix coated fibre (MCF), onto a shaping mandrel. In the simple example given, a tubular mandrel is used, but it will be appreciated and understood that any hollow shape can be formed and the term thin-wall construction is understood in this context. The MCF is in this case silicon carbide surrounded by a metal material outer, being any one of aluminium, titanium or steel. Again, other forms of fibre can be used.

(10) The system 1 is arranged to accurately wind the MCF onto the mandrel in a first layer and, subsequently, in a second layer over the first layer. Further layers may be deposited in this way. As winding proceeds, the system 1 accurately fuses or bonds certain predetermined adjacent turns of the thread to ensure the closely packed turns remain static within each layer. Adjacent turns of different layers can also be fused or bonded in this way. The pattern of these ‘tacks’ (so-called because they are point-like) is predetermined and programmed within the computer to ensure rigidity and strength of the component when complete. In the case of MCF, the bonding occurs on the matrix material around the outside of the MCF with the inner silicon carbine ‘floating’.

(11) Referring to FIG. 1, the system 1, comprises a computer control system (CCS) 3 which is akin to a computer numerical control (CNC) system in that it comprise one or more processors or microcontrollers which operate under program control to operate various hardware components of the system. The CCS 3 includes memory on which is stored the or each computer program for this purpose, although firmware may be used in addition or as an alternative. RAM is used in conjunction with the processor(s) or microcontroller(s) in the conventional way. A user control 5 module comprises input and output means through which the user can upload instructions for the CCS 3 and monitor progress, output and any system messages.

(12) The CCS 3 controls the operation of a fibre reel 9, a rotating mandrel 7 and a laser system 11. The control of these components 9, 7, 11 is done under program control to automatically and precisely perform a manufacturing method to be explained below. It is to be understood that the manufacturing method is partial in the sense that subsequent treatments steps, e.g. HIPing may be employed to finish the component prior to use. In other embodiments, the CCS 3 does not directly control the fibre reel 9 which is simply guided and tensioned but left effectively to freely dispense the fibre as the mandrel 7 rotates. In other embodiments, the fibre reel 9 and mandrel 7 are not computer controlled, and the CCS 3 only controls the laser system 11.

(13) FIG. 2 shows a cylindrical mandrel 7 from above. Alongside it is the laser system 11 which includes the laser (or more than one laser) module mounted on a movable head 13 which is moved along a horizontal track 15 according to computer control. The head 13 may move in more than one direction, but given that the mandrel 7 rotates under CCS 3 control, it is assumed in this instance one dimensional movement is sufficient. The CCS 3 determines when the laser module(s) are on/off based on position of the head 13 along the track and the relative rotational position of the mandrel 7. For more complex mandrel shapes (e.g. for domes, blades etc.) multiple axis of movement of the head 13 will be required.

(14) A number of turns of MCF thread 17 are shown already wound on the mandrel 7.

(15) Referring to FIGS. 2 to 5, the general method performed by the CCS 3 under program control is as follows: 1) The thread 17 is wound around the mandrel 7 to form a coil of closely-adjacent turns in a first, in this case horizontal, layer; 2) During or after the first layer is complete, the laser system 11 is operated to fuse or bond certain adjacent turns to one another in a point-like manner (see reference numerals 21, 23, 25, 27); 3) The thread 17, whether the same or a different thread, is wound around the mandrel 7 over the first layer to form a second layer of closely-adjacent turns; and 4) Stage 2 above is repeated for the second layer.

(16) As indicated in FIG. 4, which is a partial plan view, only certain adjacent turns of a given layer need be fused in this way, i.e. not all adjacent turns need be fused in this way. Also, a predetermined pattern of fuse points is employed to avoid weaknesses e.g. due to a linear side-by-side pattern of points. Here, the points are distributed in both horizontal and vertical directions.

(17) As indicated in FIG. 5, the second layer 29 preferably nests within the upper gaps of the first layer 17 to minimise the gaps in between. It is worth pointing out at this stage that the thread need not have a circular cross-section and cross-sections resulting in smaller gaps can be employed.

(18) As also indicated in FIG. 5, certain predetermined ones of the first and second layers 17, 29 can be fused together using the same method. The laser beam is focused between the junction of the first and second layers 17, 29 for this purpose.

(19) In the first example shown and described with reference to FIGS. 2 to 5, it will be noted that the orientations of the thread 17 for the first and second layers 17, 29 is the same. However, the two layers 17, 19 can be oriented differently, as indicated in FIG. 6, which is a further embodiment where the second layer 35 in this case is oriented 90 degrees relative to the underlying layer. Other orientations, for example, 15, 30, 45 degree relative orientations may be used as an alternative.

(20) In a still further embodiment, represented by FIG. 7, a powdered material 7 is deposited between the first and second layers 17, 29 i.e. after the first layer is wound onto the mandrel 7. After the second layer 29 has been wound over the first layer 17 the laser 13 is controlled to heat the powdered material 37 to cause it to flow within the gaps and substantially fill said gaps to avoid subsequent points or areas of weakness. For this purpose the laser 13 is focused on this intermediate region between the layers.

(21) As mentioned previously, one or more further layers may be wound using the above principle. When all layers are deposited, the mandrel 7 is removed using conventional techniques, e.g. using a sacrificial mandrel which is destroyed leaving the outer component. The component which is likely to be only partially finished may be moved to a subsequent stage, e.g. HIPing prior to removal of the mandrel 7.

(22) It will be appreciated that the above described embodiments are purely illustrative and are not limiting on the scope of the invention. Other variations and modifications will be apparent to persons skilled in the art upon reading the present application.

(23) Moreover, the disclosure of the present application should be understood to include any novel features or any novel combination of features either explicitly or implicitly disclosed herein or any generalization thereof and during the prosecution of the present application or of any application derived therefrom, new claims may be formulated to cover any such features and/or combination of such features.