GB2244453A - Laying up table - Google Patents
Laying up table Download PDFInfo
- Publication number
- GB2244453A GB2244453A GB9007565A GB9007565A GB2244453A GB 2244453 A GB2244453 A GB 2244453A GB 9007565 A GB9007565 A GB 9007565A GB 9007565 A GB9007565 A GB 9007565A GB 2244453 A GB2244453 A GB 2244453A
- Authority
- GB
- United Kingdom
- Prior art keywords
- article
- layers
- gap
- carrier members
- layer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 239000002131 composite material Substances 0.000 claims abstract description 34
- 238000004519 manufacturing process Methods 0.000 claims abstract description 23
- 230000000694 effects Effects 0.000 claims abstract description 3
- 238000000034 method Methods 0.000 description 9
- 230000009467 reduction Effects 0.000 description 8
- 238000007596 consolidation process Methods 0.000 description 5
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 230000037303 wrinkles Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/02—Bending or folding
- B29C53/04—Bending or folding of plates or sheets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
- B32B3/04—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by at least one layer folded at the edge, e.g. over another layer ; characterised by at least one layer enveloping or enclosing a material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/02—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by a sequence of laminating steps, e.g. by adding new layers at consecutive laminating stations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
- B32B37/1018—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using only vacuum
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2009/00—Layered products
- B29L2009/001—Layered products the layers being loose
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
- B32B2037/1063—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using an electrostatic force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2603/00—Vanes, blades, propellers, rotors with blades
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
A laying up table for use in the manufacture of a composite multilayer article which is folded to form a lug section, comprising first and second carrier members (1, 2) which are moveable so as to provide a gap whose width (D) may be varied between edges thereof, and which incorporates means to hold an article placed thereon in position, and a drive arrangement 10 effect relative movement of the first and second carrier members (1, 2), wherein during the manufacture of multilayer composite articles, a layer (A) of the article is positioned on the first and second carrier members (1, 2), or previously positioned layers, and the first and second carrier members (1, 2) are moved by a predetermined distance (D) so reducing the width of the gap therebetween and slacken the portion of the layer or layers over the gap which will form the lug, so that when the layers are folded over on themselves no wrinkling occurs between the layers in the article being formed. <IMAGE>
Description
LAYING UP TABLE
This invention relates to laying up tables for use in the manufacture of multilayer composite articles which articles are folded to form a lug, and a method of manufacturing a multilayer composite article using the laying up table.
In the production of a multilayer composite article, for example, a multilayer composite fan or propeller blade or structure member for apparatus, which is folded to form a lug by which the article may be attached to another member or other equipment, the individual layers are folded over each other either on a horizontal bed or laid over a bar so that they hang vertical.
rnn the mânusâcture of a multilayer composite glade using a horizontal bed, the laying up and shaing operations on the individual layers are performed at the same tie. Further, in view of this it is very difficult and expensive to design and operate equipment for the automation of this type of manufacturing process. As â result of this the manufacture of multilayer composite articles using a horizontal bed tends to be a manual process, making it labour intensive and expensive.
Now in the manufacture of a multilayer composite blade using hanging technique the actual geometry of the process provides problems with the automation of equipment similar to those mentioned above with regard to the horizontal bed. Further there is a potential problem caused by the potential for slippage, or wrinkling caused by differential tensions, between the layers of the article which may cause wrinkles between the layers in the finished article.
Therefore, the use of these forms of laying up techniques means that the manufa#tur#ng techrL es cannot be easily controlled, arc autoration thereof is expensive.
Ultimately, the problems with these te^hnies with the production of propeller or fan blades can lead to the fan or propeller blade being wrinkled between the layers thereof. ObvIously this leads to a reduction of the potential strength of the composite blade in the area of the wrinkling.
The present invention is concerned with providing a laying up table and a method of manufacture using the laying up table which enables the multilayer composite article to be automatically manufactured with problems mentioned above being substantially eliminated.
In accordance with the present invention a laying up table for use in the manufacture of a composite multilayer article which is folded to form a lug section, comprises:
- first and second carrier members, which
are moveable so as to provide a gap
whose width may be varied between edges thereof, and which incorporates means to hold an article placed thereon
in position; and - a drive arrangement to effect relative
movement of the first and second
carrier members; wherein during the manufacture of multilayer composite articles, a layer of the article is positioned on the first and second carrier members, or previously positioned layers, and the first and second carrier members are moved by a predetermined distance so reducing the width of the gap therebetween and slacken the portion of the layer or layers over the gap which will form the lug, so that when the layers are folded over on themselves and no wrinkling occurs between the layers in the article being formed.
A laying ur table maae in accordance with the present invention has the advantage or enabling multilayer composite articles to be produced in which the winkles wrinkles between Detween layers have been substantially eliminated, whilst enabling the production technique to be easily automated.
Preferably, the means to hold an article in position on the first and second carrier members is suction or vacuum operated.
Alternatively, the means to hold an article in position on the first and second carrier members is electrostatically operated.
In a preferred embodiment of the present invention the drive arrangement comprises:
- two bogie members each having a shaft
with drive wheels mounted at the ends
thereof, one bogie member being mounted
under each carrier member transverse to
the direction of travel thereof;
- two drive belts, one connectIng the
respective drlve wheels at each end of
the shaft of the bogie merger;
- two mounting members, one for each Or the carrier members, fixedly mounted to
the drive belts; and - a stepper motor arranged so that it
causes movement of the two mounting
members wherein the two mounting members are fixedly mounted to the drive belts so that the movement induced by the stepper motor in the two mounting members is in opposing directions.
Preferably, the drive arrangement further comprises a position feedback sensor.
In one embodiment of the present invention a gearbox is provided in association with the stepper motor to accurately control the length of movement of the stepper motor.
In a preferred arrangement of the present Invention, the movement of the first and secon carrier mer.#ers by a predetermined do stance so reducing the gap between the first and second carrier member, is controlled and determined by a microprocessor in response to signals fror, the position feedback sensor.
It should be noted that the reduction in trite width of the gap and the consequential slackening in the layers between the first and second carrier members enables the composite multilayer article to be manufactured so that when the layers are folded over upon themselves no wrinkling is caused in the vicinity of the lug formed and the lug is correctly shaped.
Now if the reduction in the width of the gap is not sufficient wrinkling will be caused. Further, if the reduction in the width of the gap is too great stretching and layer movement causing wrinkling may result. However in either case the lug will not meet the required specification and therefore neither will the finished article. In view of this it is clearly apparent how important accurate control of the reduction in the width of the ga is to tne product being ran#factureo.
Now when the layers are simply folded over upon themselves they will in the area of the lug subtend a shape, having a semicircular section in the area at the base of the lug. Therefore, the reduction in the gap between the first a second carrier members is dependent/related to the periphery of the circle defined by the semicircular section subtended by the respective layer in the finished article. The width of the gap is therefore a function of # d t where d is the diameter of the
circle defined by the semicircular
base section subtended by the
respective layer and t is the
thickness of the layer of the
composite article.
The area at the base of the lug may be deliberately shaped to fit certaIn operational characteristics. The reduction in the width of the gap ifl these cases will still be a function of fr, d and t however a far more complex function than wlth the previously discussed situation.
In one arrangement of the present invention sensors may be provided in association with the present invention, so that accurate tensional data may be obtained which enables accurate monitoring of the manufacture of the multilayer composite article.
In accordance with a second aspect of the present invention there is provided a method of manufacturing a composite multilayer article which is folded to form a lug section using a laying up table as hereinbefore described, which comprises:
- presetting the width of the gap between
the first and second carrier members;
- laying a first layer of composite
material on the first and second
carrier mergers;
- reducing the width of the gap between
the first and second carrier members by
a predetermined distance;
- repeatedly until the composite article
preform has been formed
- laying a subsequent layer of
composite material on the
previously laid layer;
- heat bonding the newly laid
layer of composite material
to the previously laid
material;
- reducing the width of the gap
between the first and second
carrier members by a
predetermined distance; and - folding the preform over upon itself to
form c lug.
Preferably the method o manufacturing a composite multilayer article arns no includes subject Inc the folded preform to consolidation and resin injection in order to form an article of the correct shape ano profile, and which is sufficiently rigid and strong to fulfil the desired function.
Preferably, the consolidation of the folded preform is effected by a 3-D heat and vacuum consolidation process.
The invention will now be illustrated by way of description of an example with reference to the accompanying drawings, in which:
Figure 1 shows a schematic representation of
a laying up table made in
accordance with the present
invention;
Figure 2 shows a schematic representation of
the laying up table drive
arrangement for use with the laying
up table shown in Figure 1; and Fire 3 shows a schematic representation of
the steps involved in the
manufacture of a composite
propeller or fan blade.
N- referring to Figures 1 and 2 of the drawIngs, a laying up table made in accordance with the present invention, comprises:
- a first carrier member 1 and a second
carrier member 2, both of which have a
vacuum hold facility in order to hold
articles being layered and bonded in
position thereon; and - a drive arrangement, to move the first
and second carrier members 1 and 2
relative to one another and provide a
gap of variable width therebetween.
The drive arrangement comprises:
- a first bogie member 3 having a shaft 4 It two drive wheels 5 mounted at the
ends thereof, whIch bogie me~3e- mounted under the first carrier member
1 so that it extends transversely to the dIrectIon of movement of the first
carrier member 1; a second bogie member 6 having a shaft 7 with drive wheels 8 mounted one at each end of the shaft 7, which bogie member is mounted under the second carrier member 2; two drive belts 9, one mounted between the drive wheels 5 and 6, at a respect end of the bogie members 3 and 6;; a first mounting member 10 onto which the first carrier member 1 is mounted, and which mounting member 10 is fixedly secured to the two drive belts 9 on the uppermost extending section thereof; z second mounting member li onto which the second carrier r,tem3er 2 is mounted and which mounting member is fixedly secured to the two drive belts 9 on the lower most extending section thereof; position feedback sensors 5 which determine the wldth of the gap D; and - a stepper motor 12 which is connected
by a belt means 13 to the drive wheel 5
of the first bogie member 3.
The stepper motor 12 may include or have associated therewith a gearbox means, which reduces or scales up the length of the movement induced by the stepper motor in order to reduce the gap D by the predetermined distance.
With the first and second carrier members fixedly mounted to the drive belts 9 in the manner described overleaf the movement of the first and second carrier members 1 and 2 is in directly opposed directions.
This type of laying up table is suited for use the production of multilayered articles, such as composite fan or propeller blades. In particular, composite fan or propeller blades which are performed from a folded preform, the folding of which produces a root lug for attachment of the blades to another member or other eaipment.
In the manufacture of a multilayer composite fan blade formed from a folded preform, which has a lug member, the following operational steps will be followed.
The lay up table is set-up so that a gap of width
D exists between the first and second carrier members 1 and 2.
The first layer A of the multilayer composite fan blade is now laid upon the first and second carrier members 1 and 2 so that the lug section overlies the gap D. This layer is held in pcslticn by the action of the vacuum hold down facility provided in the first and second carrier mergers 1 and 2.
The first and second carrier members 1 and 2 are now moved in opposing directions under the influence of the stepper motor 12 so that the width of the gap D between the carrier members 1 and 2 is reduced by a predetermined amount iD.
The second layer of the multilayer composite fan blade is now laid upon the first layer A (or previously laid layer with subsequent layers), is then heat bonded in the conventional manner to the preceding layer and then the width of the gap D is reduced by a predetermined amount.
Subsequent layers are also laid in this manner until all the layers of the multilayer composite fan blade are in place.
A multilayer blade preform is formed in this manner. Once this has been completed, the preform is folded over onto its self about a pivot point, so that the section of the layers in ne vicinty of the gap D form a tab section, It should e noted that the watn of the gap D between the first and second carrier members 1 and 2 is aiwes reduced to provide the correct blade lug length.
When the blade preform is folded the layers In the vicinity of the lug section slbenas a shape having a semicircular base section. The semicirclular base section in turn defines a circle, and the blade lug length required corresponds to the circumference of this defined circle when the preform if folded.
Now as the first and second carrier members 1 and 2 are moved in accordance with the desired periphery of the defined circle. The distance to which the width of the gap D is set after the laying of each subsequent layer of the preform is dictated by the function:
t i where t is the thickness of the
layer of the composite article to
be laid in the vicinity of
the lug sect on for each layer.
Further, obviously the scale of the reduction of the gap D in the build up of the preform will depend upon the physIcal chrteristie of the desired final blade. Therefore, the operation of the stepper motor 12 is controlled by a microprocessor (not shown).
The folded preform is then removed and subjected to further consolidation, for example, a 3-D heat vacuum consolidation phase and resin injection to form a composite fan blade. These manufacturing techniques are well known in the industry and therefore further explanation is not required.
In the finished product made in accordance with the above described method of manufacture the first laid layer A forms the outer most layer of the finished product.
Claims (1)
1. A laying up table for use in the manufacture of a composite multilayer article which is folded to form a lug section, comprising:
- first and second carrier members, which
are moveable so as to provide a gap
whose width may be varied between edges
thereof, and which incorporates
means to hold an article placed thereon
in position; and - a drive arrangement to effect relative movement of the first and second
carrier members; wherein touring the manufacture of multilayer composite articles, a layer of the article is positioned on the first and second carrier me;-tbers, or previously positioned layers, and the first and second carrier members are moved by a predetermined distance so reducing the width of the gap therebetween and slacken the portion of the layer or layers over the gap which will form the lug, so that when the layers are folded over on themselves and no wrinkling occurs between the layers in the article being formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9007565A GB2244453A (en) | 1990-04-04 | 1990-04-04 | Laying up table |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9007565A GB2244453A (en) | 1990-04-04 | 1990-04-04 | Laying up table |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB9007565D0 GB9007565D0 (en) | 1990-05-30 |
| GB2244453A true GB2244453A (en) | 1991-12-04 |
Family
ID=10673840
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9007565A Withdrawn GB2244453A (en) | 1990-04-04 | 1990-04-04 | Laying up table |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2244453A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2432090R1 (en) * | 2012-03-26 | 2014-08-12 | Airbus Operations, S.L. | PROCESS OF MANUFACTURE OF PARTS PERFORMED IN COMPOSITE MATERIAL AND EMPLOYED DEVICE. |
| WO2014184474A1 (en) * | 2013-05-17 | 2014-11-20 | Aircelle | Process for manufacturing non-planar composite parts |
| US8911650B2 (en) | 2008-07-29 | 2014-12-16 | Airbus Operations Limited | Method of manufacturing a composite element |
| US20150231848A1 (en) * | 2014-02-18 | 2015-08-20 | The Boeing Company | Composite Filler |
| WO2017174945A1 (en) * | 2016-04-06 | 2017-10-12 | Safran Nacelles | Preform for composite materials, having narrowed angles after conformation |
| CN110520267A (en) * | 2017-04-28 | 2019-11-29 | 株式会社斯巴鲁 | Composite molding fixture, composite material forming method and composite material |
| US10858944B2 (en) | 2018-03-09 | 2020-12-08 | Rolls-Royce Plc | Method of manufacturing a fan blade and a fan blade |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1372076A (en) * | 1971-05-25 | 1974-10-30 | Velo Bind Inc | Apparatus for casing books |
| GB2012301A (en) * | 1978-01-16 | 1979-07-25 | Johnson & Son Inc S C | Aqueous liquid scouring cleanser |
| GB1578244A (en) * | 1976-02-19 | 1980-11-05 | Black & Decker Inc | Foldable workbenches |
| US4415149A (en) * | 1981-06-25 | 1983-11-15 | Wen Products, Inc. | Portable workbench |
| US4498662A (en) * | 1983-05-04 | 1985-02-12 | Halter Wilbur C | Adjustable pipe clamp holders |
-
1990
- 1990-04-04 GB GB9007565A patent/GB2244453A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1372076A (en) * | 1971-05-25 | 1974-10-30 | Velo Bind Inc | Apparatus for casing books |
| GB1578244A (en) * | 1976-02-19 | 1980-11-05 | Black & Decker Inc | Foldable workbenches |
| GB2012301A (en) * | 1978-01-16 | 1979-07-25 | Johnson & Son Inc S C | Aqueous liquid scouring cleanser |
| US4415149A (en) * | 1981-06-25 | 1983-11-15 | Wen Products, Inc. | Portable workbench |
| US4498662A (en) * | 1983-05-04 | 1985-02-12 | Halter Wilbur C | Adjustable pipe clamp holders |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9573298B2 (en) | 2008-07-29 | 2017-02-21 | Airbus Operations Limited | Apparatus for manufacturing a composite element |
| US8911650B2 (en) | 2008-07-29 | 2014-12-16 | Airbus Operations Limited | Method of manufacturing a composite element |
| ES2432090R1 (en) * | 2012-03-26 | 2014-08-12 | Airbus Operations, S.L. | PROCESS OF MANUFACTURE OF PARTS PERFORMED IN COMPOSITE MATERIAL AND EMPLOYED DEVICE. |
| US9782958B2 (en) | 2012-03-26 | 2017-10-10 | Airbus Operations S.L. | Method and device for manufacturing composite material parts |
| WO2014184474A1 (en) * | 2013-05-17 | 2014-11-20 | Aircelle | Process for manufacturing non-planar composite parts |
| FR3005598A1 (en) * | 2013-05-17 | 2014-11-21 | Aircelle Sa | PROCESS FOR MANUFACTURING NON-PLAN COMPOSITE PARTS |
| US20150231848A1 (en) * | 2014-02-18 | 2015-08-20 | The Boeing Company | Composite Filler |
| US9662842B2 (en) | 2014-02-18 | 2017-05-30 | The Boeing Company | Composite filler |
| US9566739B2 (en) * | 2014-02-18 | 2017-02-14 | The Boeing Company | Composite filler |
| US10661495B2 (en) | 2014-02-18 | 2020-05-26 | The Boeing Company | Composite filler |
| US11247383B2 (en) | 2014-02-18 | 2022-02-15 | The Boeing Company | Composite filler |
| WO2017174945A1 (en) * | 2016-04-06 | 2017-10-12 | Safran Nacelles | Preform for composite materials, having narrowed angles after conformation |
| FR3049887A1 (en) * | 2016-04-06 | 2017-10-13 | Aircelle Sa | PREFORM FOR COMPOSITE MATERIALS HAVING SQUARE ANGLES AFTER CONFORMATION |
| CN110520267A (en) * | 2017-04-28 | 2019-11-29 | 株式会社斯巴鲁 | Composite molding fixture, composite material forming method and composite material |
| EP3616873A4 (en) * | 2017-04-28 | 2021-01-20 | Subaru Corporation | Composite-material molding tool, composite-material molding method and composite material |
| US11584042B2 (en) | 2017-04-28 | 2023-02-21 | Subaru Corporation | Composite material forming jig, composite material forming method and composite material |
| US10858944B2 (en) | 2018-03-09 | 2020-12-08 | Rolls-Royce Plc | Method of manufacturing a fan blade and a fan blade |
| US11187084B2 (en) | 2018-03-09 | 2021-11-30 | Rolls-Royce Plc | Method of manufacturing a fan blade and a fan blade |
| US11441429B2 (en) | 2018-03-09 | 2022-09-13 | Rolls-Royce Plc | Composite fan blade and manufacturing method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| GB9007565D0 (en) | 1990-05-30 |
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