Blade made of organic matrix composite material provided with a metal strip, and a method of fastening a metal strip on a blade fiber preform
US-2016312616-A1 · Oct 27, 2016 · US
Method of fabricating a composite material blade having an integrated metal leading edge for a gas turbine aeroengine
US2016167269A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2016167269-A1 |
| Application number | US-201414908321-A |
| Country | US |
| Kind code | A1 |
| Filing date | Jul 22, 2014 |
| Priority date | Jul 29, 2013 |
| Publication date | Jun 16, 2016 |
| Grant date | — |
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- Title
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Abstract
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A method of fabricating a blade of composite material having an incorporated metal leading edge for a gas turbine aeroengine, the method including in succession placing a metal strip for making the leading edge of a blade in a cavity of an injection mold for making the blade, closing the injection mold, injecting a thermoplastic resin under pressure into the cavity of the mold so as to shape and overmold the metal strip, compacting the assembly, solidifying the resin by regulating the temperature of the injection mold, and unmolding the resulting blade.
First claim
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1 . A method of fabricating a blade of composite material having an incorporated metal leading edge for a gas turbine aeroengine, the method comprising in succession: placing a metal strip for making the leading edge of a blade in a cavity of an injection mold for making the blade; closing the injection mold; injecting a filled thermoplastic resin under pressure into the cavity of the mold so as to shape and overmold the metal strip; compacting the assembly; solidifying the resin by regulating the temperature of the injection mold; and unmolding the resulting blade:, in which method the injection step is performed in a mold cavity having no fiber preform. 2 . A method according to claim 1 , including comprising completely closing the injection mold prior to starting injection of the resin. 3 . A method according to claim 1 , including comprising partially closing the injection mold prior to and during injection of the resin. 4 . A method according to claim 3 , further including comprising compressing the partially closed injection mold in order to close it completely during the step of injecting the resin. 5 . A method according to claim 1 , wherein the method comprises molding the blade simultaneously with molding at least one platform of the blade. 6 . (canceled) 7 . (canceled) 8 . The use of the method according to claim 1 for fabricating a fan blade, an outlet guide vane, an inlet guide vane, or a variable stator vane.
Assignees
Inventors
Classifications
Metals, alloys or intermetallic compounds · CPC title
Moulding material on one side only of the preformed part · CPC title
Selecting composite materials, e.g. blades with reinforcing filaments · CPC title
Inserting articles into the mould (B29C45/14827 takes precedence) · CPC title
essentially without removing material · CPC title
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- What does patent US2016167269A1 cover?
- A method of fabricating a blade of composite material having an incorporated metal leading edge for a gas turbine aeroengine, the method including in succession placing a metal strip for making the leading edge of a blade in a cavity of an injection mold for making the blade, closing the injection mold, injecting a thermoplastic resin under pressure into the cavity of the mold so as to shape an…
- Who is the assignee on this patent?
- Safran
- What technology area does this patent fall under?
- Primary CPC classification B29C45/14336. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Thu Jun 16 2016 00:00:00 GMT+0000 (Coordinated Universal Time) (A1). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 1 related publication on this page (citations in our corpus or others sharing the same primary CPC).