Flow body for a gas turbine, gas turbine, method for manufacturing a flow body for a gas turbine, and method for repairing a flow body of a gas turbine
US-2024376825-A1 · Nov 14, 2024 · US
Manufacturing method
US9914171B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9914171-B2 |
| Application number | US-201514873994-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 2, 2015 |
| Priority date | Oct 15, 2014 |
| Publication date | Mar 13, 2018 |
| Grant date | Mar 13, 2018 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
The present invention provides a method of forming a leading edge for an aerofoil component e.g. an aerofoil blade. The method comprises forming a pre-form having a precursor edge and processing said precursor edge to form the leading edge. The pre-form is formed using metal injection molding. The leading edge may have an elliptical profile.
First claim
Opening claim text (preview).
We claim: 1. A method of forming a leading edge of an aerofoil component, the method comprising: forming a pre-form having a precursor edge; and processing the formed precursor edge of the pre-form to form the leading edge of the aerofoil component, wherein: the pre-form is formed using metal injection molding, and the formed precursor edge is sharper than the formed leading edge of the aerofoil component, which is formed as a result of the processing. 2. A method of forming an aerofoil component having a leading edge, the method comprising forming the leading edge according to the method of claim 1 . 3. The method according to claim 1 , wherein forming the pre-form includes: mixing powdered metal or metal alloy with a binder; shaping the mixture by injection into a die; removing the binder; and consolidating the metal/metal alloy powder using heat. 4. The method according to claim 3 , wherein the binder is a thermoplastic plastic. 5. The method according to claim 3 , further comprising removing the binder using a solvent. 6. The method according to claim 1 , further comprising processing the precursor edge to form the leading edge having an elliptical profile. 7. The method according to claim 1 , wherein the step of processing the precursor edge includes mechanical vibratory processing. 8. The method according to claim 1 , wherein the aerofoil component is a blade for a fan, a compressor, or a turbine. 9. A method of manufacturing a fan, a compressor, or a turbine, the method comprising forming a leading edge of a blade of an aerofoil using the method of claim 1 .
Assignees
Inventors
Classifications
not by heating only · CPC title
related to the leading edge of a rotor blade · CPC title
Processes characterised by the sequence of their steps · CPC title
Blades · CPC title
turbine or like blades from one piece · CPC title
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Frequently asked questions
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- What does patent US9914171B2 cover?
- The present invention provides a method of forming a leading edge for an aerofoil component e.g. an aerofoil blade. The method comprises forming a pre-form having a precursor edge and processing said precursor edge to form the leading edge. The pre-form is formed using metal injection molding. The leading edge may have an elliptical profile.
- Who is the assignee on this patent?
- Rolls Royce Plc, Rolls Royce Deutschland Ltd & Co Kg
- What technology area does this patent fall under?
- Primary CPC classification B22F5/04. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Mar 13 2018 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).