Segmented core and method for molding an impeller
US-2015375294-A1 · Dec 31, 2015 · US
Additively manufactured core for use in casting an internal cooling circuit of a gas turbine engine component
US11059093B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11059093-B2 |
| Application number | US-201816217908-A |
| Country | US |
| Kind code | B2 |
| Filing date | Dec 12, 2018 |
| Priority date | Oct 26, 2015 |
| Publication date | Jul 13, 2021 |
| Grant date | Jul 13, 2021 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core portion.
First claim
Opening claim text (preview).
What is claimed: 1. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component, the method comprising: manufacturing a base core portion of a first crushable material without at least one portion of the internal cooling circuit; and additively manufacturing an additive core portion to the base core portion, the additive core portion comprising the at least one portion of the internal cooling circuit of the core to form a complete internal cooling circuit, the additive core portion manufactured of a second crushable material, the second crushable material less crushable than the first crushable material. 2. The method as recited in claim 1 , further comprising casting the base core portion. 3. The method as recited in claim 1 , further comprising forming the additive core portion to form a multiple of trailing edge crossovers. 4. The method as recited in claim 1 , further comprising additively manufacturing the additive core portion to form a multiple of pin-shaped protrusions. 5. The method as recited in claim 1 , further comprising firing the additive core portion and the base core portion. 6. The method as recited in claim 1 , further comprising additively manufacturing the additive core portion to form a trailing edge portion of the core. 7. The method as recited in claim 1 , further comprising positioning the core within a shell. 8. The method as recited in claim 7 , wherein the additive core portion at least partially contacts the shell.
Assignees
Inventors
Classifications
Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS] · CPC title
Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title
Manufacture of moulds · CPC title
Process efficiency · CPC title
by thermal treatment, e.g. strain annealing (C30B1/12 takes precedence) · CPC title
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- What does patent US11059093B2 cover?
- A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core port…
- Who is the assignee on this patent?
- United Technologies Corp, Raytheon Tech Corp
- What technology area does this patent fall under?
- Primary CPC classification B22C9/103. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Jul 13 2021 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).