Rapid processing of laminar composite components
US-12180120-B2 · Dec 31, 2024 · US
Gas turbine engine component external surface micro-channel cooling
US10329917B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10329917-B2 |
| Application number | US-201414767922-A |
| Country | US |
| Kind code | B2 |
| Filing date | Feb 26, 2014 |
| Priority date | Mar 5, 2013 |
| Publication date | Jun 25, 2019 |
| Grant date | Jun 25, 2019 |
How to read this patent
A practical reading order for non-experts. Skip the full description unless you need deep technical detail.
- Title
What the patent document calls the invention.
- Abstract
A short plain-language summary of the technical disclosure.
- Assignees and inventors
Who owns or filed the patent and who is credited as inventor.
- Key dates
Filing, priority, publication, and grant dates set the timeline.
- First independent claim
The legal scope of protection — read this for what is actually claimed.
- CPC / IPC classifications
Technology tags used to group this patent with similar filings.
- Citations and related patents
Prior art links and similar publications in this corpus.
Abstract
Official abstract text for this publication.
A gas turbine engine component that includes a structure having a surface which includes multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm.
First claim
Opening claim text (preview).
What is claimed is: 1. A gas turbine engine component comprising: a structure having a surface, the surface including multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm, wherein the structure includes a substrate, a thermal barrier coating is adhered to the substrate with a bond coat having a uniform thickness, the thermal barrier coating providing the surface with the channels provided only in the thermal barrier coating such that the bond coat is arranged on a side of the thermal barrier coating opposite the channels, wherein the cooling channels are arranged in an intersecting pattern. 2. The gas turbine engine component according to claim 1 , wherein the surface is a line-of-sight surface. 3. The gas turbine engine component according to claim 1 , wherein the structure is an airfoil having an internal cooling passage. 4. The gas turbine engine component according to claim 1 , wherein the substrate is a nickel alloy, and the thermal barrier coating is a ceramic. 5. The gas turbine engine component according to claim 1 , wherein the cooling channels include a generally U-shaped cross-section. 6. The gas turbine engine component according to claim 1 , wherein the cooling channels include a generally V-shaped cross-section. 7. The gas turbine engine component according to claim 1 , wherein the cooling channels form pyramid shaped structures. 8. The gas turbine engine component according to claim 1 , wherein the cooling channels are arranged at acute angles relative to one another. 9. A gas turbine engine component comprising: a structure having a surface, the surface including multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm, wherein the structure includes a substrate, a thermal barrier coating is adhered to the substrate with a bond coat having a uniform thickness, the thermal barrier coating providing the surface with the channels provided only in the thermal barrier coating such that the bond coat is arranged on a side of the thermal barrier coating opposite the channels, wherein the cooling channels are arranged in a circular pattern. 10. The gas turbine engine component according to claim 9 , wherein the surface is a line-of-sight surface. 11. The gas turbine engine component according to claim 9 , wherein the structure is an airfoil having an internal cooling passage. 12. The gas turbine engine component according to claim 9 , wherein the substrate is a nickel alloy, and the thermal barrier coating is a ceramic. 13. The gas turbine engine component according to claim 9 , wherein the cooling channels include a generally U-shaped cross-section. 14. The gas turbine engine component according to claim 9 , wherein the cooling channels include a generally V-shaped cross-section. 15. A gas turbine engine component comprising: a structure having a surface, the surface including multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm, wherein the structure includes a substrate, a thermal barrier coating is adhered to the substrate with a bond coat having a uniform thickness, the thermal barrier coating providing the surface with the channels provided only in the thermal barrier coating such that the bond coat is arranged on a side of the thermal barrier coating opposite the channels, wherein the cooling channels provide a circular recess without circumscribing the structure. 16. The gas turbine engine component according to claim 15 , wherein the surface is a line-of-sight surface. 17. The gas turbine engine component according to claim 15 , wherein the structure is an airfoil having an internal cooling passage. 18. The gas turbine engine component according to claim 15 , wherein the substrate is a nickel alloy, and the thermal barrier coating is a ceramic. 19. The gas turbine engine component according to claim 15 , wherein the cooling channels include a generally U-shaped cross-section. 20. The gas turbine engine component according to claim 15 , wherein the cooling channels include a generally V-shaped cross-section.
Assignees
Inventors
Classifications
by the use of microcircuits · CPC title
Film cooling (F01D5/187 takes precedence) · CPC title
by film cooling · CPC title
Cross-Sectional Technologies · mapped topic
in gas turbines · CPC title
Patent family
Related publications grouped by family.
External sources
Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US10329917B2 cover?
- A gas turbine engine component that includes a structure having a surface which includes multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm.
- Who is the assignee on this patent?
- United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F01D5/147. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jun 25 2019 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).