Engine systems and methods for removing particles from turbine air
US-2015354461-A1 · Dec 10, 2015 · US
Outer rim seal assembly in a turbine engine
US8939711B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-8939711-B2 |
| Application number | US-201313768561-A |
| Country | US |
| Kind code | B2 |
| Filing date | Feb 15, 2013 |
| Priority date | Feb 15, 2013 |
| Publication date | Jan 27, 2015 |
| Grant date | Jan 27, 2015 |
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 seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.
First claim
Opening claim text (preview).
What is claimed is: 1. A seal assembly between a hot gas path and a disc cavity in a turbine engine comprising: a non-rotatable vane assembly including a row of vanes and an inner shroud; a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, the blades extending from a platform of the blade assembly; and an annular wing member located radially between the hot gas path and the disc…
Assignees
Inventors
Classifications
Patent family
Related publications grouped by family.
External sources
Next steps
Free tools are coming soon. Tell us what you want to track and we'll notify you.
Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US8939711B2 cover?
- A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. T…
- Who is the assignee on this patent?
- Lee Ching-Pang, Tham Kok-Mun, Shivanand Manjit, and 4 more
- What technology area does this patent fall under?
- Primary CPC classification F01D5/081. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jan 27 2015 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).