Fuel system and method for supplying a combustion chamber in an aircraft turboshaft engine with fuel
US-2024318601-A1 · Sep 26, 2024 · US
US9404657B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9404657-B2 |
| Application number | US-201314039913-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 27, 2013 |
| Priority date | Sep 28, 2012 |
| Publication date | Aug 2, 2016 |
| Grant date | Aug 2, 2016 |
A practical reading order for non-experts. Skip the full description unless you need deep technical detail.
What the patent document calls the invention.
A short plain-language summary of the technical disclosure.
Who owns or filed the patent and who is credited as inventor.
Filing, priority, publication, and grant dates set the timeline.
The legal scope of protection — read this for what is actually claimed.
Technology tags used to group this patent with similar filings.
Prior art links and similar publications in this corpus.
Official abstract text for this publication.
A combustor for a gas turbine engine includes an forward fuel injection system in communication with a combustion chamber and a downstream fuel injection system that communicates with the combustion chamber downstream of the forward fuel injection system.
Opening claim text (preview).
What is claimed is: 1. A combustor for a gas turbine engine comprising: a forward fuel injection system in communication with a combustion chamber; and a downstream fuel injection system that communicates with said combustion chamber downstream of said forward fuel injection system, wherein said downstream fuel injection system is radially inboard of said combustion chamber and a main supply line of a radially inner fuel injection manifold extends through a vane in a turbine s…
Related publications grouped by family.
Free tools are coming soon. Tell us what you want to track and we'll notify you.
Answers are generated from the same data shown on this page.