Fuel system and method for supplying a combustion chamber in an aircraft turboshaft engine with fuel
US-2024318601-A1 · Sep 26, 2024 · US
US9052115B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9052115-B2 |
| Application number | US-201213455480-A |
| Country | US |
| Kind code | B2 |
| Filing date | Apr 25, 2012 |
| Priority date | Apr 25, 2012 |
| Publication date | Jun 9, 2015 |
| Grant date | Jun 9, 2015 |
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A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. Injectors circumferentially arranged around the flow sleeve provide fluid communication through the flow sleeve and into the combustion chamber. A valve upstream from the injectors has a first position that permits working fluid flow to the injectors and a second position that prevents working fluid flow to the injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid through a combustion chamber, diverting a portion of the working fluid through injectors circumferentially arranged around the combustion chamber, and operating a valve upstream from the injectors to control the working fluid flow through the injectors.
Opening claim text (preview).
What is claimed is: 1. A system for supplying a working fluid to a combustor, comprising: a liner, wherein the liner at least partially defines a combustion chamber within the combustor; a flow sleeve that circumferentially surrounds the liner, wherein the flow sleeve and the liner define an annular passage therebetween; a plurality of injectors circumferentially arranged around and extending through the flow sleeve and the liner, each injector having a plurality of fuel ports…
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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