Finely distributed combustion system for a gas turbine engine
A finely distributed combustion system for a gas turbine engine is provided. A combustor body may extend along a longitudinal axis. A premixer space may be formed within the combustor body to premix air and fuel. The premixer space is in communication with an array of finely distributed perforations arranged in a wall of the combustor body to eject an array of premixed main flamelets throughout a contour of the combustor body between the upstream base of the combustor body and the downstream base of the combustor body. The array of finely distributed perforations—potentially comprising thousands or even hundreds of thousands of perforations spatially distributed on a miniaturized scale—for ejecting the premixed main flamelets is technically advantageous compared to conventional distributed combustion systems, where injection of relatively longer main flames occurs just at a few discrete axial locations.
Siemens Energy Global GmbH & Co KG
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F23R F23R F23R F23D F23R F23D F23D F23R F23R F23R F23R F02C F23R F23R
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Juan Enrique Walter Ray Andrew J. Yuntao
Portillo Bilbao Laster North Chen