Heat shield-less combustor and cooling of combustor liner

Details Heat shield-less combustor and cooling of combustor liner Heat shield-less combustor and cooling of combustor liner

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/42 (2006.01) F02C 3/14 (2006.01)

Patent

CA 2579057

A gas turbine engine combustor (16) comprises a heat shield-less combustor design in which a plurality of holes (46, 46~) are provided in the dome portion of the liner itself (34, 34A, 34B), which holes are adapted to direct air into the combustion chamber in a spiral around the axis of an associated one of the fuel nozzle openings.

Chambre de combustion (16) de moteur à turbine de gaz comprenant une chambre de combustion sans bouclier thermique, une pluralité de trous (46, 46~) étant conçue dans la partie voûtée de l~avion de ligne lui-même (34, 34A, 34B), lesdits trous étant adaptés pour diriger l~air dans la chambre de combustion, dans une spirale entourant l'axe d~une ouverture associée des injecteurs à combustible.

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