| CPC F02C 7/052 (2013.01) [B03C 3/017 (2013.01); B03C 3/366 (2013.01); B03C 3/45 (2013.01); B03C 3/70 (2013.01); B03C 3/86 (2013.01); F23R 3/42 (2013.01)] | 20 Claims |

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1. A gas turbine engine combustor section extending axially from a pre-diffuser at a forward end to an aft end relative to an engine axis, the gas turbine engine combustor section comprising:
a combustor liner defining a combustion chamber;
a combustor dome situated at a forward end of the combustor liner and affixed thereto;
an electrostatic particulate matter collector comprising a first charged flow guide having an axially forward-most extent aligned with the pre-diffuser, and widening radially with respect to the engine axis from the axially forward-most extent to the combustor dome;
a fuel nozzle extending through the first charged flow guide into the combustor dome; and
a power supply electrically coupled to positively charge the first charged flow guide.
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