Patent ID: 6983606
Filing Date: 2006-01-10
Classification: F02C,F23R

Abstract:
1. A fuel injection system in a gas turbine engine, comprising: an annular combustion chamber centered about a central rotational axis of the engine; a centrifugal compressor having an impeller centered about the central rotational axis, the impeller having a contoured rear surface substantially opposite an air-receiving front surface, the rear surface having a radially outboard portion defining a first lip protruding into a circumferential opening defined by the annular combustion chamber; and a fuel supply line having a fuel release point proximate a portion of the rear surface radially inboard from the first lip, the rear surface, the first lip, and the circumferential opening defining a flow path for fuel to flow from the fuel supply line into the combustion chamber; wherein said first lip directs the fuel flow substantially parallel to said central rotational axis.