General Electric Company

Hubert Smith Roberts, Jr

Anthony Paul Greenwood

Marwan Al-Roub

Clifford Stephen Creevy

A combustor for a gas turbine engine that facilitates reducing combustor chamber dump pressure losses to improve combustor and engine performance is described. The combustor includes a diffuser that diffuses airflow directed into the combustor. The diffuser includes an outer wall, an inner wall, and a plurality of splitter vanes between the outer wall and the inner wall. The splitter vanes are spaced radially apart, and each is spaced radially from a respective diffuser wall such that an outer passage, an inner passage, and a central passage are defined by the splitter vanes.

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Cincinnati, OH, United States of America

Hubert Smith Roberts, Jr