Patent ID: 7533531
Filing Date: 2009-05-19
Classification: F02C,F23D,F23K,F23R

Abstract:
1. A gas turbine engine internal fuel manifold assembly comprising: an annular fuel distribution manifold having a solid annular body and at least one circumferentially-extending fuel flow passage defined in the solid annular body; and a plurality of fuel nozzles directly mounted to said fuel distribution manifold, and having spray tips in fuel flow communication with said at least one fuel flow passage, each of said spray tips having at least one core airflow passage extending through a center thereof between a spray tip outlet and an air inlet defined in said fuel nozzle, said inlet being in communication with an air source independently of said fuel distribution member, said fuel nozzles each defining a central spray axis concentric with said at least one core airflow passage, and wherein said fuel nozzles are mounted in a radially offset manner relative to said fuel distribution manifold such that said central spray axis extends through said fuel nozzle between said spray tip and said air inlet without intersecting said annular fuel distribution manifold.