Patent ID: 6651439
Filing Date: 2003-11-25
Classification: F23R,Y02T

Abstract:
A method for supplying airflow to a gas turbine engine combustor through a diffuser, the combustor including at least one dome, the gas turbine engine having a longitudinal axis of symmetry, the diffuser including a radially outer wall, a radially inner wall, and a plurality of splitter vanes spaced radially between the radially outer wall and radially inner wall, said method comprising the steps of:directing compressed airflow axially to the combustor diffuser; and channeling the compressed airflow through at least three passages defined by the splitter vanes and extending through the diffuser, wherein a portion of the airflow exiting the diffuser is channeled radially inwardly with respect to the engine centerline through a radially inner passage, and a portion of the airflow is channeled obliquely with respect to the engine centerline through a center passage that is defined between a radially outer passage and the radially inner passage, and channeling the airflow discharged from the at least three passages through a diffuser dump region defined between the combustor dome and the diffuser.