Patent ID: 7373772
Filing Date: 2008-05-20
Classification: F01D,F05D

Abstract:
1. A combustion system component for location between a turbine combustor and a first stage turbine airfoil, comprising: a transition piece including a body defining a flowpath and having a generally circular inlet end for receiving combustion products from the combustor and a generally rectilinear outlet end for flowing the combustor products into the first stage nozzle; said body defining between said inlet end and said outlet end an enclosure for confining the flow of combustion products between said ends; a plurality of dilution holes formed in said transition piece body in a first zone adjacent said inlet end and in a second zone adjacent said outlet end for flowing dilution air into the transition piece body; said dilution holes being sized such that substantial equal quantities of the dilution air flow into the flowpath in said zones, respectively; and wherein said holes are located in said transition piece body in accordance with the hole numbers