Patent ID: 7621132
Filing Date: 2009-11-24
Classification: F23R,Y02E

Abstract:
1. A burner for a gas turbine engine comprising: a) a burner housing defining a longitudinal axis and having axially opposed upstream and downstream end portions, the housing having at least one fuel inlet passage and at least one air inlet passage which are adapted to supply fuel and air respectively to a main internal combustion chamber defined in the burner housing; b) a pilot combustor disposed within the main internal combustion chamber of the burner housing and having a central axis aligned along the longitudinal axis of the burner housing, the pilot combustor having an inlet for receiving a rich fuel and air mixture, a pilot combustion chamber within which the rich fuel and air mixture is combusted into combustion products, and an outlet for exhausting the combustion products from the pilot combustion chamber; and c) a quencher disposed within the burner housing and having an air inlet and a plurality of air outlets for directing cooling air toward the outlet of the pilot combustor to cool the combustion products exhausted from the pilot combustor; wherein the outlet of the pilot combustor has an annular cross-section adjacent to the quencher.