Patent ID: 9027349
Filing Date: 2015-05-12
Classification: F23R

Abstract:
1. A gas turbine combustor comprising: a combustion chamber to which fuel and air are supplied; an air hole plate located on an upstream side of the combustion chamber and having a first air hole adapted to supply air to the combustion chamber, and second air holes installed on an outer circumferential side of the first air hole and adapted to supply air to the combustion chamber; a first fuel nozzle adapted to supply gaseous fuel to the first air hole; second fuel nozzles adapted to supply gaseous fuel to the second air holes; a first orifice adapted to allow the gaseous fuel supplied to the first air hole to cause a pressure drop; and a second orifice adapted to allow the gaseous fuel supplied to each of the second air holes to cause a pressure drop; wherein the second orifice has an opening area smaller than an opening area of the first orifice.