Patent ID: 9458767
Filing Date: 2016-10-04
CPC Classification: F01D,F02C

Claim Text:
1. A turbine nozzle segment, comprising: an inner platform, an outer platform and an airfoil that extends therebetween, the airfoil having a forward portion and an aft portion that is disposed downstream from the forward portion; a fuel injection insert that extends between the inner platform and the outer platform, wherein the fuel injection insert is positioned downstream from the aft portion of the airfoil, the fuel injection insert including a pressure side, a suction side and a trailing edge defined along an aft portion of the fuel injection insert, wherein the fuel injection insert is detached from the airfoil, such that a gap is formed between a forward portion of the fuel injection insert and the aft portion of the airfoil; a source of fuel in fluid communication with the fuel injection insert, wherein the fuel is combusted downstream of the airfoil; a fuel circuit that extends within the fuel injection insert; and a plurality of fuel injection ports disposed within the fuel injection insert, wherein the plurality of fuel injection ports are in fluid communication with the fuel circuit, wherein at least one fuel injection port of the plurality of fuel injection ports is defined along at least one of the pressure side and the suction side of the fuel injection insert.