Gas turbine combustor endcover assembly with integrated flow restrictor and manifold seal

An endcover assembly for a turbine combustor adapted to support one or more combustor nozzles, the endcover assembly comprising:

• a substantially flat endcover plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber;
• plural premix fuel passages extending through said substantially flat endcover plate;
• a fuel manifold porting block secured to said opposite side of said substantially flat endcover plate, with a port connecting to each of said plural passages;
• and a fuel restrictor insert formed with multiple flow orifices secured to said fuel manifold porting block at the interface between each premix fuel passage in said endcover plate and each port in said fuel manifold porting block.

A manifold porting block for use with an endcover of a turbine combustor adapted to support one or more combustor nozzles, the manifold porting block comprising:

• a mounting surface configured to abut against a surface of the endcover within the combustor;
• fuel passages adapted to align with passages in the endcover plate;
• and
• a fuel restrictor insert with multiple flow orifices is aligned with one of the fuel passages, the fuel restrictor insert is secured to said fuel manifold porting block and the fuel restrictor insert is proximate to the mounting surface.