Abstract: A burner includes a main body having an outer surface and at least partially defining an interior. The main body further includes an upstream end axially spaced from a downstream end. The outer surface includes a burner front face at the downstream end of the main body. An annular cooling air plenum is defined in the main body radially inwardly from the outer surface. A cooling air passage extends from the outer surface to the annular cooling air plenum. A plurality of cooling channels is circumferentially spaced apart from one another along the burner front face. Each cooling channel of the plurality of cooling channels extends from a respective inlet in fluid communication with the annular cooling air plenum to a respective outlet.

Abstract: A burner includes a main body having an outer surface and at least partially defining an interior. The main body further includes an upstream end axially spaced from a downstream end. The outer surface includes a burner front face at the downstream end of the main body. An annular cooling air plenum is defined in the main body radially inwardly from the outer surface. A cooling air passage extends from the outer surface to the annular cooling air plenum. A plurality of cooling channels is circumferentially spaced apart from one another along the burner front face. Each cooling channel of the plurality of cooling channels extends from a respective inlet in fluid communication with the annular cooling air plenum to a respective outlet.

Abstract: This application describes a mixing system for a gas turbine combustor arrangement, the mixing system including a lobed mixer and a wall, enclosing a fluid flow path, wherein the lobed mixer is arranged in the wall, between a first part of the wall and a second part of the wall, and wherein the first part of the wall and the second part of the wall are spaced apart in the direction of a lobed mixer axis. Details of the lobed mixer and a method of mixing two flows in a mixing system are also described.

Abstract: The invention relates to a transition piece assembly for a gas turbine. A transition piece having one end adapted for connection to a gas combustor and an opposite end adapted for connection to a first turbine stage. The transition piece having at least one external liner and at least one internal liner. The internal liner forms the hot gas flow channel. A first section of the transition piece assembly upstream of a first turbine stage has a plurality of cooling apertures. Cooling medium through the cooling apertures enters the plenum, which is created between external and internal liners and a cooling medium flows along at least the first section of the transition piece assembly. At least one second section upstream of the first section with respect to the hot gas flow has at least one additional air inlet system.

Abstract: This application describes a mixing system for a gas turbine combustor arrangement, the mixing system including a lobed mixer and a wall, enclosing a fluid flow path, wherein the lobed mixer is arranged in the wall, between a first part of the wall and a second part of the wall, and wherein the first part of the wall and the second part of the wall are spaced apart in the direction of a lobed mixer axis. Details of the lobed mixer and a method of mixing two flows in a mixing system are also described.