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 burner of a gas turbine has a duct, a vortex generator extending in the duct and including a leading edge and a trailing edge. The trailing edge has a first order lobed shape. The first order lobed shape is defined by a second order lobed shape. Preferably a nozzle for fuel injection is connected to the vortex generator and the second order lobed shape is only provided at the nozzles.

Abstract: The present invention relates to an axial swirler, in particular for premixing of oxidizer and fuel in gas turbines. The axial swirler for a gas turbine burner includes a plurality of swirl vanes with a streamline cross-section being arranged around a swirler axis and extending in radial direction between an inner radius Rmin and an outer radius Rmax. Each swirl vane has a leading edge, a trailing edge, and a suction side and a pressure side extending each between the leading and trailing edges. A discharge flow angle ? between a tangent to the swirl vane camber line at its trailing edge and the swirler axis is first function of radial distance R from the swirler axis. A position of maximum camber of the swirl vane is second function of radial distance R from the swirler axis. At least one swirl vane of the first and second functions include each a respective local maximum and local minimum values along said radial distance from Rmin to Rmax. The invention also relates to a burner with such a swirler.

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 burner of a gas turbine has a duct, a vortex generator extending in the duct and including a leading edge and a trailing edge. The trailing edge has a first order lobed shape. The first order lobed shape is defined by a second order lobed shape. Preferably a nozzle for fuel injection is connected to the vortex generator and the second order lobed shape is only provided at the nozzles.

Abstract: The present invention relates to an axial swirler, in particular for premixing of oxidizer and fuel in gas turbines. The axial swirler for a gas turbine burner includes a plurality of swirl vanes with a streamline cross-section being arranged around a swirler axis and extending in radial direction between an inner radius Rmin and an outer radius Rmax. Each swirl vane has a leading edge, a trailing edge, and a suction side and a pressure side extending each between the leading and trailing edges. A discharge flow angle a between a tangent to the swirl vane camber line at its trailing edge and the swirler axis is first function of radial distance R from the swirler axis. A position of maximum camber of the swirl vane is second function of radial distance R from the swirler axis. At least one swirl vane of the first and second functions include each a respective local maximum and local minimum values along said radial distance from Rmin to Rmax. The invention also relates to a burner with such a swirler.