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公开(公告)号：US10215416B2
公开(公告)日：2019-02-26
申请号：US14950759
申请日：2015-11-24
摘要： 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.
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公开(公告)号：US10060622B2
公开(公告)日：2018-08-28
申请号：US14793775
申请日：2015-07-08
CPC分类号： F23D14/02 , F23C2900/07001 , F23D14/24 , F23R3/14
摘要： 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 α 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.
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