By enhancing the pre-mixing of fuel and air prior to combustion, recently developed lean-burn combustor systems have led to reduced NOx and particulate emissions in gas turbines. Lean-burn combustor exit flows are typically characterized by non-uniformities in total temperature, or so-called hot-streaks, swirling velocity profiles, and high turbulence intensity. Whilst these systems improve combustor performance, the exiting flow-field presents significant challenges to the aero-thermal performance of the downstream turbine. This paper presents the commissioning of a new fully annular lean-burn combustor simulator for use in the Oxford Turbine Research Facility (OTRF), a transonic rotating facility capable of matching non-dimensional engine conditions. The combustor simulator delivers an engine-representative turbine inlet condition featuring swirl and hot-streaks simultaneously. To the authors' knowledge, this simulator is the first of its kind to be implemented in a rotating turbine test facility.

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