Compact Combustion Systems Using a Combination of Trapped Vortex and High-G Combustor Technologies

Abstract

Major advances in combustor technology are required to meet the conflicting challenges of improving performance, increasing durability and maintaining cost. Ultra-short combustors to minimize residence time, with special flame-holding mechanisms to cope with increased through-velocities are likely in the future. This paper focuses on vortex-stabilized combustor technologies that can enable the design of compact, high-performance combustion systems. Compact combustors weigh less and take up less volume in space-limited turbine engine for aero applications. This paper presents the UCC, a novel design based on TVC work that uses high swirl in a circumferential cavity to enhance mixing rates via high cavity g-loading on the order of 3000 g’s. The UCC design integrates compressor and turbine features which will enable a shorter and potentially less complex gas turbine engine. Ultimately, it is envisioned that this type of combustion system can be used as the main combustor and/or as a secondary combustor between the high pressure and low pressure turbine to operate as a reheat cycle engine. The focus on this paper includes experimental results of the UCC for a variety of conditions: (1) the addition of turbine vanes in the combustor flowpath, (2) a comparison of JP-8 and FT fuel performance in the combustor, (3) the use of trapped-vortex-like air addition to increase combustor flammability limits, and (4) combustor performance related to two different fuel injector designs. Lean blowout fuel-air ratio limits at 20% the value of current systems were demonstrated. Combustion efficiency was measured over a wide range of UCC operating conditions. This data begins to build the design space required for future engine designs that may use these novel, compact, high-g combustion systems.