Effect of dilution in an inter-turbine Flameless combustor
A.A.V. Perpignan (TU Delft - Flight Performance and Propulsion)
Arvind Rao (TU Delft - Flight Performance and Propulsion)
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Abstract
Alternatives
to combustion in aircraft engines are not expected to become feasible in the
decades to come. As the aviation traffic increases and regulations become more
stringent, reduction in pollutant emissions are needed. The Flameless
Combustion (FC) regime has been one of the promising candidates to achieve
lower emissions in gas turbine engines. This combustion regime is characterized
by welldistributed reactions, with low peak temperatures, resulting in lower
emissions and acoustic oscillations. However, the attainment of the FC regime
is not straight forward considering the conditions and requirements of gas
turbines. Most of the previous combustor design attempts failed to provide
broad operational range, high combustion efficiency, or were difficult to
integrate in an engine. Along with a novel aircraft concept, the European project
AHEAD (Advanced Hybrid Engines for Aircraft Development) resulted in the
conceptual design of a gas turbine engine with two sequential combustion
chambers1. As the aircraft concept allows the use of cryogenic fuels, the first
combustion chamber was designed to operate with hydrogen or natural gas. The
second is the inter-turbine combustor herein studied, which would operate under
the FC regime burning conventional fuels.
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