Manfred Aigner

TL;DR: A gas turbine model combustor for swirling CH 4 /air diffusion flames at atmospheric pressure with good optical access for detailed laser measurements is discussed in this article, where three flames with thermal powers between 76 and 349 kW and overall equivalence ratios between 055 and 075 were investigated.

TL;DR: In this paper, a numerical study of mixing and combustion enhancement has been performed for a Mach 2 model scramjet (supersonic combustion ramjet) combustor Fuel (hydrogen) is injected at supersonic speed through the rear of a lobed strut located at the channel symmetry axis.

TL;DR: In this article, a FLOX® burner with a combustion chamber with quartz windows was installed into a high pressure test rig with optical access, and the combustion behavior was investigated as a function of equivalence ratio and fuel composition.

TL;DR: In this article, a commercial swirl burner for industrial gas turbine combustors was equipped with an optically accessible combustion chamber and installed in a high-pressure test-rig. Several premixed natural gas/air flames at pressures between 3 and 6 bar and thermal powers of up to 1MW were studied by using a variety of measurement techniques.

TL;DR: In this paper, an overview of the progress in the design of an enhanced FLOX ® burner is given, where a fuel fiexible burner concept was developed to fulfill the requirements of modern gas turbines: high specific power density, high turbine inlet temperature, and low NO x emissions.