High-Pressure Combustor Test Facility 2
The High Pressure Combustion Chamber Test Stand 2 is the test stand with the widest range of operations. From small can combustors and multi-stage combustion systems to full engine combustor ring tests, almost any test is possible.
The High Pressure Combustor Test Facility 2 (HBK 2) is used as a research platform to validate next-generation combustor technologies. The aim is to enable partners to accelerate the development cycle of the gas turbine combustor component for use in aircraft engines and power plant turbines. To this end, the Institute of Propulsion Technology is combining its core expertise in the validation of combustor technologies up to 40 bar and its cutting-edge research in advanced minimally invasive measurement methods to create a globally unique facility. In cooperation with research partners, DLR provides expertise and facilities to further develop the state of the art in combustion diagnostics.
Characteristics of the test bed
Very wide operating range
Multi-sector or full-ring tests under real operating conditions for combustion chamber pressure and exhaust gas temperature
Flexible use of different fuels
Research Topics
Aviation:
Validation of prototype fat-lean module technology in multi-sector or full-ring experiments under real operating conditions for combustion chamber pressure and exhaust gas temperature.
Aeronautics/Energy Technology:
Basic research on DLR's own development of optical measurement technology under real operating conditions
Energy technology:
Flexibilisation of gas turbines in today's energy market: substitution of standard fuels by future fuels such as hydrogen to reduce climate-damaging emissions.
Simulation to demonstrate combustor technologies for CO2 capture
Demonstration of oxyfuel combustor technologies at real pressures up to 300 bar
Tecnical Data
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Performance | 60 MWth |
Static pressure | bis 40 bar |
Preheating temperature | bis 973 K |
Air mass flow | bis 50 kg/s |
Fuels | CH4, H2, Kerosin, Heizöl, SAF |
