1.8 Simulated Altitude Test Cells
23
Fig. 1.18 The air conditioning system for air supply (© DGA Aero-engine Testing)
– an air dryer and a water injection system regulate humidity, the main function of
the air dryer being to remove the moisture of the air upstream of the turbine to
avoid damaging its blades.
Downstream, cooling systems such as chillers, water injection systems, water
cooling jacketed pipes, channels where pipes are immersed are used to cool the working gases (see Fig. 1.18). Compressors (exhausters) enable regulation of pressure and
release of air back into the atmosphere.
The air supply and exhaust system enable the recreation of the same temperature,
pressure, humidity and mass flow rate as the corresponding altitude and aircraft
velocity required by the customer. They can provide:
– a mass flow rate up to 150 kg/s,
– a pressure from quasi vacuum to 22 bar,
– a temperature from −70 to 520 °C.
The above-mentioned range of values is given for all the test-beds of DGA Aeroengine Testing facility, including combustion chamber test rigs. Conditions at the
outlet of the compressor are reproduced upstream the combustion chamber, where
the pressure can reach, 22 bar and temperature, 520 °C.
23
Fig. 1.18 The air conditioning system for air supply (© DGA Aero-engine Testing)
– an air dryer and a water injection system regulate humidity, the main function of
the air dryer being to remove the moisture of the air upstream of the turbine to
avoid damaging its blades.
Downstream, cooling systems such as chillers, water injection systems, water
cooling jacketed pipes, channels where pipes are immersed are used to cool the working gases (see Fig. 1.18). Compressors (exhausters) enable regulation of pressure and
release of air back into the atmosphere.
The air supply and exhaust system enable the recreation of the same temperature,
pressure, humidity and mass flow rate as the corresponding altitude and aircraft
velocity required by the customer. They can provide:
– a mass flow rate up to 150 kg/s,
– a pressure from quasi vacuum to 22 bar,
– a temperature from −70 to 520 °C.
The above-mentioned range of values is given for all the test-beds of DGA Aeroengine Testing facility, including combustion chamber test rigs. Conditions at the
outlet of the compressor are reproduced upstream the combustion chamber, where
the pressure can reach, 22 bar and temperature, 520 °C.