Inter Compressor Duct
The Inter Compressor Duct is a state-of-the-art test facility specifically designed for the in-depth study of steep compressor intercoolers. It also allows the investigation of advanced stator concepts for future engine generations.
Steep intermediate compressor ducts (ICD) offer a promising opportunity to reduce the climate impact of future aircraft engines through lower fuel consumption. The fuel savings are due to several factors, including the reduced weight of the compact engine, the resulting lighter support structure in the engine mount, the improved centre of gravity and the reduced drag.
Characteristics of the Inter Compressor Duct
- Swirler as a rotor replacement: The test bench provides the ability to generate variable swirl to realistically simulate the discharge conditions of the final low-pressure compressor rotor. This makes it possible to generate a realistic inflow to the ICD without the need to install rotating components. This enables cost-effective test campaigns with low design costs.
- Comprehensive, advanced measurement technology: Boundary layer combs, traversable 3- and 5-hole probes, a large number of pressure holes, laser-optic measurement methods and the ability to visualise flow using oil film images provide a detailed flow picture.
- Wide operating range: All major operating points of an aircraft engine, such as take-off, flight and climb, can be analysed with the test stand. A wide range of independently adjustable Mach and Reynolds numbers allows these operating conditions to be closely approximated.
- Air extraction: In real aircraft engine operation, air is always extracted from the ICD to supply the cabin. During the transition to another operating point, a lot of air is typically extracted from the ICD. With the existing lead extraction system, the operating points can be set even more realistically.
Research Topics
Technology Readiness Level 3-5
Detailed study of intermediate compressor ducts
Validation testing of new ICD concepts
Provide detailed measurement data for CFD validation
Investigation of active and passive flow control, transition behaviour
Tecnical Data
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Inlet Mach number | 0.2 – 1.4 |
Reynolds number | 8x105 – 5.3x106 |
Mass flow | 0.1 kg/sec. – 20 kg/sec. |
Total pressure | 0.6 bar – 3 bar |
Temperature | max. 310 K |
Intensity of the inlet turbulence | 0.6 – 4.0 % |
Wind tunnel height | 1.200 mm |
Tapping air mass flow | 0 – 5 kg/sec. |
