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Facilities

Atmosphärische-Primär-Zonen Prüfstand

Der Prüfstand wurde konzipiert, um Luftstromzerstäuberdüsen für die schadstoffarme Verbrennung zu untersuchen. Bei den Düsen handelt es sich um Eigenentwicklungen und Düsen von Industriepartnern. Es können sowohl Isotherme Zerstäubungsversuche als auch Experimente in einer Modellbrennkammer mit Luftvorwärmung und Verbrennung durchgeführt werden.

Single Sector Combustor (SSC) Cologne

High pressure combustion test rig (up to 20 bar) offering three-way optical access to combustor primary zone. Air flow routing characteristic of aero-engine combustors: Mixing jets downstream of primary zone.

Hot-Acoustic-Testrig (HAT), Berlin

The Hot-Acoustic Testrig, which was erected and is operated in close cooperation between DLR department of engine acoustics and Technischen Universität Berlin, chair of aero engines, is a unique facility for acoustic and aerodynamic test at surfaces exposed to high temperature and grazing flow in aero engines.

High Pressure Combustor Test Bed 1 (HBK-1) and test section BOSS Cologne

The test bed HBK-1 provides the operation and supply infrastructure for the test section BOSS (Big Optical Single Sector). In this optically accessible high pressure single sector combustor, burners for lean combustion systems in aeroengines are investigated using optical, in particular laser-based methods.

High Pressure Combustion Chamber Test Rig 2 (HBK 2) Cologne

The HBK2 is the test bed with the broadest operational range. The flexible design allows for the testing of staged combustion, full annular aero engine combustors or small can combustion systems

High Pressure Combustion Chamber Test Rig 3 (HBK 3) Cologne

Today, the HBK3 is used as our middle class test bed to provide an economic testing environment for single sector aero engine combustors and smaller heavy duty systems.

Hochdruck-Kühlungsmessstrecke

Die Temperaturen in Triebwerksbrennkammern liegen mit bis zu 2500 K weit über den zulässigen Materialtemperaturen der Brennkammerwand. Daher ist eine intensive Kühlung der Brennkammerwand erforderlich, wofür ein erheblicher Anteil der vom Verdichter in das Triebwerk geförderten Luft genutzt wird. Für zukünftige leistungsstärkere effizientere und schadstoffarme Triebwerke muss der Anteil der Kühlluft drastisch verringert werden. Dafür bedarf es fortschrittlicher und neu zu entwickelnder Wand- und Kühlkonzepte.

Lean-Permixed-Prevaporized Combustion (LPP) Cologne

The LPP (Lean Premixed Prevaporised) test rig, at DLR Cologne-Porz is designed to operate under high pressure, temperature and velocity conditions, approximating the values found in actual gas turbine combustion systems. The Test rig is fully equipped to perform the measurements on sprays and mixing of air and fuel, under non-reactive conditions.

Multistage Two Shaft Compressor Test Facility (M2VP) Cologne

The driving unit consists of two electrical engines and a two stage gearbox system. The turning direction and the speed of each motor can be independently chosen.

Turbomachinery noise test rigs, Berlin

The analysis of the sound field emitted by turbomachines helps to understand the mechanisms of how turbomachinery noise is generated and is a basic requirement for the development of noise reduction methods.

Low Speed Cascade Tunnel, Göttingen (NGG)

The NGG is an intermediate running blow down type facility, built up in a similar way as the Windtunnel for Straight Cascades (EGG). Atmospheric air from the wind tunnel hall passes the inlet duct, the test section with the cascade, an adjustable choking diffuser and finally through a valve (o-ring flap) and a pipe system into a large vacuum vessel. The vessel with a capacity of 10000 m³ is constantly evacuated by a set of vacuum pumps, allowing measuring times of up to 20 minutes. The mass flow through the wind tunnel and hence the back pressure or isentropic exit Mach number of the cascade is set by an adjustable diffuser.

Skin friction reduction by means of riblet surfaces, Berlin

Skin friction reducing riblet surfaces consist of very small grooves with sharp ridges which have to be aligned with the mean flow. The grooves have to be designed in a way that they appear to the flow as a hydrodynamically smooth surface, i.e. they are almost completely submerged in the viscous sublayer. The skin friction reduction is obtained by the reduction of the turbulent spanwise motion near the wall.

Radial Compressor Cologne

Radial (centrifugal) compressors can be built rather compact and are known to be robust in handling. They find their widespread application in aero-engines of small- and medium power.

The Probe Calibration Facility, Göttingen (SEG)

Pneumatic probes are still useful tools when investigating flow fields within turbomachines, cascades or any other aerodynamic facilities. Due to the fact that flow velocity and flow direction cannot be measured directly by the probes as well as due to inaccuracies when manufacturing the probe heads, a calibration process in flow fields with well known and constant flow conditions is necessary.

Subsonic Cascade Tunnel, Berlin

The secondary flow at the sidewalls (casing, hub) is causing the corner separation on the suction side of the vane which is responsible for losses and the decrease of the achievable pressure ratio in a compressor stage. By the use of methods of the high lift aerodynamics of airplanes it is possible to eliminate or at least to reduce the flow separation.

Liner-and Thermoacoustic-Test Rigs, Berlin

Several test rigs serving the investigation of acoustic damping and other thermoacoustic phenomena (like direct and indirect combustion noise and thermoacoustic instabilities). High accuracy model test rigs for fundamental research as well as applied test rigs with a wide operating range are available.

Transonic Cascade Tunnel Cologne

Der Prüfstand wird für grundlegende aerodynamische Untersuchungen an Profilen der Turbomaschine und für das Studium spezieller Strömungsphänomene eingesetzt. Er hat eine Messstrecke mit variablem Querschnitt von 168mm x 150-330mm und ermöglicht Anströmmachzahlen bis M1 = 1.4 mit einem sehr stabilen Betriebsverhalten ...

Turbine test facility NGTurb

The new turbine test facility at DLR in Göttingen, called Next Generation Turbine Test Facility (NG-Turb). Both capable of simulating the main flow parameters of future high-performance turbines (e.g. higher pressure ratios, more stages, extension to low pressure turbines etc.) and enough size to enable more detailed measurements during the experiments.

The Straight Cascade Tunnel Göttingen (EGG)

For the experimental and theoretical development of bladings for axial flow turbomachines the simulation of the two-dimensional flow field by a straight cascade is a very helpful and versatile tool. An infinitely long linear cascade is obtained by geometrically developing a cylindrical (blade-to-blade) intersection of the blade row into the plane. A real straight cascade, installed into a winndtunnel, consists of a finite number of profiles taken from that infinitely long linear cascade. The straight cascade tunnel at DLR Göttingen is of the blowdown type with atmospheric inlet.

The Rotating Cascade Tunnel Göttingen (RGG)

The DLR tunnel for rotating cascades was in particular designed and built for the testing of annular cascades for turbines in a wide range of parameters. Nevertheless an essential design goal was to create a facility which is as versatile as possible. Consequently it is now mostly used to investigate turbine stages.