Tran­son­ic cas­cade wind tun­nel TGK

Compressor cascade in the mirror of the Schlieren optics
Com­pres­sor cas­cade in the mir­ror of the Schlieren op­tics
Image 1/2, Credit: DLR (CC-BY 3.0)

Compressor cascade in the mirror of the Schlieren optics

Com­pres­sor cas­cade in the mir­ror of the Schlieren op­tics
Transsonisches Versuchsgitter
Tran­son­ic com­pres­sor cas­cade
Image 2/2, Credit: DLR (CC-BY 3.0)

Transonic compressor cascade

Tran­son­ic com­pres­sor cas­cade

The transonic cascade wind tunnel (TGK) is installed at the DLR Institute of Propulsion Technology in Cologne. This large-scale facility is used for investigations on compressor blade cascades; it is the world‘s only such facility that allows inflow Mach numbers of up to 1.4, whilst simultaneously enabling independent variation of the Reynolds number.

The TGK at DLR is also unique due to its extremely stable test conditions, especially at the speed of sound. Among other things, this is made possible by the continuous closed-loop operation of the tunnel. In addition, the aerodynamic load (AVDR) acting on the investigated cascades can be controlled with great precision due to the high extraction capacities.

Aerodynamics of compressor blade cascades

The TGK is used for fundamental research into the aerodynamics of compressor blade cascades. It enables the assessment of the load and loss behaviour of the cascades. Due to its excellent accessibility for measurements, the TGK is used to test prototypes of new measurement methods. In addition, the facility can generate highly precise experimental data that is used for the validation of numerical simulations.

Due to its focus on fundamental research, the TGK serves as a link between theoretical research findings and their applications. Such applications include highly complex, experimental testing currently being completed on a rotating compressor rig at the Multistage Two Shaft Compressor Test Facility in Cologne. The facility enables the performance of highly precise, detailed measurements of individual flow phenomena, thus allowing a more profound analysis of flow effects.

Contact
  • Dr.–Ing. Alexander Hergt
    Ger­man Aerospace Cen­ter (DLR)
    DLR In­sti­tute of Propul­sion Tech­nol­o­gy
    Fan and Com­pres­sor

Cookies help us to provide our services. By using our website you agree that we can use cookies. Read more about our Privacy Policy and visit the following link: Privacy Policy

Main menu