Abstract
This paper experimentally investigates a highly-loaded 1.5-stage transonic axial compressor, which comprises a variable inlet guide vane, a BLISK rotor, and a variable stator in tandem arrangement. A detailed comparison between the newly designed compressor stage and a reference stage with a conventional stator design was conducted by using extensive instrumentation. Thus, steady and unsteady phenomena—focusing on the aerodynamic and aeroelastic behavior—were analyzed. Due to the new stator vane design, a higher aerodynamic stator vane loading was pursued, while the vane count was reduced. This, in turn, allowed a rotor design with an increased work coefficient. This experimental study revealed several effects of the optimized compressor stage in terms of both performance and the corresponding aerodynamics, as well as the aeroelastic behavior.
Highlights
Future aero engines face the environmental challenge of drastically reducing greenhouse gases
The reduced mass flows for the respective operating points near the choking limit and at the peak efficiency (PE) operating points matched for both configurations
The outcomes of the experimental investigations conducted here can be split into two parts
Summary
Future aero engines face the environmental challenge of drastically reducing greenhouse gases. Politically defined regulations regarding emissions are becoming increasingly important. To achieve these regulations, novel approaches in technology development are inevitably necessary. The development trends of aero engines aim for opportunities to increase efficiency in conjunction with reduced weight and size. The axial core compressor offers great potential by increasing the overall pressure ratio with a minimum number of compressor stages, as well as reduced blade and vane counts. This results in highly-loaded compressor stages that are prone to flow separation. The work coefficient of the rotor can be increased which leads to an optimized stage loading
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: International Journal of Turbomachinery, Propulsion and Power
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
