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Stall Warning Indicator

Ref-Nr: TA-16060 / TUB


The invention enables the prediction of instability in a compressor, which allows an early warning in the event of a fault. The early warning system can be used in thermal turbomachinery, for example in aircraft engines.


Performance data of newly developed compressors are so far Measured on a test bench and then Transferred to a characteristic diagram. An essential component of seeking a characteristic field is the so-called surge limit, since this is essential for Ensuring safe operation.

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Exceeding the surge limit will result in instabilities, Causing extremely high aerodynamic loads to the compressor did may result in Considerable structural damages. HOWEVER, since the surge line on the test bench can only be Identified if it has already been exceeded, so far costly complete failures of the tested compressors are accepted.

It is THUS to object of the Invention to Provide a method for deterministic mining of indicator for a prediction of instabilities in a compressor, Which Allows Reliably on early warning of the possible occurrence seeking instabilities, love especially the achievement of the surge limit.


The method developed by scientists from the institute of Aerospace Engineering is an early warning system for compressor instabilities. .According to this method the compressor on a test bench is Gradually been moved to its surge limit. During this process high-resolution pressure measurement is Performed and the collected data can be used to calculate a specific integral parameters.

If this parameter is afterwards subsequently Plotted over all Measured operating points, one can obtain a secure Possibility of Predicting the operating limit and THUS the surge limit, enabling a due detection of instabilities burner

Functionality and potential of the novel method as stall warning algorithm where successfully Investigated using a newly built miniature single-stage low speed axial compressor.


  • Determining the surge line without exceeding it --> non-destructive measurement
  • Disturbances can be CLEARLY Identified and quantified
  • Indication of last stable operating point before potential stall possible


The method can be Applied to thermal turbo machines: such as axial or radial compressors, whereby axial compressors represent a central component in aircraft engines.


Possible cooperation:

  • R & D Cooperation
  • Patent Sale
  • Licensing

Technische Universität Berlin

Jeanne Trommer
+49 30 314 75916
Fraunhoferstr. 33-36
10587 Berlin




  • PCT anhängig
  • DE erteilt


algorithm, axial compressor stall, early warning system, method, rotating instabilities, stall inception, stall indicator

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