Stall In Compressors Research Articles

Discussion: “Surge and Rotating Stall in Axial Flow Compressors—Parts I and II” (Greitzer, E. M., 1976, ASME J. Eng. Power, 98, pp. 190–211)

Discussion: “Surge and Rotating Stall in Axial Flow Compressors—Parts I and II” (Greitzer, E. M., 1976, ASME J. Eng. Power, 98, pp. 190–211)

Surge and Rotating Stall in Axial Flow Compressors—Part II: Experimental Results and Comparison With Theory

This paper reports an experimental study of axial compressor surge and rotating stall. The experiments were carried out using a three stage axial flow compressor. With the experimental facility the physical parameters of the compression system could be independently varied so that their influence on the transient system behavior can be clearly seen. In addition, a new data analysis procedure has been developed, using a plenum mass balance, which enables the instantaneous compressor mass flow to be accurately calculated. This information is coupled to the unsteady pressure measurements to provide the first detailed quantitative picture of instantaneous compressor operation during both surge and rotating stall transients. The experimental results are compared to a theoretical model of the transient system response. The theoretical criterion for predicting which mode of compression system instability, rotating stall or surge, will occur is in good accord with the data. The basic scaling concepts that have been developed for relating transient data at different corrected speeds and geometrical parameters are also verified. Finally, the model is shown to provide an adequate quantitative description of the motion of the compression system operating point during the transients that occur subsequent to the onset of axial compressor stall.

Surge and Rotating Stall in Axial Flow Compressors—Part I: Theoretical Compression System Model

This paper reports a theoretical study of axial compressor surge. A nonlinear model is developed to predict the transient response of a compression system subsequent to a perturbation from steady operating conditions. It is found that for the system investigated there is an important nondimensional parameter on which this response depends. Whether this parameter is above or below a critical value determines which mode of compressor instability, rotating stall or surge, will be encountered at the stall line. For values above the critical, the system will exhibit the large amplitude oscillatory behavior characteristic of surge; while for values below the critical it will move toward operation in rotating stall, at a substantially reduced flow rate and pressure ratio. Numerical results are presented to show the motion of the compression system operating point during these two basic modes of instability, and a physical explanation is given for the mechanism associated with the generation of surge cycle oscillations.

Closure to “Discussions of ‘Surge and Rotating Stall in Axial Flow Compressors—Parts I and II’” (1976, ASME J. Eng. Power, 98, pp. 212–216)

Closure to “Discussions of ‘Surge and Rotating Stall in Axial Flow Compressors—Parts I and II’” (1976, ASME J. Eng. Power, 98, pp. 212–216)

Discussion: “Surge and Rotating Stall in Axial Flow Compressors—Parts I and II” (Greitzer, E. M., 1976, ASME J. Eng. Power, 98, pp. 190–211)

Discussion: “Surge and Rotating Stall in Axial Flow Compressors—Parts I and II” (Greitzer, E. M., 1976, ASME J. Eng. Power, 98, pp. 190–211)

Discussion: “Surge and Rotating Stall in Axial Flow Compressors—Parts I and II” (Greitzer, E. M., 1976, ASME J. Eng. Power, 98, pp. 190–211)

Discussion: “Surge and Rotating Stall in Axial Flow Compressors—Parts I and II” (Greitzer, E. M., 1976, ASME J. Eng. Power, 98, pp. 190–211)

Prediction of Compressor Stall for Distorted and Undistorted Inlet Flow

A simulation technique is presented for the prediction of compressor stall for axial-flow compressors for clean and distorted inlet flow. The simulation is implemented on the digital computer and uses stage stacking and lumped-volume gas dynamics. The resulting nonlinear differential equations are linearized about a steady-state operating point, and a Routh-Hurwitz stability test is performed on the linear system matrix. Parallel compressor theory is utilized to extend the technique to the distorted inlet-flow problem. The method is applied to the eight-stage J85-13 compressor. Analytical stall prediction for the undistorted stall line shows good agreement with experimental results. The predicted stall line for distorted inlet flow is in agreement with experimental results only for large distortion extends and/or low distortion levels. Results for low distortion extents and high distortion level do not agree with experimental results.

Paper 17: Stage Matching, Stall, and Surge in Multi-Stage Axial Flow Compressors

Despite major advances in axial compressor theory and practice, the lack of a rational method of predicting surge limits remains as an outstanding deficiency. Accumulating experience suggests the association of surge initiation with local stalling phenomena, within the compressor, which are inadequately represented by conventional assumptions. A simple, revised model of stage matching under local stalling conditions is shown to provide a rational and consistent qualitative description of observed compressor off-design and surge initiation characteristics, and the effects on these of a variety of factors. Improved local stall criteria could provide the key to quantitative predictions of multi-stage compressor surge limits.

Rotating Stall in Multistage Axial Compressors : 2nd Report, Small Disturbance Theory 2

The effect of the axial distance is examined closely by the theory presented in the 1st report. A criterion whether the stall cells of a shorter or a longer wave length are likely to occur is derived. The results of calculations are compared with the experiments of many investigations and agree fairly well, although the linearizing assumptions are far from real in many cases. The effect of the axial distance found by G. Sovran is well predicted by this theory. The experiments conducted by one of the authors at the Aeronautical Research Institute also confirm these predictions.

Rotating Stall in Axial Flow Compressors

The classical theories of linearized aerodynamics yields a complete description of the flow field due to the rotating stall in a two-dimensional cascade of airfoils, when the extension of the stalled region is small. The corresponding physical scheme can be used for larger stalled regions, without the limitations of the linearizing assumptions, if no through flow is assumed through the stall zones. Experimental researches on a single rotor confirm the results of the theoretical calculations, where the mean radius section of the rotor is described by means of a two-dimensional model.

Closure to “Discussions of ‘Compressor Surge and Stall Propagation’” (1955, Trans. ASME, 77, pp. 467–469)

Closure to “Discussions of ‘Compressor Surge and Stall Propagation’” (1955, Trans. ASME, 77, pp. 467–469)

Experimental Investigations of Propagating Stall in Axial-Flow Compressors

Abstract Measurements of velocity fluctuations in stalled operation of an axial-flow compressor have demonstrated that stalling occurs for the most part in well-defined regions over the compressor annulus. These stalled regions rotate without changing shape in the direction of the blade rotation with a speed proportional to, but of smaller magnitude than, the rotor speed. Two principal types of propagating stall were observed, one with the stalled region or regions extending over part of the blade height, the other with a single stalled region over the full blade height.