Experimental and Numerical Investigations of Rotating Instability Phenomenon in An Axial Compressor Stator

Beselt, Christian; Rennings, Ruben van; Thiele, Frank; Peitsch, Dieter

doi:10.2514/6.2012-2980

Cited by 6 publications

(5 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…At this operating point, the peak efficiency was determined in earlier investigations [17,19,20]. With increasing incidence this position moves upstream.…”

Section: Surface Static Pressure Distributionmentioning

confidence: 83%

See 1 more Smart Citation

Three-Dimensional Flow Field in Highly Loaded Compressor Cascade

Beselt

Eck

Peitsch

2014

Journal of Turbomachinery

View full text Add to dashboard Cite

Within the present paper, a detailed experimental investigation is presented. The influence of blade loading on the development and interaction of secondary flow structures within an annular compressor stator cascade (CSC) is examined. Experimental results at 3% chord hub clearance were obtained at four different blade loadings. Included are blade and endwall flow visualization, time resolved measurements of the static pressure on the endwall and radial-circumferential hot-wire traverse measurements within the passage as well as five-hole probe traverse measurements at the inlet and the outlet of the passage. The experimentally obtained results give detailed insight on the effect of the incidence on the development and interaction of the clearance vortex, horseshoe vortex, and the passage vortex. Furthermore, it will be shown that a vortex breakdown of the clearance vortex occurs at higher loadings.

show abstract

“…At this operating point, the peak efficiency was determined in earlier investigations [17,19,20]. With increasing incidence this position moves upstream.…”

Section: Surface Static Pressure Distributionmentioning

confidence: 83%

“…in detail in earlier publications, such as Beselt et al [17,18], Beselt and Peitsch [19,20], and Pardowitz et al [21,22]. The test rig was designed as a hub loaded stator to achieve similar flow conditions on the hub of the stator as on a rotor tip.…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Flow Field in Highly Loaded Compressor Cascade

Beselt

Eck

Peitsch

2014

Journal of Turbomachinery

View full text Add to dashboard Cite

show abstract

“…A1a, f = 217Hz, λ = 360 • , and θ = 77 • in the Ref. 20 so that the following modal estimation results can be calculated according to the equation (5) to (7). Figure A2 shows the Fourier spectrum results of the pressure signal monitored by the sensor installed along the chordwise on the tip of the rear rotor.…”

Section: Appendixmentioning

confidence: 99%

“…Subsequently, Inoue et al (6) observed the early premature of the stall by installing a high-frequency response pressure sensor on the casing of an axial-flow isolated rotor. The disturbance occurred when the flow rate is higher than the stall point, and it happened only in the large tip or hub clearance (7) situations. The phenomenon is rotating instability.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of rotating instability in a contra-rotating axial flow compressor

et al. 2021

View full text Add to dashboard Cite

The rotating instability in a contra-rotating axial flow compressor is investigated by experiments. Twenty-four pressure sensors were installed on the casing to capture the unsteady flow in the rotor tip region simultaneously. A double-phase-locking technique suitable for the contra-rotating compressor was proposed to characterise the static pressure contours of the rotor tip. The mean and root-mean-square pressure contours indicate that rotating instability occurs before the rotating stall happened, and the rotor tip clearance vortex is located upstream of the rear rotor leading edge plane before stall. Fourier spectrum shows that rotating instability and rotating stall both happened under the stall condition, and the frequency band of rotating instability does not change with the flow rate. In the front rotor, the frequency of rotating instability is half of the blade passing frequency. It is verified that the modal estimation method can be implemented by using the average azimuthal phase velocity, which significantly reduced the number of pressure sensors required. Modal estimation results show that each peak of the rotating instability frequency band corresponds to a unique dominant circumferential mode. By optimising average azimuthal phase velocity, an improved modal estimation method is obtained, which can further improve the reliability of the modal estimation results.

show abstract

“…All of which concentrate on comprehending the complex secondary flow phenomena within the CSC. For this purpose different measurement techniques comprising oil flow visualization, five-hole probe measurements, hotwire measurements and time-resolved static pressure measurements on the side walls have been carried out (Beselt et al 2012(Beselt et al , 2013a(Beselt et al , b, 2014Pardowitz et al 2012aPardowitz et al , 2013Pardowitz et al , 2015Peter et al 2017). A detailed description of the inlet flow conditions to the CSC is provided by .…”

Section: Test Sectionmentioning

confidence: 99%

Advanced application of a sublayer fence probe in highly instationary turbomachinery flows: observations on prestall instabilities

Eck¹,

Rückert²,

Peitsch³

2019

Exp Fluids

Self Cite

View full text Add to dashboard Cite

The present paper introduces a novel approach for measuring near wall flow velocities by utilizing a sublayer surface fence probe. Hereby, a difference in static pressure builds up over a microscopic obstacle within the viscous sublayer. An analytical model of the angular dependent pressure difference is employed to derive information about the flow direction. Furthermore, a computational preston tube approach has been used to calibrate the surface fence probe with regard to a flow velocity to be assigned to half of the fence height. Through the use of a sophisticated analyzing algorithm the flow direction and its velocity can be determined as a function of time. As a proof of concept measurements were conducted within the radial gap of an annular compressor rig yielding both mean and time resolved near wall flow fields. Former are in very good compliance with oil flow visualizations proving the methods accuracy. The experimental results give unprecedented insights into an unsteady flow phenomenon that arises when an axial compressor is operating close to its stalling limit. The presented technique allows for investigating turbomachinery areas which formerly were observable only by computational means.

show abstract

Experimental and Numerical Investigations of Rotating Instability Phenomenon in An Axial Compressor Stator

Cited by 6 publications

References 16 publications

Three-Dimensional Flow Field in Highly Loaded Compressor Cascade

Three-Dimensional Flow Field in Highly Loaded Compressor Cascade

Experimental investigation of rotating instability in a contra-rotating axial flow compressor

Advanced application of a sublayer fence probe in highly instationary turbomachinery flows: observations on prestall instabilities

Contact Info

Product

Resources

About