Tip Gap Variation on a Transonic Rotor in the Presence of Tip Blowing

Guinet, Cyril; Streit, J. Anton; Kau, Hans-Peter; Gümmer, Volker

doi:10.1115/gt2014-25042

Cited by 15 publications

(10 citation statements)

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“…The casing treatment has proven its ability to enhance the stall margin of the rotor [15]. Running a model consisting of rotor and stator, almost no extension of the operating range can be achieved in the compressor stage.…”

Section: Discussionmentioning

confidence: 99%

Influence of a Tip Blowing Casing Treatment on the Stator Flow

Inzenhofer¹,

Hupfer²,

Guinet³

et al. 2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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In modern turbo machines, the stage loading in compressors is significantly increased to meet the power demand with enhanced efficiency. Casing treatments have proven to be effective in preventing stability issues that occur due to the high stage loading. Most numerical casing treatment studies cover only the rotor and neglect the stage behavior. However, the stage behavior is obviously impacted and the stator has to be redesigned if the rotor is treated.The present study investigates a 1.5 stage transonic and tip critical compressor. The stage was designed without a casing treatment. However, using a casing treatment now widely extend the operating range of the rotor, thus increasing its overall total pressure ratio. Therefore, the stator has also to cover a broader operating range. As the stator was not designed for this degree of throttling, surge is now triggered by the stator. In order to redesign the stator, the authors investigate the baseline stator to identify the reasons for failure and draw conclusions regarding the influence of the tip blowing casing treatment on the stator.The numerical investigation of the combined rotor and stator shows, on the one hand, the influence of the connecting interface on the compressor characteristic and the flow field. A model with a mixing plane interface is compared to a setup with a sliding plane interface. On the other hand, while using the circumferentially discrete interface, the influence of the tip blowing on the downstream stator is analyzed in depth. NomenclatureCT = casing treatment CTDI = CT duct inlet CTDO = CT duct outlet DP = design point operating condition MP = mixing plane NS = near stall operating condition PE = peak efficiency operating condition SC = smooth casing SM = stall margin SP = sliding plane TBCT = recirculating tip blowing casing treatment (U)RANS = (unsteady) Reynolds averaged Navier-Stokes (V)IGV = (variable) inlet guide vane [m 2 ] = flow area [J/(kgK)] = specific gas constant A.; Guinet, C.; Hupfer, A.; Schrapp, H.; Gümmer2 [K] = static temperature [m/s] = absolute flow velocity ̇ [kg/s] = mass flow ̇ [-] = corrected mass flow rate [Pa] = static pressure at stator inlet , [Pa] = total pressure at stator inlet , [Pa] = total pressure at stator exit , , [Pa] = total isentropic pressure at stator exit r [-] = radius, radial direction [m/s] = circumferential flow velocity [m/s] = velocity [m/s] = relative flow velocity x [-] = axial direction y + [-] = non-dimensional wall distance [°] = absolute flow angle [°] = absolute flow angle at stator leading edge − _ [°] = absolute flow angle of the SC-MP configuration at design point [°] = absolute flow angle at stator outlet [°] = relative flow angle [°] = relative flow angle at rotor inlet − _[°] = relative flow angle of the SC-MP configuration at design point [-] = circumferential direction [-] = total pressure ratio [-] = loss parameter − _[-] = loss of the SC-MP configuration at design point

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Section: Discussionmentioning

confidence: 99%

Influence of a Tip Blowing Casing Treatment on the Stator Flow

Inzenhofer¹,

Hupfer²,

Guinet³

et al. 2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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“…In general this type of casing treatment has proven its ability to enhance stall margin [16]. Losses provoked by the TBCT are in general relatively low.…”

Section: Discussionmentioning

confidence: 99%

“…Khaleghi et al [13] state in their study that small injection mass flows as 0.2% of total mass flow can already be very effective. The baseline configuration of the present study was found to be already effective with a mass flow rate of 0.4% at near stall conditions [16]. Weichert et al investigated the possibility of self-regulation of the recirculating mass flow rate for a low speed rig.…”

Section: Introductionmentioning

confidence: 94%

Parametric Study of the Bleed Position in a Tip Blowing Casing Treatment

Guinet¹,

Bettrich²,

Gümmer³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Stability issues are often restricting the design space of axial-flow compressors. Casing treatments have shown the ability to enhance stability on existing designs in a late design phase. Prior studies have identified the positioning of the casing treatment as an important parameter for both stability and overall efficiency. Particularly for axial casing treatments, the downstream position of the fluid removal was found to be relevant. Within the present study the focus is put on a tip blowing casing treatment consisting of an axially and circumferentially discrete bleed port connected to an upstream injection port. For this kind of casing treatment, an accurate positioning of the fluid removal has high importance. Therefore, in the present study a parametric variation of the bleed port's axial position is carried out at design speed. Minimizing losses at sufficient stall margin improvement requires recirculation mass flows dependent on operating point. In support of that goal of mass flow self-regulation criteria for the fluid removal port position are derived. The analysis of the flow field, of the pressure distribution and of the shock-vortex-interaction help to identify an ideal position. The study is carried out on the isolated rotor of a 1.5 stage research compressor arrangement. NomenclatureCT = casing treatment TBCT = recirculating tip blowing CT CSCT = circumferential-slot CT ASCT = axial-slot CT CTDI = CT duct inlet CTDO = CT duct outlet SC = smooth casing DP = design point operating condition PE = peak efficiency operating condition NS = near stall operating condition SM = stall margin (V)IGV = (variable) inlet guide vane (U)RANS = (unsteady) reynolds averaged navier-stokes y + [-] = non-dimensional wall distance [Pa] = static pressure [Pa] = total pressure ̇ [ / ] = recirculation mass flow rate Π [-] = total pressure ratio [K] = total temperature Ma [-] = Mach number [-] = heat capacity ratio [m²] = nozzle cross section R [J/kg/K] = gas constant Downloaded by UNIVERSITY OF QUEENSLAND on July 30, 2015 | http://arc.aiaa.org |

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“…Resulting from this work, a recirculation passage geometry similar to that described by Guinet et al [14,15] has been designed and simulated. Design features of the passage are currently under URANS investigation by the authors and are providing early evidence of a significant increase in stall margin.…”

Section: Conclusion and Discussionmentioning

confidence: 99%

Pathways to Improved Aerodynamic Design

Page¹,

Hield²,

Mantell³

et al. 2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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Abstract. Large-scale unsteady graphical processor unit (GPU) based calculations are used to study the flow in realistic transonic fan geometries and shown to produce useful insights into the complex unsteady flow physics in systems of practical engineering relevance. Inlet flow distortion produces complex flow patterns which can significantly reduce stall margin. In order to design efficient, well targeted fan stabilizing technologies, it is essential to gain understanding into which specific features of distorted flow patterns are important in causing instability.In this paper, the use of large-scale, high-fidelity 3D unsteady Reynolds-Averaged Navier Stokes (URANS) calculations with sliding planes is shown to allow the isolation of a wide range of inlet distortion features and a high throughput of calculations is achieved. This facilitates a comprehensive investigation into stall margin loss and the observation of complex instability processes, which is in turn used to support the development of specialized design solutions. The costs of simulations and turnaround times are given. The potential for mixed fidelity simulations, in particular mixing one-dimensional low order models and large eddy type simulations to generate inlet conditions, is discussed. 7544Figure 1: Aerospace airframe and propulsion technology under development.

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Tip Gap Variation on a Transonic Rotor in the Presence of Tip Blowing

Cited by 15 publications

References 0 publications

Influence of a Tip Blowing Casing Treatment on the Stator Flow

Influence of a Tip Blowing Casing Treatment on the Stator Flow

Parametric Study of the Bleed Position in a Tip Blowing Casing Treatment

Pathways to Improved Aerodynamic Design

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