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

Guinet, Cyril; Bettrich, Valentin; Gümmer, Volker

doi:10.2514/6.2014-3441

Cited by 6 publications

(5 citation statements)

References 13 publications

(20 reference statements)

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“…Implementing a so-called tip blowing casing treatment (TBCT) gives the opportunity of tip blowing including the advantages of recycling low momentum flow after the passage shock, as investigations by Guinet et al [1] have shown. The injected air in front of the leading edge (CT duct inlet) is extracted after the passage shock (CT duct outlet).…”

Section: Introductionmentioning

confidence: 98%

“…As the pressure-driven tip leakage flow has a strong impact on the secondary flow phenomena, instabilities increase towards rising blade loading as well as for an increasing tip clearance. The tip leakage causes endwall blockage, which interacts with the main flow and develops into the tip leakage vortex, as depicted by Guinet et al [1]. The interaction of this vortex with the passage shock wave is one reason for the vortex growth towards operating points at strongly reduced corrected mass flow rate, as depicted by Cumpsty [2].…”

Section: Introductionmentioning

confidence: 98%

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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: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 98%

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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“…The self-recirculating passage, taking advantage of the pressure difference in rotor passage, suctions the fluid downstream of the rotor and jets this part of the fluid upstream of the rotor. Guinet et al 22 made efforts to explore the impact of the location of the bleed port. The results demonstrated that the bleed port at 28% axial chord length achieved effective stability expansion under the condition of minimal impact on performance.…”

Section: Introductionmentioning

confidence: 99%

Impact of the ending position of controllable speed casing on the flow stability in a transonic compressor rotor

Zhao

Zhong

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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The structure of casing treatment has a significant influence on the stability expansion effect. The ending position of the rotatable ring is one of the important structural parameters in the controllable speed casing. The impact of ending position of the rotatable ring rotating at the same speed as the rotor on the stability expansion and stability expansion mechanism was studied in this paper. The results show that, when the ending position of rotatable ring expands downstream in the range of 20% to 60% axial chord length, because of the improvement in the tip leakage vortex trajectory and main flow/leakage flow interface, the stability expansion effect rises gradually. The further downstream expansion of ending position from 60% axial chord length, however, has a slight impact on tip flow, bringing out a steady stability expansion effect around 52.5%. The best stability expansion effect of ending position occurs at 60% axial chord length where the stable operating margin increases by 53.5%.

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“…However, CFD studies often focus on aircraft engines configurations, such as Refs [5] [6] [7] [8] [9].…”

Section: Introductionmentioning

confidence: 99%

“…The bleeding of air from the compressor of a jet engine, operating at high load, is proven to reduce the adverse effects of secondary flows. These include tip leakage vortex or blockage generation, aligning the vortex trajectory with the flow, thus extending the surge margin [8] [9]. Benefits pointed out in those studies originate from the passage boundary layer ingestion that contributes to the reduction of losses.…”

Section: Introductionmentioning

confidence: 99%