Flow in a Rotating Cavity With Axial Throughflow at Engine Representative Conditions

Atkins, Nicholas R.; Kanjirakkad, Vasudevan

doi:10.1115/gt2014-27174

Cited by 43 publications

(69 citation statements)

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“…The results also show that the value of N is not only a function of a/b but there are other parameters such as the axial and rotational Reynolds numbers that should be considered. The unsteady and unstable nature of the flow structure within the cavity was also observed and stated by various researchers including [ (Atkins & Kanjirakkad, 2014), (King , et al, 2005), (Tian, et al, 2004)].…”

Section: Numerical Resultsmentioning

confidence: 75%

“…The above authors also showed that despite the unstable and evolutionary nature of the complicated flow pattern, the free convection correlations for a vertical flat plate with constant temperature gives an encouraging prediction for the global Nusselt number values for the buoyancy-induced flow (Dweik, et al, 2009a). Atkins and Kanjirakkad (Atkins & Kanjirakkad, 2014) conducted measurements in the same multiple cavity rig as (Alexiou, 2000;Long, et al, 2007) but this time with a stationary shaft and the direction of flow through the rig reversed compared to the previous builds. Additionally, in these experiments the shroud was radiantly heated.…”

Section: Introductionmentioning

confidence: 91%

“…The nominal diameter of the thermocouple beads is 0.4 mm. The installation procedure is described in Atkins and Kanjirakkad (Atkins & Kanjirakkad, 2014). The shaft air thermocouples are positioned at r/b = 0.25.…”

Section: Figure 4: Cross-sectional View Of the Mcrmentioning

confidence: 99%

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Experimental and Computational Investigation of Flow Structure of Buoyancy Induced Flow in Heated Rotating Cavities

Fazeli¹,

Kanjirakkad²,

Long³

2020

Proceedings of Global Power &Amp; Propulsion Society

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This paper presents Laser-Doppler Anemometry (LDA) measurements obtained from the Sussex Multiple Cavity test facility. This facility comprises a number of heated disc cavities with a cool bore flow and is intended to emulate the secondary air system flow in an H.P compressor. Measurements were made of the axial and tangential components of velocity over the respective range of Rossby, Rotational and Axial Reynolds numbers, (Ro, Re θ and Re z), 0.32 < Ro < 1.28, Re θ = 7.1 × 10 5 , 1.2 × 10 4 < Re z < 4.8 × 10 4 and for the values of the buoyancy parameter (β∆T) : 0.50 < β∆T < 0.58. The frequency spectra analysis of the tangential velocity indicates the existence of pairs of vortices inside the cavities. The swirl number, X k , calculated from these measurements show that the cavity fluid approaches solid body rotation near the shroud region. The paper also presents results from Unsteady Reynolds-Averaged Navier-Stokes (URANS) calculations for the test case where Ro = 0.64. The time-averaged LDA data and numerical results show encouraging agreement.

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Section: Numerical Resultsmentioning

confidence: 75%

Section: Introductionmentioning

confidence: 91%

See 1 more Smart Citation

Experimental and Computational Investigation of Flow Structure of Buoyancy Induced Flow in Heated Rotating Cavities

Fazeli¹,

Kanjirakkad²,

Long³

2020

Proceedings of Global Power &Amp; Propulsion Society

Self Cite

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show abstract

“…(Apart from those on the cob surfaces, the differences between the two sets of temperature were smaller than the uncertainty in the measured values.) Table 1 shows the main parameters and average Nusselt numbers for the 19 test cases of Atkins and Kanjirakkad [12]. For each of the four approximate Rossby numbers, the cases are presented in order of ascending Grashof number.…”

Section: Experimentally Derived Nusselt Numbers and Disc Temperaturesmentioning

confidence: 99%

“…The geometry of the disc, which is shown in Figure 6, is based on the experimental Sussex rig described in [12]. The thermal conductivity, , of the titanium disc and the finite-difference equations used for the numerical solution of Equation (33) are given in [4].…”

Section: Modelled Disc Temperaturesmentioning

confidence: 99%

Buoyancy-Induced Heat Transfer inside Compressor Rotors: Overview of Theoretical Models

2018

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Increasing pressures in gas-turbine compressors, particularly in aeroengines where the pressure ratios can be above 50:1, require smaller compressor blades and an increasing focus on blade-clearance control. The blade clearance depends on the radial growth of the compressor discs, which in turn depends on the temperature and stress in the discs. As the flow inside the disc cavities is buoyancy-driven, calculation of the disc temperature is a conjugate problem: the heat transfer from the disc is coupled with the air temperature inside the cavity. The flow inside the cavity is three-dimensional, unsteady and unstable, so computational fluid dynamics is not only expensive and time-consuming, it is also unable to achieve accurate solutions at the high Grashof numbers found in modern compressors. Many designers rely on empirical equations based on inappropriate physical models, and recently the authors have produced a series of papers on physically-based theoretical modelling of buoyancy-induced heat transfer in the rotating cavities found inside compressor rotors. Predictions from these models, all of which are for laminar flow, have been validated using measurements made in open and closed compressor rigs for a range of flow parameters representative of those found inside compressor rotors. (The fact that laminar buoyancy models can be used for large Grashof numbers (up to 10 12 ), where most engineers expect the flow to be turbulent, is attributed to the large Coriolis accelerations in the fluid core and to the fact that there is only a small difference between the rotational speed of the core and that of the discs.) As many as 223 separate tests were analysed in the validation of the models, and good agreement between the predictions and measurements was achieved for most of these cases. This overview paper has collected together the equations from these papers, which should be helpful to designers and research workers. The paper also points out the limitations of the models, all of which are for steady flow, and shows where further experimental evidence is needed.

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Thermal Impact of Rotational Reynolds Number on Aircraft Engine Compressor Disks

Ahmed

Reddy

Venkatesh

2022

Trans Indian Natl. Acad. Eng.

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Flow in a Rotating Cavity With Axial Throughflow at Engine Representative Conditions

Cited by 43 publications

References 0 publications

Experimental and Computational Investigation of Flow Structure of Buoyancy Induced Flow in Heated Rotating Cavities

Experimental and Computational Investigation of Flow Structure of Buoyancy Induced Flow in Heated Rotating Cavities

Buoyancy-Induced Heat Transfer inside Compressor Rotors: Overview of Theoretical Models

Thermal Impact of Rotational Reynolds Number on Aircraft Engine Compressor Disks

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