Flow Distributions and Discharge Coefficient Effects for Jet Array Impingement With Initial Crossflow

Florschuetz, L. W.; Isoda, Yoshitaka

doi:10.1115/1.3227415

Cited by 36 publications

(8 citation statements)

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“…6). Nonetheless, Florschuetz and Isoda (1983) have shown that for AP/P < 0.20-0.30 this procedure gives pressure loss predictions in excellent agreement with experiments; this assurance suffices the scope of this work, because situations requiring higher pressure drops have little practical applications in gas turbine cooling. 3.7 Typical gas turbine conditions Tab.…”

Section: Pressure Dropssupporting

confidence: 52%

“…12). - Florschuetz and Isoda (1983) and Florschuetz, Metzger and Su (1984) analyzed the effects of non-zero initial crossflow, a situation corresponding to the midchord region, where jets are crossed by spent flow coming from the leading edge ( Fig. 2).…”

Section: Literature Surveymentioning

confidence: 99%

“…The relaxation of these simplifying assumptions prevents from attaining an analytical solution. The case with friction and variable C D has been solved numerically and tested experimentally by Florschuetz and Isoda (1983), who showed that: -Viscous effects become significant only when the initial crossflow is of the same order of total jet flow. For the scheme of Fig.…”

Section: Flow Distributionmentioning

confidence: 99%

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Cooling Flow Prediction for Fully Impingement Cooled Gas Turbine Blades

Consonni

1995

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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This paper presents a one-dimensional model to calculate the cooling flow of fully impingement cooled blades. The coolant is assumed to be ejected through a jet array running along the whole blade chord, with crossflow in the blade-to-blade plane from the leading edge toward the trailing edge. The simplicity of this cooling scheme translates to analytic formulations highlighting the peculiarities of impingement and the influence of geometric and fluid-dynamic parameters. Results show that the coolant flow required to maintain the blade surface under a given maximum temperature varies strongly with the jet-to-jet spacing, while the jet-to-wall gap mainly affects pressure losses. Compared to other types of convection, impingement does not afford reductions of cooling flow nor pressure losses: the basic benefits are the capability to achieve high local heat transfer coefficients and more uniform temperature distributions. Since the cooling schemes of actual gas turbine blades are substantially more complex — an elaborate combination of convection, impingement and film cooling — the present model cannot be used to predict the cooling flow required by actual engines. Nonetheless, it can give quantitative indications on the potential of impingement and help the selection of impingement array geometry.

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Section: Pressure Dropssupporting

confidence: 52%

Section: Literature Surveymentioning

confidence: 99%

Section: Flow Distributionmentioning

confidence: 99%

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Cooling Flow Prediction for Fully Impingement Cooled Gas Turbine Blades

Consonni

1995

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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“…An explanation for this type of behavior was originally presented in some detail in connection with noninitial crossflow test x/L Fig. 12 Effect of initial crossflow on jet array flow distribution for B(5,8,3)I geometry -experimental data compared with predictive model [12].…”

Section: Resultsmentioning

confidence: 99%

Heat Transfer Characteristics for Jet Array Impingement With Initial Crossflow

Florschuetz

Metzger

1983

Volume 4: Heat Transfer; Electric Power

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Two-dimensional arrays of circular air jets impinging on a heat transfer surface parallel to the jet orifice plate are considered. The jet flow, after impingement, is constrained to exit in a single direction along the channel formed by the jet orifice plate and the heat transfer surface. In addition to the crossflow which originates from the jets following impingement, an initial crossflow is present which approaches the array through an upstream extension of the channel. The temperature of the initial crossflow air may differ from the jet air temperature. The configurations considered are intended to model the impingement cooled midchord region of gas turbine airfoils in cases where an initial crossflow is also present. Nusselt numbers and dimensionless adiabatic wall temperatures resolved to one streamwise jet hole spacing were experimentally determined for ratios of the initial crossflow rate to the total jet flow rate ranging from zero to unity. These are presented and discussed relative to the flow and geometric parameters.

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“…Outputs revealed that the previous numerical results had a good agreement with the experimental data at a low range of Reynolds numbers. Florschuetz et al [8][9][10] performed experimental work and theoretical analysis to study the effect of heat transfer performance for nozzle array impingement with the cross-flow on a flat test plate. The results confirmed that the crossflow decreased the performance of heat transfer.…”

Section: Introductionmentioning

confidence: 99%

Optimization of A Swirl with Impingement Compound Cooling Unit for A Gas Turbine Blade Leading Edge

et al. 2020

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In this article, a compound unit of swirl and impingement cooling techniques is designed to study the performance of flow and heat transfer using multi-conical nozzles in a leading-edge of a gas turbine blade. Reynolds Averaged Navier-Stokes equations and the Shear Stress Transport model are numerically solved under different nozzle Reynolds numbers and temperature ratios. Results indicated that the compound cooling unit could achieve a 99.7% increase in heat transfer enhancement by increasing the nozzle Reynolds number from 10,000 to 25,000 at a constant temperature ratio. Also, there is an 11% increase in the overall Nusselt number when the temperature ratio increases from 0.65 to 0.95 at identical nozzle Reynolds number. At 10,000 and 15,000 of nozzle Reynolds numbers, the compound cooling unit achieves 47.9% and 39.8% increases and 63.5% and 66.3% increases in the overall Nusselt number comparing with the available experimental swirl and impingement models, respectively. A correlation for the overall Nusselt number is derived as a function of nozzle Reynolds number and temperature ratio to optimize the results. The current study concluded that the extremely high zones and uniform distribution of heat transfer are perfectly achieved with regard to the characteristics of heat transfer of the compound cooling unit.

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Flow Distributions and Discharge Coefficient Effects for Jet Array Impingement With Initial Crossflow

Cited by 36 publications

References 0 publications

Cooling Flow Prediction for Fully Impingement Cooled Gas Turbine Blades

Cooling Flow Prediction for Fully Impingement Cooled Gas Turbine Blades

Heat Transfer Characteristics for Jet Array Impingement With Initial Crossflow

Optimization of A Swirl with Impingement Compound Cooling Unit for A Gas Turbine Blade Leading Edge

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