Mach Number, Reynolds Number, Jet Spacing Variations: Full Array of Impinging Jets

Goodro, Matt; Ligrani, Phil; Fox, Michael; Moon, Hee Koo

doi:10.2514/1.44029

Cited by 31 publications

(27 citation statements)

References 23 publications

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“…Quite interesting results on jet array impingement systems have been recently pointed out by Goodro and coworkers [12][13][14][15][16]. The authors reveal that the holes' discharge coefficient is affected by both jet Reynolds and Mach number.…”

Section: Introductionmentioning

confidence: 89%

Numerical Characterization of Pressure Drop Across the Manifold of Turbine Casing Cooling System

Soghe

Andreini

2012

Volume 4: Heat Transfer, Parts a and B

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An array of jets is an arrangement typically used to cool several gas turbine parts. Some examples of such applications can be found in the impingement cooling systems of turbine blades and vanes or in the turbine blade tip clearances control of large aero-engines. In order to correctly evaluate the impinging jet mass flow rate, the characterization of holes discharge coefficient is a compulsory activity. In a previous work, the authors have performed an aerodynamic analysis of different arrays of jets for active clearance control; the aim was the definition of a correlation for the discharge coefficient (C d ) of a generic hole of the array. The developed empirical correlation expresses the (C d ) of each hole as a function of the ratio between the hole and the manifold mass velocity and the local value of the pressure ratio. In its original form, the correlation does not take in to account the effect of the hole length to diameter ratio (t/d) so, in the present contribution, the authors report a study with the aim of evaluating the influence of such parameter on the discharge coefficient distribution. The data were taken from a set of CFD RANS simulations, in which the behavior of the cooling system was investigated over a wide range of fluid-dynamics conditions (pressure-ratio ¼ 1.01-1.6, t/d ¼ 0.25-3). To point out the reliability of the CFD analysis, some comparisons with experimental data were drawn. An in depth analysis of the numerical data set has led to an improved correlation with a new term function of the hole length to diameter ratio.

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Section: Introductionmentioning

confidence: 89%

Numerical Characterization of Pressure Drop Across the Manifold of Turbine Casing Cooling System

Soghe

Andreini

2012

Volume 4: Heat Transfer, Parts a and B

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“…For the lower Reynolds numbers investigated, a New York Blower Co. 7.5 HP, size 1808 pressure blower is employed. For higher Reynolds numbers, a DRUM Industries, 50 HP, D807 Figure 1: Impingement investigations experimental facility [33][34][35][36][37][38][39][40][41][42]. (a) Component arrangement for Mach number, Reynolds number, and hole spacing investigations.…”

Section: Impingement Flow Facility and Impingement Array Platesmentioning

confidence: 99%

“…A Bonneville crossfl ow heat exchanger is located within the plenum, which is farther downstream. As the air exits the heat exchanger, and the second plenum, the air passes into a 0.22 m outer diameter pipe, which contains the ASME Standard orifi ce plate employed to measure the air mass fl ow rate [33][34][35][36][37][38][39][40][41][42]. This pipe then connects to the 0.635 × 0.635 m side of a plenum, as shown in Fig.…”

Section: Impingement Flow Facility and Impingement Array Platesmentioning

confidence: 99%

“…Individual plates with holes used to produce the impingement jets are located at the bottom of this plenum, as shown in Fig. 2 [33][34][35][36][37][38][39][40][41][42]. The plenum is thus designed so that different impingement plates can be installed at this location using a 9.5 mm thick polyurethane gasket and ¼ in SAE J429 Grade 5 bolts.…”

Section: Impingement Flow Facility and Impingement Array Platesmentioning

confidence: 99%

“…The plenum is thus designed so that different impingement plates can be installed at this location using a 9.5 mm thick polyurethane gasket and ¼ in SAE J429 Grade 5 bolts. Figure 3 shows the test plate confi gurations, which are employed [37]. Here, each impingement plate is arranged with multiple rows of holes in the streamwise direction, arranged so that holes in adjacent rows are staggered with respect to each other.…”

Section: Impingement Flow Facility and Impingement Array Platesmentioning

confidence: 99%

See 2 more Smart Citations

Recent Developments in Impingement Array Cooling, Including Consideration of the Separate Effects of Mach Number, Reynolds Number, Temperature Ratio, Hole Spacing, and Jet-to-Target-Plate Distance

Ligrani

2014

Impingement Jet Cooling in Gas Turbines

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Presented are data that illustrate the effects of Mach number, Reynolds number, temperature ratio, hole spacing, and jet-to-target-plate distance on surface Nusselt numbers produced by an array of jets impinging on a fl at plate. The local and spatially averaged Nusselt numbers, and local and spatially averaged recovery factors are unique because: (i) data are obtained at constant Reynolds number as the Mach number is varied, and at constant Mach number as the Reynolds number is varied, (ii) data are obtained at constant Reynolds number and constant Mach number, as the temperature ratio is varied, (iii) data are obtained at constant temperature ratio, Mach number, and Reynolds number, as the impingement hole spacing is varied, (iv) data are obtained as the jet-to-target-plate distance is varied as Reynolds number, Mach number, hole spacing, and temperature ratio are constant, and (v) data are given for jet impingement Mach numbers up to 0.74, and for Reynolds numbers up to 60,000. Also included are crossfl ow-to-jet mass velocity ratio data and discharge coeffi cient data. Impingement hole spacings are 5D, 8D, and 12D in the streamwise and spanwise directions, with jet-to-target-plate distances of 1.5D, 3D, 5D, and 8D. Local spatially resolved and spatially averaged Nusselt numbers, measured using infrared thermography and energy balance techniques, show strong dependence on the impingement jet Reynolds number for each situation as the jet Mach number is maintained constant. Nusselt numbers show negligible variations with Mach number, between Ma = 0.1 and 0.2, however, data taken at Mach numbers greater than approximately 0.25 (as the Reynolds number is held constant)

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Investigation of the Conjugate Heat Transfer and Flow Field for a Flat Plate with Combined Film and Impingement Cooling

Cao

Zhang³

et al. 2020

J. Therm. Sci.

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Mach Number, Reynolds Number, Jet Spacing Variations: Full Array of Impinging Jets

Cited by 31 publications

References 23 publications

Numerical Characterization of Pressure Drop Across the Manifold of Turbine Casing Cooling System

Numerical Characterization of Pressure Drop Across the Manifold of Turbine Casing Cooling System

Recent Developments in Impingement Array Cooling, Including Consideration of the Separate Effects of Mach Number, Reynolds Number, Temperature Ratio, Hole Spacing, and Jet-to-Target-Plate Distance

Investigation of the Conjugate Heat Transfer and Flow Field for a Flat Plate with Combined Film and Impingement Cooling

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