Flow and heat transfer measurements in swirl tubes with one and multiple tangential inlet jets for internal gas turbine blade cooling

Biegger, Christoph; Rao, Yu; Weigand, Bernhard

doi:10.1016/j.ijheatfluidflow.2018.07.011

Cited by 37 publications

(8 citation statements)

References 17 publications

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“…The tangential injection creates a vortex in the quartz tube which stabilizes the plasma in the center and prevents the walls of the reactor from coming into contact with the plasma [40]. The pressure and velocity in the reactor center are lower than at the wall [41], two effects that ensure the ignition is favored in the tube center. At the wall, the pressure and velocity are higher leading to better cooling of the discharge tube.…”

Section: Methodsmentioning

confidence: 99%

Influence of hydrogen addition on methane coupling in a moderate pressure microwave plasma

Wnukowski

Steeg

Hrycak

et al. 2021

Fuel

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Section: Methodsmentioning

confidence: 99%

Influence of hydrogen addition on methane coupling in a moderate pressure microwave plasma

Wnukowski

Steeg

Hrycak

et al. 2021

Fuel

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“…Where P sj is nozzle inlet static pressure, L is axial length of vortex chamber, V j is nozzle inlet speed, D c is vortex chamber section top length, P so is outlet static pressure, ρ is cool air density. Thermal performance factor 21 is defined as follows:…”

Section: Parameter Definitionmentioning

confidence: 99%

“…Where Nu 0 and f 0 are the Nusselt umber and pressure loss coefficient of smooth straight channels, Nu a is globally averaged Nusselt number. Nu 0 and f 0 are defined as follows: 21 Nu 0 ¼ 0:023Re 0:8 Pr 0:4 (7)…”

Section: Parameter Definitionmentioning

confidence: 99%

Numerical investigation on vortex cooling flow and heat transfer characteristics for gas turbine blade with variable coolant chamber cross-sectional shapes

Li,

Gao,

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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In this paper, according to the actual size of gas turbine blade interior space, eight vortex cooling models with different cross-sectional shapes of coolant chambers are established. Rectangular, Circle, Trapezoidal up, Trapezoidal down, Ellipse up, Ellipse down, Sine up and Sine down are the eight coolant chamber shapes. Functions of variable coolant chamber structures on vortex cooling flow and heat exchange characteristics are numerically analyzed by verifying the Standard k- ω turbulence model and conducting grid independence analysis. Research results show that the heat exchange ability of Sine up coolant chamber is the best compared with the other coolant chambers. The cool air enters the vortex chamber at a faster speed and impacts on the target surface to form a high-pressure area and a low-temperature swirl. The more the cool air moves downstream, the greater the turbulent kinetic energy becomes, which is more conducive to the heat transfer. Therefore, Sine up coolant chambers have the highest thermal performance factor. Due to the low drag coefficient and high target surface average Nusselt number of Ellipse up, its thermal exchange performance is second only to that of Sine up. Circle coolant chamber will not bring favorable factors to engineering application because of the slowest flow speed and the worst heat exchange capacity. For Trapezoidal up and Trapezoidal down, the flow velocity, pressure distribution, turbulent kinetic energy intensity and heat transfer uniformity are almost the same as Rectangle coolant chamber. The models of Ellipse down and Sine down coolant chambers exhibit less turbulent kinetic energy strength to heat transfer and higher temperature in the vortex chamber, and it is not suggested for cooling system optimal design.

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“…The results revealed that there was a 5.2% increase in the heat transfer due to using film holes bleeding compared to the case without it. Biegger et al [29] presented an experimental and numerical investigation to study the flow and heat transfer in a swirl pipe with multiple tangential jet nozzles. They confirmed that the swirling pipe with one jet nozzle obtains higher heat transfer while the model with multiple jets achieves more uniform heat transfer with higher pressure loss.…”

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 and heat transfer measurements in swirl tubes with one and multiple tangential inlet jets for internal gas turbine blade cooling

Cited by 37 publications

References 17 publications

Influence of hydrogen addition on methane coupling in a moderate pressure microwave plasma

Influence of hydrogen addition on methane coupling in a moderate pressure microwave plasma

Numerical investigation on vortex cooling flow and heat transfer characteristics for gas turbine blade with variable coolant chamber cross-sectional shapes

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

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