A Novel Anti-Vortex Turbine Film Cooling Hole Concept

Heidmann, James D.; Ekkad, Srinath V.

doi:10.1115/gt2007-27528

Cited by 48 publications

(32 citation statements)

References 23 publications

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“…Schulz et al [8] have done the experimental investigations of an anti-vortex film cooling geometry under low and high turbulence conditions. Similar observations have been reported as the previous results [6,7]. It is suggested that the new hole design reduces the jet exit momentum, preventing jet detachment leads to significant improvement in film cooling effectiveness.…”

Section: Literature Reviewsupporting

confidence: 80%

“…However, among all the considered cases, shaped hole producing better-quality film cooling effectiveness mainly due to better coolant distribution in the lateral direction and at near the hole. Heidmann et al [6] have proposed new cooling hole design namely anti-vortex film cooling hole. The anti-vortex cooling hole consists of single hole which accompanied with two sister holes.…”

Section: Literature Reviewmentioning

confidence: 99%

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Parametric Study on Anti-Vortex Film Cooling Hole Arrangements

Abdullah

Aminnuddin

Mohammed

2014

AMM

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Abstract. Film cooling has been extensively used to provide thermal protection for the external surface of the gas turbine blades. Numerous number of film cooling holes designs and arrangements have been introduced. The main motivation of these designs and arrangements are to reduce the liftoff effect cause by the counter rotating vortices (CRVP) produce by cylindrical cooling hole. One of the efforts is the introduction of newly found anti-vortex film cooling design. The present study focuses on anti-vortex holes arrangement consists of a main hole and pair of smaller holes. All three holes share a common inlet with the outlet of the smaller holes varies base on it relative position towards the main hole. Three anti-vortex holes arrangements have been considered; downstream anti-vortex hole arrangement (DAV), lateral anti-vortex hole arrangement (LAV), and upstream anti-vortex hole arrangement (UAV). In addition, a single hole (SH) film cooling has also been considered as the baseline. The investigation make used of ANSYS CFX software ver. 14. The investigations are made through Reynolds Average Navier Stokes analyses with the application of shear k-ε turbulence model. The results show that the anti-vortex designs produce significant improvement in term of film cooling effectiveness and distribution. The LAV arrangement shows the best film cooling effectiveness distribution among all considered cases and is consistent for all blowing ratios (BR). The results also unveil the formation of new vortex pair on both side of the primary hole CRVP. Interaction between the new vortices and the main CRVP structure reduce the lift off explaining the increased lateral film effectiveness.

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Section: Literature Reviewsupporting

confidence: 80%

Section: Literature Reviewmentioning

confidence: 99%

Parametric Study on Anti-Vortex Film Cooling Hole Arrangements

Abdullah

Aminnuddin

Mohammed

2014

AMM

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“…The anti-vortex hole (AVH) geometry was developed by Heidmann et al [6] and could possibly, though optimization reduce or counter the vorticity of the counter rotating vortex that exists in conventional straight and even shaped hole film cooling schemes. The geometry examined in this study was selected from the study by Dhungel et al [7] that compared six different anti-vortex hole geometries.…”

Section: Film Cooling Geometrymentioning

confidence: 99%

“…The concept of Anti-Vortex Hole (AVH) was developed by Heidmann et al [6] in order to reduce this vortex effect by introducing two side holes that produce a strong upwash effect that is intended to balance the downwash on the outside of the main hole jet CRV or "kidney vortex". This is the main difference between the AVH and single hole geometry.…”

Section: Visualization Of Counter Rotating Vorticesmentioning

confidence: 99%

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Flow Visualization of Multi-Hole Film-Cooling Flow under Varying Freestream Turbulence Levels

Repko¹,

Nix²,

Uysal³

et al. 2016

JFCMV

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A flat plate film cooling flow from a multi-exit hole configuration has been numerically simulated using both steady and unsteady Reynolds Averaged Navier Stokes (RANS and URANS) Computational Fluid Dynamics (CFD) formulations. This multi-exit hole concept, the Anti-Vortex Hole (AVH), has been developed and studied by previous research groups and shown to mitigate or counter the vorticity generated by conventional holes resulting in a more attached film cooling layer and higher film cooling effectiveness. The film cooling jets interaction with the free stream flow is a long studied area in gas turbine heat transfer. The present study numerically simulates the jet interaction with the multi-exit hole concept at a high blowing ratio (M = 2.0) and density ratio (DR = 2.0) in order to provide a more detailed, graphical explanation of the improvement in film cooling effectiveness. This paper presents a numerical study of the flow visualization of the interaction of film cooling jets with a subsonic crossflow. The contour plots of adiabatic cooling effectiveness were used to compare the multi-exit hole and conventional single hole configurations. The vortex structures in the flow were analyzed by URANS formulations and the effect of these vortices on the cooling effectiveness was investigated together with the coolant jet lift-off predictions. Quasi-Instantaneous Temperature Isosurface plots are used in the investigations of the effect of turbulence intensity on the cooling effectiveness and coolant jet coverage. The effect of varying turbulence intensity was investigated when analyzing the jets' interaction with the cross flow and the corresponding temperatures at the wall. The results show that as the turbulence intensity is increased, the cooling flow will stay more attached to the wall and have more pronounced lateral spreading far downstream of the cooling holes.

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Film cooling with using the decomposition of an NH3 cooling stream as a chemical heat sink

et al. 2012

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The inlet temperatures of gas turbines are generally increasing over time, so conventional cooling methods are likely to approach their useful limits. It is therefore essential to investigate novel cooling methods. Based on the theory of heat transfer enhancement, a novel film cooling method for gas turbine blades using a chemical heat sink is proposed. In this method, the endothermic reaction of an NH 3 cooling stream heated by the main gas stream takes place, reducing the convective heat transfer between the mainstream and the blades. Therefore, film cooling effectiveness is improved. To test the feasibility of the proposed method, numerical simulations were conducted, using the classical flat plate with a 30 degree angled cylindrical hole (diameter, D). Film cooling effectiveness at different blowing ratios (M = 0.5, 1.0, and 1.5) were computed and compared with the results of conventional cooling methods. The simulation results show that the proposed method can enhance film cooling effectiveness not only in the stream-wise direction, but also in the span-wise direction. The span-averaged film effectiveness is improved in the presence of a chemical heat sink, with the value of X/D (the ratio of downstream distance from the center of the film hole to the diameter of the film hole) increasing downstream of the film hole. The novel film cooling approach showed the best performance at M = 0.5. reaction, heat sink, film cooling, heat transfer, numerical simulation Citation:Cheng K Y, Chen W, Liang S Q, et al. Film cooling with using the decomposition of an NH 3 cooling stream as a chemical heat sink.

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A Novel Anti-Vortex Turbine Film Cooling Hole Concept

Cited by 48 publications

References 23 publications

Parametric Study on Anti-Vortex Film Cooling Hole Arrangements

Parametric Study on Anti-Vortex Film Cooling Hole Arrangements

Flow Visualization of Multi-Hole Film-Cooling Flow under Varying Freestream Turbulence Levels

Film cooling with using the decomposition of an NH3 cooling stream as a chemical heat sink

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