The Effect of Internal Crossflow on the Adiabatic Effectiveness of Compound Angle Film Cooling Holes

McClintic, John W.; Klavetter, Sean R.; Winka, James R.; Anderson, Joshua B.; Bogard, David G.; Laskowski, Gregory M.; Briggs, Robert

doi:10.1115/1.4029157

Cited by 40 publications

(8 citation statements)

References 9 publications

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“…In addition to co-flow and counter-flow coolant supply configurations studies, several authors have studied effects of crossflow on film cooling performance compared to plenum or co-flow configurations [7,[11][12][13][14]. In one of these studies, Saumweber et al [12] came to the general conclusion that fan-shaped holes are more sensitive to coolant crossflow than round holes, and the effectiveness of both hole shapes are strongly impacted by the internal coolant flow direction.…”

Section: Review Of Literaturementioning

confidence: 99%

Effects of Coolant Feed Direction on Additively Manufactured Film Cooling Holes

Stimpson

Snyder

Thole

et al. 2018

Journal of Turbomachinery

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Gas turbine components subjected to high temperatures can benefit from improved designs enabled by metal additive manufacturing (AM) with nickel alloys. Previous studies have shown that the impact on fluid flow and heat transfer resulting from surface roughness of additively manufactured parts is significant; these impacts must be understood to design turbine components successfully for AM. This study improves understanding of these impacts by examining the discharge coefficient and the effect of the coolant delivery direction on the performance of additively manufactured shaped film cooling holes. To accomplish this, five test coupons containing a row of baseline shaped film cooling holes were made from a high-temperature nickel alloy using a laser powder bed fusion (L-PBF) process. Flow and pressure drop measurements across the holes were collected to determine the discharge coefficient from the film cooling holes. Temperature measurements were collected to assess the overall effectiveness of the coupon surface as well as the cooling enhancement due to film cooling. The Biot number of the coupon wall was matched to a value one might find in a turbine engine to ensure this data is relevant. It was discovered that the flow experienced greater aerodynamic losses in film cooling holes with greater relative roughness, which resulted in a decreased discharge coefficient. The effectiveness measurements showed that the film cooling performance is better when coolant is fed in a co-flow configuration compared to a counter-flow configuration.

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Section: Review Of Literaturementioning

confidence: 99%

Effects of Coolant Feed Direction on Additively Manufactured Film Cooling Holes

Stimpson

Snyder

Thole

et al. 2018

Journal of Turbomachinery

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show abstract

“…In (Saumweber et al, 2012a) the authors concluded that this coolant inclination was influenced by blowing ratio and cooling flow Mach number. In (McClintic et al, 2015; geometries with compound injection angles were studied, concluding that higher adiabatic effectiveness was achieved for crossflow counter to the direction of the coolant injection. Finally, it was confirmed that ingestion of mainstream gas was present in cross flow conditions too (McClintinc et al, 2018).…”

Section: Introductionmentioning

confidence: 99%

Investigating the effects of fan-shaped cooling hole geometry parameters on film cooling effectiveness for internal coolant cross-flow using CFD

Gousopoulos¹,

Nikolos²

2020

Proceedings of Global Power &Amp; Propulsion Society

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The geometry and distribution of cooling holes play a vital role in the effectiveness of the surface cooling of gas turbine blades, as well as in the design and operation of modern gas turbines. The geometry parameters of a cooling hole affect the downstream temperature and flow fields, as well as the adiabatic film cooling effectiveness distribution. To gain a better view on the way the cooling holes' performance is affected, cross-flow (with internal cooling flow direction normal to the external hot gas flow) CFD simulations were performed for fan-shaped cooling holes. Initially, an existing cooling hole geometry was considered, while then the cooling hole geometry was rotated around the symmetry axis of its cylindrical part. The simulation results revealed that the cooling hole rotation affects adiabatic effectiveness positively at low and intermediate blowing ratios. The observation that the cooling flow attaches to the walls of the rotated holes more effectively is the main reason for the increase in the cooling effectiveness.

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“…It is found that a continuous ribbed cooling channel can increase the laterally averaged heat transfer coefficient compared with smooth cooling channel. MeClintic et al (2015) used an experimental flat plate facility to study the effects of internal cross flow on film cooling performance. Compared with a plenum-fed configuration and the case where the coolant flew in line with the coolant hole span-wise direction, significantly greater adiabatic effectiveness was achieved for cross flow countered to the direction of coolant injection.…”

Section: Introductionmentioning

confidence: 99%

Computational analysis of span-wise hole locations on fluid flow and film cooling of internal channels with crescent ribs

Zhang

Liu

Sundén

et al. 2019

HFF

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Purpose This study aims to clarify the mechanism of film hole location at the span-wise direction of an internal cooling channel with crescent ribs on the adiabatic film cooling performance, three configurations are designed to observe the effects of the distance between the center of the ellipse and the side wall(Case 1, l = w/2, Case 2, l = w/3 and for Case 3, l = w/4). Design/methodology/approach Numerical simulations are conducted under two blowing ratios (i.e. 0.5 and 1) and a fixed cross-flow Reynolds number (Rec = 100,000) with a verified turbulence model. Findings It is shown that at low blowing ratio, reducing the distance increases the film cooling effectiveness but keeps the trend of the effectiveness unchanged, while at high blowing ratio, the characteristic is a little bit different in the range of 0 = x/D = 10. Research limitations/implications These features could be explained by the fact that shrinking the distance between the hole and side wall induces a much smaller reserved region and vortex downstream the ribs and a lower resistance for cooling air entering the film hole. Furthermore, the spiral flow inside the hole is impaired. Originality/value As a result, the kidney-shaped vortices originating from the jet flow are weakened, and the target surface can be well covered, resulting in an enhancement of the adiabatic film cooling performance.

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The Effect of Internal Crossflow on the Adiabatic Effectiveness of Compound Angle Film Cooling Holes

Cited by 40 publications

References 9 publications

Effects of Coolant Feed Direction on Additively Manufactured Film Cooling Holes

Effects of Coolant Feed Direction on Additively Manufactured Film Cooling Holes

Investigating the effects of fan-shaped cooling hole geometry parameters on film cooling effectiveness for internal coolant cross-flow using CFD

Computational analysis of span-wise hole locations on fluid flow and film cooling of internal channels with crescent ribs

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