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Research Papers

Film Cooling Measurements for a Laidback Fan-Shaped Hole: Effect of Coolant Crossflow on Cooling Effectiveness and Heat Transfer

[+] Author and Article Information
Marc Fraas

Institute of Thermal Turbomachinery (ITS),
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
e-mail: marc.fraas2@kit.edu

Tobias Glasenapp, Achmed Schulz, Hans-Jörg Bauer

Institute of Thermal Turbomachinery (ITS),
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 18, 2018; final manuscript received October 2, 2018; published online January 21, 2019. Editor: Kenneth Hall.

J. Turbomach 141(4), 041006 (Jan 21, 2019) (10 pages) Paper No: TURBO-18-1251; doi: 10.1115/1.4041655 History: Received September 18, 2018; Revised October 02, 2018

Internal coolant passages of gas turbine vanes and blades have various orientations relative to the external hot gas flow. As a consequence, the inflow of film cooling holes varies as well. To further identify the influencing parameters of film cooling under varying inflow conditions, the present paper provides detailed experimental data. The generic study is performed in a novel test rig, which enables compliance with all relevant similarity parameters including density ratio. Film cooling effectiveness as well as heat transfer of a 10–10–10 deg laidback fan-shaped cooling hole is discussed. Data are processed and presented over 50 hole diameters downstream of the cooling hole exit. First, the parallel coolant flow setup is discussed. Subsequently, it is compared to a perpendicular coolant flow setup at a moderate coolant channel Reynolds number. For the perpendicular coolant flow, asymmetric flow separation in the diffuser occurs and leads to a reduction of film cooling effectiveness. For a higher coolant channel Reynolds number and perpendicular coolant flow, asymmetry increases and cooling effectiveness is further decreased. An increase in blowing ratio does not lead to a significant increase in cooling effectiveness. For all cases investigated, heat transfer augmentation due to film cooling is observed. Heat transfer is highest in the near-hole region and decreases further downstream. Results prove that coolant flow orientation has a severe impact on both parameters.

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References

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Figures

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Fig. 1

Test rig in perpendicular coolant flow configuration (adjusted from Fraas et al. [7]): (1) turbulence grid, (2) boundary layer bleed, (3) ejection module, (4) sapphire windows, and (5) test plate

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Fig. 2

Geometry of the laidback fan-shaped hole used in this study

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Fig. 3

Adiabatic film cooling effectiveness ηaw along the centerline at M = 1.0:2.0;3.0 against 5 ≤ x/D ≤ 50 (parallel coolant flow (ǁ), ReD,cc = 5000)

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Fig. 4

Laterally averaged adiabatic film cooling effectiveness ηaw,lat at M = 1.0:2.0;3.0 against 5 ≤ x/D ≤ 50 (parallel coolant flow (ǁ), ReD,cc = 5000)

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Fig. 5

Contours of adiabatic film cooling effectiveness ηaw for 5 ≤ x/D ≤ 50 and −4 ≤ y/D ≤ 4 at M = 1.0:2.0;3.0 and different coolant flow conditions: (a) parallel coolant flow orientation (ǁ), ReD,cc = 5000, (b) perpendicular coolant flow orientation (⊥), ReD,cc = 5000, and (c) perpendicular coolant flow orientation (⊥), ReD,cc = 30,000

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Fig. 6

Comparison of adiabatic film cooling effectiveness ηaw along the centerline with data from Schroeder and Thole [1] for M = 1.0;2.0:3.0 and 5 ≤ x/D ≤ 40

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Fig. 7

Adiabatic film cooling effectiveness ηaw at M = 1.0 and M = 3.0 for parallel (ǁ) and perpendicular (⊥) coolant flow (ReD,cc = 5000) against y/D at x/D = 5 (a) and x/D = 40 (b) (legend applicable for both graphs)

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Fig. 8

Laterally averaged adiabatic film cooling effectiveness ηaw,lat for parallel coolant flow (ǁ) and perpendicular coolant flow (⊥) at blowing ratios M = 1.0 and M = 3.0 and 5 ≤ x/D ≤ 50

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Fig. 9

Laterally averaged heat transfer coefficients hf,lat/h0,lat for parallel coolant flow (ǁ) and perpendicular coolant flow (⊥) at blowing ratios M = 1.0 and M = 3.0, and 5 ≤ x/D ≤ 50

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Fig. 10

Contours of heat transfer coefficients hf,lat/h0,lat for 5 ≤ x/D ≤ 50 and −4 ≤ y/D ≤ 4 at M = 1.0 and ReD,cc = 5000 with lines of constant adiabatic film cooling effectiveness (black): (a) parallel coolant flow orientation (ǁ) and (b) perpendicular coolant flow orientation (⊥)

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Fig. 11

Adiabatic film cooling effectiveness ηaw at M = 1.0 and M = 3.0 for ReD,cc = 5000 and ReD,cc = 30,000 (perpendicular coolant flow (⊥)) against y/D at x/D = 5 (a) and x/D = 40 (b) (legend applicable for both graphs)

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Fig. 12

Laterally averaged adiabatic film cooling effectiveness ηaw,lat against 5 ≤ x/D ≤ 50 for perpendicular coolant flow (⊥) and Reynolds numbers ReD,cc = 5000 and 30,000 at blowing ratios M = 1.0 and M = 3.0

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Fig. 13

Ratio of heat transfer coefficients hf,lat/h0,lat for perpendicular coolant flow against 5 ≤ x/D ≤ 50 at blowing ratios M = 1.0 and M = 3.0 and Reynolds numbers ReD,cc = 5000 and 30,000

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Fig. 14

Spatially averaged adiabatic film cooling effectiveness η=aw for blowing ratios 0.5 ≤ M ≤ 3.0

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