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Research Papers

Secondary Flow Loss Reduction Through Blowing for a High-Lift Front-Loaded Low Pressure Turbine Cascade

[+] Author and Article Information
Stuart I. Benton

Graduate Fellow
e-mail: benton.53@osu.edu

Jeffrey P. Bons

Professor
e-mail: bons.2@osu.edu
Department of Mechanical and Aerospace Engineering,
The Ohio State University,
2300 West Case Road,
Columbus, OH 43235

Rolf Sondergaard

Aerospace Engineer
Propulsion Directorate of the Air Force Research Laboratory,
1950 Fifth Street,
Wright Patterson AFB, OH 45433 
e-mail: rolf.sondergaard@wpafb.af.mil

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received July 2, 2012; final manuscript received July 25, 2012; published online November 5, 2012. Editor: David Wisler.

J. Turbomach 135(2), 021020 (Nov 05, 2012) (8 pages) Paper No: TURBO-12-1114; doi: 10.1115/1.4007531 History: Received July 02, 2012; Revised July 25, 2012

Efforts to increase individual blade loading in the low pressure turbine have resulted in blade geometries optimized for midspan performance. Many researchers have shown that increased blade loading and a front-loaded pressure distribution each separately contribute to increased losses in the endwall region. A detailed investigation of the baseline endwall flow of the L2F profile, which is a high-lift front loaded profile, is performed. In-plane velocity vectors and total pressure loss maps are obtained in five planes oriented normal to the blade surface for three Reynolds numbers. A row of pitched and skewed jets are introduced near the endwall on the suction surface of the blade. The flow control method is evaluated for four momentum coefficients at the high Reynolds number, with a maximum reduction of 42% in the area averaged total pressure loss coefficient. The same blade is also fitted with midspan vortex-generator jets and is tested at a Reynolds number of 20,000, resulting in a 21% reduction in the area averaged total pressure loss.

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References

Figures

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Fig. 1

Pressure coefficients at the Reynolds numbers of interest

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Fig. 5

Distance between the vortex core and the blade suction surface for the baseline cases

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Fig. 4

The PIV velocity vectors overlaid on contours of the total pressure loss coefficient

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Fig. 3

Normalized midspan loss versus the Reynolds number of the present study compared to the experimental data of Lyall et al. [11]

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Fig. 2

Location and domain of the measurement planes

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Fig. 8

The CAD model showing flow control placement

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Fig. 7

Decomposed endwall and midspan area-averaged losses as a fraction of the total area-averaged loss

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Fig. 6

Schematic of the loss decomposition process

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Fig. 9

Total pressure loss coefficient and streamwise-normal velocity vectors in the outlet plane for the baseline case: Re = 80,000

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Fig. 10

Total pressure loss coefficient and streamwise-normal velocity vectors in the outlet plane for the controlled case of Cμ = 4%: Re = 80,000

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Fig. 11

Mass averaged values as a function of the span: Re = 80,000. Exit angle (left) and total pressure loss coefficient (right).

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Fig. 15

Total pressure loss coefficient in the outlet plane for the baseline case: Re = 20,000

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Fig. 16

Total pressure loss coefficient in the outlet plane for the controlled case of Cμ,EW = 4% and BMS = 2.1: Re = 20,000

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Fig. 12

Distance between the vortex core and the blade suction surface: Re = 80,000

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Fig. 13

The PIV velocity vectors overlaid on contours of the in-plane velocity magnitude at plane NP1

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Fig. 14

Area-averaged total pressure loss coefficient in the outlet plane for the controlled cases

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