Effects of Reynolds Number and Free-Stream Turbulence on Boundary Layer Transition in a Compressor Cascade

Schreiber, H. A.; Steinert, W.; Küsters, Bernhard

doi:10.1115/1.1413471

Cited by 58 publications

(9 citation statements)

References 16 publications

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“…Experimentally, Leipold et al [6] measured loss and boundary layer parameters in a highly loaded transonic compressor cascade for Reynolds numbers between 300,000 and 1 Â 10 6 . Schreiber et al [7] reported performance dependence of a roughened controlled-diffusion airfoil (CDA) on Reynolds numbers ranging from 100,000 to 3 Â 10 6 . Analytical models to predict performance deterioration of gas turbine compressors have been developed by many researchers including Millsaps et al [8], Aker and Saravanamottoo [9], Massardo [10], Syverud and Bakken [11], and Song et al [12].…”

Section: Introductionmentioning

confidence: 99%

Effects of Reynolds Number and Surface Roughness Magnitude and Location on Compressor Cascade Performance

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Hobson

Song

et al. 2012

Journal of Turbomachinery

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An experimental investigation has been conducted to characterize the influence of Reynolds number and surface roughness magnitude and location on compressor cascade performance. Flow field surveys have been conducted in a low-speed, linear compressor cascade. Pressure, velocity, and loss have been measured via a five-hole probe, pitot probe, and pressure taps on the blades. Four different roughness magnitudes, Ra values of 0.38 μm (polished), 1.70 μm (baseline), 2.03 μm (rough 1), and 2.89 μm (rough 2), have been tested. Furthermore, various roughness locations have been examined. In addition to the as manufactured (baseline) and entirely rough blade cases, blades with roughness covering the leading edge, pressure side, and 5%, 20%, 35%, 50%, and 100% of suction side from the leading edge have been studied. All of the tests have been carried out for Reynolds numbers ranging from 300,000 to 640,000. For Reynolds numbers under 500,000, the tested roughnesses do not significantly degrade compressor blade loading or loss. However, loss and blade loading become sensitive to roughness at Reynolds numbers above 550,000. Cascade performance is more sensitive to roughness on the suction side than pressure side. Furthermore, roughness on the aft 2/3 of suction side surface has a greater influence on loss. For a given roughness location, there exists a Reynolds number at which loss begins to significantly increase. Finally, increasing the roughness area on the suction surface from the leading edge reduces the Reynolds number at which the loss begins to increase.

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Section: Introductionmentioning

confidence: 99%

Effects of Reynolds Number and Surface Roughness Magnitude and Location on Compressor Cascade Performance

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Hobson

Song

et al. 2012

Journal of Turbomachinery

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“…1) There was a good agreement between the test data and the calculated efficiency and performance within Reynolds numbers from 30,000 to 295,000. Schreiber et al 3) researched transition phenomena on the blade surface in a compressor cascade by changing the Reynolds number and turbulence intensity, finding a laminar separation bubble with reattachment on the suction surface at relatively low Reynolds number. Van Treuren et al 4) ran wind tunnel tests at Reynolds numbers from 25,000 to 50,000 and found that a large separation near the trailing edge of a turbine cascade degraded total pressure loss.…”

Section: Introductionmentioning

confidence: 99%

Effects of Low Reynolds Number on Loss Characteristics in Transonic Axial Compressor

Choi

Baek

Park

et al. 2010

Trans. Japan Soc. Aero. S Sci.

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A three-dimensional computation was conducted to understand effects of low Reynolds numbers on loss characteristics in a transonic axial compressor, Rotor 67. As a gas turbine becomes smaller and it operates at high altitude, the engine frequently operates under low Reynolds number conditions. This study found that large viscosity significantly affects the location and intensity of the passage shock, which moves toward the leading edge and has decreased intensity at low Reynolds number. This change greatly affects performance as well as internal flows, such as pressure distribution on the blade surface, tip leakage flow and separation. The total pressure ratio and adiabatic efficiency both decreased by about 3% with decreasing Reynolds number. At detailed analysis, the total pressure loss was subdivided into four loss categories such as profile loss, tip leakage loss, endwall loss and shock loss.

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“…For most turbine compressors, the Reynolds numbers based on chord Re c are typically between 0.6 × 10 6 and 4 × 10 6 [9] (the Reynolds numbers based on the leading edge half thickness Re t are typically between 0.3 × 10 4 and 0.9 × 10 4 for aero-engine). The free-stream turbulence intensities (Tu) are around 4% [10] (around 12% when the wake comes).…”

Section: Introductionmentioning

confidence: 99%

The Analysis of Leading Edge Deformations on Turbomachine Blades

Liu

2019

Energies

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With recent advancements in the development of material and manufacturing technology, the leading edge geometry of turbomachine blades has attracted widespread attention. “Sharp” leading edges always have a better aerodynamic performance, though it is prone to deformations easily. Thus, flat plates and real compressor cascades with different leading edge deformations were investigated to study the influence, which is applicable for thin blades at low speeds. Different boundary layer characteristics, including the velocity profile, transition process, and loss, are compared. The results show that there are several kinds of contradictory influence mechanisms and that the final phenomenon is closely related to the condition of the original boundary layer. In low turbulence, with large and laminar separation, the deformations can suppress separation and decrease loss. In high turbulence, with short and transitional separation, deformations can promote the transition process and increase the loss. The sensitivities of different the original leading edge shapes are also compared. This indicates that a good design always has a better robustness at low turbulence values, while it is worse at high turbulence values. The cascade experiment and simulation show that the deformation influence is similar to flat plates and that it is enlarged near the hub, which affects the corner separation.

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Effects of Reynolds Number and Free-Stream Turbulence on Boundary Layer Transition in a Compressor Cascade

Cited by 58 publications

References 16 publications

Effects of Reynolds Number and Surface Roughness Magnitude and Location on Compressor Cascade Performance

Effects of Reynolds Number and Surface Roughness Magnitude and Location on Compressor Cascade Performance

Effects of Low Reynolds Number on Loss Characteristics in Transonic Axial Compressor

The Analysis of Leading Edge Deformations on Turbomachine Blades

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