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1

Study on the behavior of streamwise vortices formed between leading edge tubercles in a compressor cascade

Zheng Tan, Qiang Xiao-Qing, Teng Jin-Fang, Feng Jin-Zhang

Journal of Theoretical and Applied Mechanics

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2019

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Vol. 57 nr 3

617--629

EN

A study has been carried out to investigate the formation mechanism and development of streamwise vortices induced by leading edge tubercles in a high speed compressor cascade. The preliminary assessment of the cascade performance in terms of the total pressure loss coefficient shows that the loss reduction is achieved at high incidence angles. A smaller wavelength leads to higher additional losses at the design point, but gives rise to a greater loss reduction at high incidence angles. The modified cascade with a tubercle wavelength of 4% chord achieves the maximum loss reduction of 36.1% at i = 10◦ , as well as the stall angle improvement of 27.6%. The formation mechanism of streamwise vortices is elaborated on the basis of the streamwise vorticity equation, in which the streamwise turning terms may be responsible for the generation of streamwise vortices. Slices of streamwise vorticity at various streamwise locations, combined with vorticity strength distributions, have been presented to study the development of streamwise vortices. The counter-rotating vortices are divided into the crest-induced streamwise vortices (CSVs) and trough-induced streamwise vortices (TSVs). A streamwise vortex pair formed from a part of the CSV sheets behind troughs, is gradually entrained by the TSV pair along the streamwise direction. In addition, the tubercles with a smaller wavelength result in higher streamwise vorticity strength with which the streamwise vortices interact with the flow separation more sufficiently and delay the separation to a greater extent.

2

Numerical loss analysis in a compressor cascade with leading edge tubercles

Zheng T., Qiang X.-Q., Teng J.-F., Teng J.-Z.

Journal of Theoretical and Applied Mechanics

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2018

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Vol. 56 nr 4

1083--1095

EN

A numerical analysis of loss has been carried out to explore the loss mechanism of leading edge tubercles in a high speed compressor cascade. Taking the lead from flippers of the humpback whale, tubercles are passive structures of a blade for flow control. Evaluation of the overall performance in terms of entropy increase shows that the loss reduction is achieved both at high negative and high positive incidence angles, while a rise in the loss is obtained near the design point. And a smaller wave number as well as a smaller amplitude results in lower additional losses at the design point. Spanwise and streamwise distributions of pitchwise-averaged entropy increase combined with flow details have been presented to survey the loss development and, subsequently, to interpret the loss mechanism. The tubercle geometry results in the deflection flow and the consequent spanwise pressure gradient. This pressure gradient induces formation of counter-rotating streamwise vortices, transports away the low-momentum fluid near wall from crests towards troughs and leads to local high loss regions behind troughs as well as loss reduction behind the crests in comparison to the baseline. The interaction between these vortices and flow separation by momentum transfer leads to separation delay and the consequent loss reduction at the outlet.

3

Non-symmetrical boundary layer suction in a compressor cascade

Liesner K., Meyer R., Schulz S.

Journal of Theoretical and Applied Mechanics

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2012

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Vol. 50 nr 2

455-472

EN

In order to simulate non-symmetrical boundary layer suction in an annular compressor, a cascade investigation has been performed with single-sided suction slots only. A preceding investigation had revealed a high potential for loss reduction by two different types of boundary layer suction. The experimental investigation was performed with five NACA 65-k48 stator blades at the design Mach number of 0.67 and Reynolds number of 560.000. The two investigated suction geometries are a narrow slot following the design of Peacock and a wider slot of own origin, both slots are positioned on one side of the passage only. The Peacock slot is placed in the corner between suction side of the vane and the side wall, the wider slot is positioned from suction side to pressure side following the side wall’s flow detachment line. With half the suction rate of the preceding investigation the efficiency of the cascade could still be enhanced. In the case with 2.5% suction rate the total pressure loss coefficient of the full passage was decreased by 13%, in the case with 1% suction rate the loss coefficient was decreased by even 10%. The outflow of the cascade is as expected no more symmetrical and the one sided suction has no large impact on the flow of the opposite side of the passage.

PL

W pracy przeprowadzono symulację problemu zasysania czynnika w niesymetrycznej warstwie przyściennej sprężarki, analizując kaskadę z jednostronnymi wlotami ssącymi. Badania poprzedzające ujawniły wysoki potencjał w ograniczaniu strat przy zastosowaniu dwóch różnych rozwiązań sposobu zasysania w warstwie przyściennej. Doświadczenia przeprowadzono, używając pięciu łopatek kierownicy sprężarki NACA 65-K48 projektowanej do przepływu przy prędkości 0.67Ma i liczby Reynoldsa 560000. Geometria obydwu rozwiązań zasysania wykorzystuje projekt wąskiej szczeliny wlotowej R.E. Peacocka oraz projekt własny szczeliny szerszej, przy czym obydwa typy umiejscowiono wyłącznie po jednej stronie kanału przelotowego. Szczelinę Peacocka umieszczono w rogu pomiędzy stroną ssącą łopatki oraz ściany, natomiast szczelina szeroka pokrywa obszar od strony ssącej do sprężającej wzdłuż linii odrywania przepływu. Przy tempie zasysania stanowiącym połowę wydatku stosowanego w poprzedzających badaniach nadal odnotowano możliwość zwiększenia sprawności kaskady. Przy spadku tempa ssania do 2.5%, współczynnik całkowitych strat ciśnienia zmalał o 13%, natomiast dla dalszego spadku do 1% współczynnik ten zmniejszył się o 10%. Zgodnie z oczekiwaniami wypływ z kaskady utracił symetrię, a zasysanie jednostronne nie zmieniło znacząco charakteru przepływu na przeciwnej stronie kanału przelotowego.

4

Numerical analysis of controlling separation in axial cascades by excitation of periodical incoming wake

Liu F., Wang J., Wu K.

TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk

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2008

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Vol. 12, No 1-2

21-34

EN

Numerical analysis has been performed of time-space structures in a large turning angle axial cascade subject to unsteady incoming wake excitation. The results have shown that intentional unsteady excitation could increase the cascade's time-averaged performance. As a result, the vortex structures corresponding to the external exciting frequency are strengthened and other disordered vortices are involved, so that the separation structures of the suction surface are translated from disorder to order. Two interaction regimes between incoming periodic wakes and separation structures are analyzed, indicating that turbulent kinetic energy can enhance momentum interchange and that wave-vortex resonance can promote rolled-up and plus-minus pairing of vortices. Based .on these, responses of separation structures from two periodic incoming wake regimes are compared. The feasibility of far-field noise reduction in ducting fans by using periodic incoming wake is considered.

5

Numerical simulation of the influence of a fillet and a bulb on the secondary flow in a compressor cascade

Hoeger M., Schmidt-Eisenlohr U., Gomez S., Sauer H., Müller R.

TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk

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2002

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Vol. 6, No 1

25-37

EN

Large fillet radii are typically found on highly loaded compressor rotors to ensure structural integrity. The objective of this paper is to investigate the impact of such real geometry effects on the flow at the hub section. Investigations were performed numerically for the idealised case of a plane compressor cascade with the 3D Navier-Stokes code TRACE_S. Realistic inlet boundary layer displacement thickness and typical loading levels close to stall are considered at low inlet Mach numbers Ma1 = 0.23. A large fillet with a relative radius of 16% chord length is considered as well as a 3D leading edge bulb-configuration designed at TU Dresden. The results are discussed in terms of iso-Mach surfaces, secondary flow patterns and spanwise incidence and turning. A complex 3D vortex system rises from the fillet radius, which improves the aerodynamic behaviour of the cascade at the end-wall section. With the bulb configuration the suction surface horse-shoe vortex leg was demonstrated to weaken the undesirable cross flow and by that to reduce the hazard of corner stall.