Aerodynamic Design of  a Part-Span Tandem Bladed Rotor for Low Speed Axial Compressor

Roy, Bishnupada; Mulmule, Aditya; Puranam, Srivatsava

doi:10.2514/6.2009-3964

Cited by 9 publications

(4 citation statements)

References 2 publications

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“…Earlier researches on tandem blades mostly focused on the overall performance of single-stage or multistage tandem compressors (Bammert and Staude 1980;Wennerstrom 1990). In the recent years, Roy et al (2009) has investigated behaviour of the tandem structure applied to the partial blade height of a compressor rotor, and the aerodynamic performance of the compressor has been significantly improved. Liu et al (2021) changed the rotor and stator of a single-stage compressor to the tandem structure, and experiments have proved that the tandem design significantly improves the compressor load and efficiency.…”

Section: Fig 1 Comparison Of Two-dimensional Flow Characteristics Bet...mentioning

confidence: 99%

Research on the Influence of Inflow Conditions on the Aerodynamic Performance of a Tandem Cascade

Yang

Liu

Mao

et al. 2022

JAFM

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We perform a thorough numerical analysis of the impact of inflow conditions on the aerodynamic performance of a tandem cascade. In particular, we investigate the effects of the incidence angle and the inlet boundary layer (IBL) thickness on the three-dimensional flow field structure and aerodynamic performance. Our results show that the gap flow strength of the tandem cascade decreases with the increase of incidence angle, and it can effectively reduce the mixing of the wakes of the forward blade (FB) and rear blade (RB). In turn, this prevents the passage vortex (PV) in the RB passage from developing along the circumferential direction. The occurrence of IBL does not modify the effects of the incidence angle on the tandem cascade, however, it reduces the load of the RB and the gap flow strength near the endwall. Under all incidence angles, IBL increases the total pressure loss of the tandem cascade, and decreases the static pressure rise (except for an incidence angle equal to -6°). The maximum loss increment is at 2° incidence angle, and the maximum static pressure rise decrement is at 6° incidence angle (Thick-IBL condition) or 7° incidence angle (Thin-IBL condition). Furthermore, we found that the presence of IBL changes the minimum loss condition from 0° (design condition) to -2° incidence angle. Our results thus indicate that in the practical engineering application of the tandem cascade, the reality that IBL degrades the tandem cascade performance in the full incidence angle range should be considered. And the strong endwall secondary flow effect caused by IBL should be considered in the tandem cascade threedimensional design, so that the tandem cascade two-dimensional performance advantage can be better played.

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Section: Fig 1 Comparison Of Two-dimensional Flow Characteristics Bet...mentioning

confidence: 99%

Research on the Influence of Inflow Conditions on the Aerodynamic Performance of a Tandem Cascade

Yang

Liu

Mao

et al. 2022

JAFM

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“…Shan et al carried out simulations on tandem cascades for six different percent pitches, and found that the total pressure recovery coefficient is increased if the vane geometry is carefully and reasonably designed [21]. Roy et al conducted aerodynamic design and experimental studies on tandem cascades in low-speed axial compressors [22]. The study indicated that the tandem cascade is more affected by the circumferential distance than the axial distance.…”

Section: Introductionmentioning

confidence: 99%

Performance Enhancement of a Centrifugal Compressor by Designing a Tandem Cascade Diffuser

Zhang

Yang

et al. 2022

Energies

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The performance of a vane diffuser plays an important role in transforming the high kinetic energy into pressure energy at the impeller outlet of a centrifugal compressor. In this study, the performance enhancement of a centrifugal compressor is achieved by designing a tandem cascade diffuser. An optimum value of the total bending angle of a tandem cascade diffuser is obtained through numerical simulation. The total bending angle is defined as the angle between the tangent line of the front blade arc line at the leading edge point and the tangent line of the rear blade arc line at the trailing edge point. The range of the total bending angle increases from zero to 21°. The simulation results show that the variation of the total bending angle has a great impact on the performances of the compressor stage. The best performance is achieved by the 10° model, by which the minimum total pressure loss coefficient and the maximum static pressure recovery coefficient are obtained. The mechanism of performance improvement by choosing a reasonable total bending angle is that the separated flow zone in the diffuser is constrained and the distribution of radial velocity at the inlet and outlet of the diffuser is more uniformed. With the 10° model, the separated zone almost completely disappears in the diffuser and a distribution of more uniform radial velocity along the meridional section is obtained. Compared with the stage of the prototype with a single row of vane diffuser, the stage with the newly designed tandem vane diffuser (10° model) achieved performance improvement, the efficiency increased about 6%, and the total pressure ratio increased about 3.5% at the flow coefficient of 0.15.

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“…Roy and Saha [7][8][9] conducted their experimental study on tandem blades. They experimentally tested controlled diffusion airfoil 21-21 and 321.…”

Section: Introductionmentioning

confidence: 99%

“…Several researchers (McGlumphy 1 ; McGlumphy et al 2 ; Hasegawa et al 5 ; Roy et al 7 ; and Roy and Saha 8 ) have demonstrated the higher diffusion capability of tandem blading over the single blade. However, these investigations were primarily focused on tandem cascade or tandem stator.…”

Section: Introductionmentioning

confidence: 99%

Design and off-design behavior of a tandem rotor stage

Kumar

Pradeep

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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With an ever-increasing focus on clean and sustainable energy for transport and power, aero-engine designers need to come up with engine designs that can meet the efficiency and thrust requirements. In this aspect, compressor/fan designers always aim at designs that can result in higher pressure ratios and maximum possible efficiency with a fewer number of stages. Compressor blades, which are designed for higher diffusion, have an inherent risk of flow separation. This, therefore, fixes the upper permissible limit in terms of diffusion. If the suction surface adverse pressure gradient can be efficiently managed to avoid flow separation, it would be possible to target higher diffusion factors. One such concept for achieving this is using tandem blading. In the present computational study, a conventional low-speed compressor stage performance is compared with a tandem stage. Both designs attempt similar levels of targeted diffusion. The computational results are simulated at the design and the off-design conditions. The computational results are validated with experimental data. A high percentage pitch and low axial overlap configuration are finalized for the design of the tandem rotor based on existing literature as well as initial parametric analyses. The study shows that it is possible to achieve higher diffusion for the tandem rotor in comparison to a single rotor. The behavior of the gap-nozzle, interaction of the tip leakage with the gap-nozzle, blockage due to the tip leakage vortex, performance of stator, and performance of both stages are discussed in detail in this paper.

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Aerodynamic Design of a Part-Span Tandem Bladed Rotor for Low Speed Axial Compressor

Cited by 9 publications

References 2 publications

Research on the Influence of Inflow Conditions on the Aerodynamic Performance of a Tandem Cascade

Research on the Influence of Inflow Conditions on the Aerodynamic Performance of a Tandem Cascade

Performance Enhancement of a Centrifugal Compressor by Designing a Tandem Cascade Diffuser

Design and off-design behavior of a tandem rotor stage

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