The Impact of Forward Swept Rotors on Tip-Limited Low-Speed Axial Compressors

McNulty, G. Scott; Decker, John J.; Beacher, B. F.; Khalid, S. Arif

doi:10.1115/gt2003-38837

Cited by 10 publications

(28 citation statements)

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“…On the basis of references [29] and [30], one may assume that NRS causes no reduction but spanwise redistribution of losses, as formulated in reference [31]. The above are in accordance with the comment in reference [8] that it is impossible to generalize how FSW (and similarly, FSK) impacts performance for all blading types. This literature overview suggests the complexity of performance and efficiency modifying effects due to FSW/FSK.…”

Section: Introductionmentioning

confidence: 65%

“…3). Such effect is recognised for a tip-FSK rotor in reference [23], and appears also for tip-FSW in reference [8]. Such rotor inlet flow modification effect is detectable for FSK rotors in reference [16], for both BSW blade root and FSW blade tip in references [24], [36], and [37], and for a strongly FSW rotor in reference [19].…”

Section: Rotor Inlet Flow Modification Due To (1)swmentioning

confidence: 96%

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Aerodynamic effects of blade sweep and skew in low-speed axial flow rotors at the design flow rate: An overview

Vad

2008

Proceedings of the Institution of Mechanical Engineers, Part A:

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A detailed literature survey is presented herein in order to overview the aerodynamic impact of non-radial blade stacking techniques applied to axial flow fan and compressor rotors. The literature suggests a consensus that forward blade sweep and skew provides a means for the following advantages in the part load operational range of low-speed axial flow turbofan and compressor rotors: improvement of efficiency and performance, and extension of stall-free operating range. However, the published research results are rather diversified regarding the judgment of performance and loss modifying effects of sweep and skew at the design point. The current paper summarizes the major aerodynamic phenomena related to such blade stacking techniques, in order to contribute to a general reasoning of performance and efficiency modification at the design flow rate. Furthermore, it provides guidelines how to consider these phenomena in tailoring the blade geometry for potential efficiency gain and for achievement of the prescribed total pressure rise at the design point. The role of adequate computational fluid dynamics tools was considered in the paper to be essential in evaluation of aerodynamic effects of non-radial blade stacking, as well as in incorporation of sweep and skew in systematic blade design techniques.

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Section: Introductionmentioning

confidence: 65%

Section: Rotor Inlet Flow Modification Due To (1)swmentioning

confidence: 96%

Aerodynamic effects of blade sweep and skew in low-speed axial flow rotors at the design flow rate: An overview

Vad

2008

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…Forward sweep was among the various geometrical features implemented in this design. Its effect was described by Mac Nulty et al [10] and Domercq [11] among others. The main impact of forward sweep on subsonic rotors is that it modifies the spanwise flow distribution by pulling part of the massflow towards tip region compared with a radially stacked conventional blade.…”

Section: Analysis Of the Three-dimensional Flowmentioning

confidence: 87%

Tip clearance effect on high-pressure compressor stage matching

Domercq

Escuret

2007

Proceedings of the Institution of Mechanical Engineers, Part A:

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Tip clearance flows have a major impact on both performance and stability of high-pressure compressors (HPC). The purpose of this paper is to underline how tip clearance variations affect the matching of compressor stages, hence modifying the efficiency and stall margin of the compressor. The practical application covered by the scope of this article is a modern highly loaded HPC dedicated to civil aircraft propulsion.The first part of the paper gives a very simple overview of stagewise matching in multistage compressors. Also, this part introduces the subject of the impact of tip clearance on stage matching.The second part of the paper illustrates the effect of increased rear block clearances on performance and stability, using some available experimental data. Finally, it is shown that three-dimensional multi-stage calculations can predict the effect of tip clearance variations on stage pressure-rise characteristics and on stage matching. This validated numerical tool therefore allows the aerodynamic design to be adjusted to the range of in-service clearances, thus providing a more robust compressor design.

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“…Corsini & Rispoli [10] also thought that the fore-swept can reduce the flow loss. In document [11], the influence of forward-swept blade on the gaps flow was studied. It is considered that the swept blade increased the stall margin and reduced the flow loss in the cascade passage.…”

Section: Introductionmentioning

confidence: 99%

Axial-Swept Influence on Inner Flow Performance of HP Steam Turbine Based on CFD

Feng

Guo

Wei

et al. 2019

Mathematical Problems in Engineering

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Swept blade technology was used to redesign the supercritical steam turbine sets that could improve the inner-efficiency of turbine sets and decrease the consumption of coal the noxious gas such as NOx. The eighth high-pressure stages, including static and rotor cascades, were selected as tested prototypes that were blew in the low-velocity wind tunnel. We used the five-hole ball head needle to measure the aerodynamic parameters distribution along the width and span direction of the high-pressure stage cascades. With the inkblot display technology, the limit flow spectrums were displaced in the blade surface and the endwalls. These tested data could be used to check the simulation results of CFD software. To improve the efficiency of the steam turbine high-pressure (HP) stage, we selected the supercritical steam turbine HP stage cascade blade as the prototype to research into its inner flow performance of the axial-swept blade by the CFD software. Two different redesigned blades, with ±20°, swept angle, and 30% swept height, named axial fore-swept and axial aft-swept, were built up. The stage passages flow field of the prototype blade, and the two redesigned swept blades were simulated using CFD software with stage interface planes between the stages. The CFD simulation results indicated that the leading edge of swept blades influenced the inlet flow field; the pressure in aft-swept blade stage in both endwalls was higher than in the middle and was beneficial to improve the passage flow properties of HP stage. But for the fore-swept HP stage, its pressure distribution was lower in both endwalls than in the middle and not beneficial to passage flow.

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The Impact of Forward Swept Rotors on Tip-Limited Low-Speed Axial Compressors

Cited by 10 publications

References 0 publications

Aerodynamic effects of blade sweep and skew in low-speed axial flow rotors at the design flow rate: An overview

Aerodynamic effects of blade sweep and skew in low-speed axial flow rotors at the design flow rate: An overview

Tip clearance effect on high-pressure compressor stage matching

Axial-Swept Influence on Inner Flow Performance of HP Steam Turbine Based on CFD

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