Experimental Investigation of a Forward Swept Rotor in a Multistage Fan with Inlet Distortion

Wadia, A. R.

doi:10.1155/2011/941872

Cited by 8 publications

(4 citation statements)

References 10 publications

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“…The flow field analysis showed that the positive curved stator improved the flow field in the distortion region, but it increased the friction loss in the non-distorted region due to the increase of curved blade surface area. Wadia et al 17 reported that the forward swept rotor presented a superior aerodynamic performance and tolerance to the non-uniform inflow.…”

Section: Introductionmentioning

confidence: 99%

Effect of three non-axisymmetric stator schemes on compressor performance with distorted inlet

Sun

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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In the boundary layer ingesting propulsion system, the compressor suffers from a non-uniform flow field. The compressor operating with distorted inflow continuously results in the loss of aerodynamic performance and stability margin. In this paper, three non-axisymmetric configurations are described for the stator of a transonic compressor to match the non-uniform flow field. The flow fields with distorted inflow at near stall condition are obtained and analyzed, the effects of the prototype stator and the three non-axisymmetric stators on aerodynamic performance are compared in detail. Results show that the non-axisymmetric stator schemes can effectively improve the stability margin of the transonic compressor and the maximum stability margin is relatively increased by 22.3% in all the three non-axisymmetric stators. The non-axisymmetric stator design is effective on decreasing the aerodynamic losses and improving the performance of the compressor operating with distorted inflow. Overall, the results show that in the design of the non-axisymmetric stator, the adoption of a curved-twisted blade and the increase of cascade solidity have the potential to reduce loss sources caused by distorted inflow.

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Section: Introductionmentioning

confidence: 99%

Effect of three non-axisymmetric stator schemes on compressor performance with distorted inlet

Sun

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Also, inflow distortion exacerbates the high cycle fatigue of the blade in the compressor (Engeda et al, 2003;Zemp et al, 2010). Wadia (2011) conducted a pilot of the performance of a forward-swept rotor in a multi-stage compressor under inflow distortion and found that the inlet guide vane row reduced the sensitivity of the multi-stage compressor to inflow distortion; moreover, it augmented the vibration amplitude of the blade. Gunn et al (2013) developed full-annulus experimental measurements of the flow field in a low-speed fan stage operating with a continuous 60-degree inlet stagnation pressure distortion.…”

Section: Introductionmentioning

confidence: 99%

Dynamic flow behavior and performance of a reactor coolant pump with distorted inflow

Fan

Guo³

et al. 2020

Engineering Applications of Computational Fluid Mechanics

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In the operation of a nuclear plant system, a distorted inflow of a reactor coolant pump appears owing to the steam generator channel head and multi-bend, leading to the deterioration of pump performance and stability. In the present study, three-dimensional numerical calculations of three model geometries are carried out using block grid technology, with RNG kand DDES model applied in the steady and transient simulation. The simulation results are validated with an experiment testing the pump with a short inlet pipe. As for the results, under the distorted inflow condition, the pump head and efficiency are reduced by 4% and 5.2% respectively at the nominal flow rate. Additionally, when the pump is coupled with upstream structures, the inlet flow becomes distorted and more chaotic, and the swirl and radial flow are produced by asymmetric pressure difference. Meanwhile, a pair of local vortices appears in the inlet section, forming re-distributed mass flow rates. As the distorted flow enters the pump, the blade inlet pressure and flow rate are unevenly distributed. Moreover, the evolution process of the vortex is accompanied with strong non-uniformity in the impeller channel, and thus asymmetric tangential force is imposed on the blades, increasing the risk of the fatigue breakdown of the impeller.

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“…Passive control of inlet distortion can be implemented with casing treatment (Prince et al, 1975;Smith and Cumpsty, 1984) or blade modification (Wadia et al, 2002). Active control methods for inlet distortion include tip injection, bleeding of flow and the application of variable inlet guide vane (VIGV) (Wadia, 2011). Both tip injection and bleeding can improve the stall margin with inlet distortion when stall is initiated at the tip, though bleeding is relatively less effective as compared with injection (Koch, 1970).…”

Section: Introductionmentioning

confidence: 99%

Investigation of the Tip Injection for Stall Control in a Transonic Compressor with Inlet Distortion

Zhang¹,

Vahdati²

2020

Proceedings of Global Power &Amp; Propulsion Society

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Experimental studies have shown that tip injection upstream of the rotor can extend its operational range when subjected to circumferential inlet distortion. Typically, injectors are placed uniformly around the annulus. However, such arrangement consumes a large amount of high-pressure air and decreases the overall efficiency of the compression system. The aim of this paper is to minimise the amount of the injected air by determining the most effective circumferential location for the injector. In this study, NASA stage 35 was used as the test case. The experiment was conducted with a circumferential total pressure distortion of 120 degrees. In the first part of this paper, numerical simulations were compared against the experimental data and good match was obtained. In the second part, tip injection at three different positions were tested: the clean flow region (Position 1), the distorted region (Position 2) and the border between the clean and distorted regions (Position 3). It was found that a mild injection (0.66% of the main flow) at Position 2 and Position 3 can extend the stall margin by 1.8% and 2.7%, respectively. No obvious improvement was observed for the injection at Position 1. With a larger injection of 1.5% of main flow at Position 3, the stall margin improved further with no efficiency loss.

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Experimental Investigation of a Forward Swept Rotor in a Multistage Fan with Inlet Distortion

Cited by 8 publications

References 10 publications

Effect of three non-axisymmetric stator schemes on compressor performance with distorted inlet

Effect of three non-axisymmetric stator schemes on compressor performance with distorted inlet

Dynamic flow behavior and performance of a reactor coolant pump with distorted inflow

Investigation of the Tip Injection for Stall Control in a Transonic Compressor with Inlet Distortion

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