Control and Entropy Analysis of Corner Flow Separation in a Compressor Cascade Using Streamwise Grooves

Yi, Weilin; Ji, Lucheng

doi:10.3390/e21100928

Cited by 9 publications

(3 citation statements)

References 38 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Because the mixing effect between the fluids in the leakage flow cannot be ignored, it is inaccurate to analyze the details of leakage flow with this coefficient. Yoon et al [27] suggested that entropy (s) is a better method to solve the problem, and in the literature [28,29], the entropy analysis method was used to analyze the flow field of cascade with severe flow separation. Then, the detailed comparative study The traditional total pressure loss coefficient used in cascade analysis does not consider the partial loss caused by the temperature change when analyzing the detailed flow field.…”

Section: Resultsmentioning

confidence: 99%

Control and Entropy Analysis of Tip Leakage Flow for Compressor Cascade under Different Clearance Sizes with Endwall Suction

Zhang

Liu

Han

et al. 2020

Entropy

View full text Add to dashboard Cite

To investigate the influence of the change of tip clearance size on the control effect of the endwall suction, the effects of endwall suction on the aerodynamic performance of the axial compressor cascade were studied numerically. Three tip clearance sizes of 0.5% h, 1.0% h, and 2.0% h (h is the blade height) were mainly considered. The results show that the endwall suction scheme whose coverage range was 8–33% axial chord can reduce the leakage flow and improve the aerodynamic performance by directly influencing the structure of tip leakage vortex. The overall total pressure loss coefficients of the three clearance size schemes at 0° angle of incidence with 0.4 inlet Mach number are reduced by about 10.3%, 10.8%, and 6.0%, respectively, at the suction flow rate of 0.7%. Under the same suction flow rate, the onset position of the tip leakage vortex of the cascade with small clearance is shifted from the 15% of the axial chord length of original to the 48% of the axial chord length, which with large clearance is nearly no changed. The leakage flow rate and the distance from the leakage vortex to the suction slot are the main reasons for the different control effect of the endwall suction under different tip clearance sizes. The difference of the spanwise distribution of flow field parameters may also cause the difference of flow control effect.

show abstract

Section: Resultsmentioning

confidence: 99%

Control and Entropy Analysis of Tip Leakage Flow for Compressor Cascade under Different Clearance Sizes with Endwall Suction

Zhang

Liu

Han

et al. 2020

Entropy

View full text Add to dashboard Cite

show abstract

“…It was also found that the secondary flow in the turbine rotor is completely different from that in a stator due to the distortion in the incoming flow. Yi and Ji [20] studied the entropy generation in a compressor cascade by RANS CFD and found a high-loss zone in the suction-hub corner near the trailing edge.…”

Section: Introductionmentioning

confidence: 99%

Entropy Generation of Secondary Flow in a Turning Passage with Different Boundary Layer Characteristics

Xia

et al. 2022

Aerospace

View full text Add to dashboard Cite

The development of secondary flow along a curved channel is a fundamental flow phenomenon occurring in a wide range of engineering applications, including turbomachinery, aerospace, heating, ventilation, air conditioning, etc. The underlying flow physics about end-wall secondary flows has been well-documented in the open literature, while the interaction between a secondary flow and a side-wall boundary layer, which is critical to the aerothermal performance of a side-wall surface, has not been comprehensively studied. In this study, the entropy generation of secondary flow and the interaction between an end-wall passage vortex and a side-wall boundary layer were numerically investigated by Reynolds-averaged Navier–Stokes (RANS) CFD for a 90° curved channel. The transportation effect of secondary flow and the generation mechanism of an induced vortex pair on the side wall is reported. It was also found that the growth of the secondary flow can be suppressed due to the displacement effect of the side-wall boundary layer. Furthermore, it was found that the interaction between a secondary flow and a side-wall boundary layer provides a suppression effect on side-wall boundary layer separation.

show abstract

“…As summarized by Wennerstrom [3], slots might be expected to have some positive benefit only at lower aspect ratios and lower Mach numbers; slots at mid-span could show relative effectiveness and slots near the end walls demonstrated ineffectiveness, which was mainly attributed to their inability to reduce the large secondary flows in the wall regions. Since then, many efforts for flow control were carried out to improve performance in highly loaded compressors using various methods, such as boundary layer aspiration [11][12][13], plasma [14,15], fluidic actuators [16], synthetic and continuous jets [17], vortex generator jets [18,19], Coanda jet flaps [20], whole span slot [21], leading-edge tubercles [22], endwall fence [23], vortex generator [24], blended blades with endwall contouring [25], and streamwise grooves [26]. However, these methods have not been widely used due to requirements of additional devices or limitations of operating range.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Investigation of Datum and Slotted Blade Profiles under Different Mach Number Conditions

Tang

Liu

2020

Energies

View full text Add to dashboard Cite

Mach number effects on loss and loading are evaluated in both the datum and slotted compressor profiles under a wide range of incidences based on two-dimensional (2D) computational fluid dynamic (CFD) simulations. First, total pressure loss and loading abilities are compared. Then, three kinds of deficit thickness are defined and evaluated, and a correlation is made between the loading and the momentum deficit thickness at the profile trailing edge. Finally, the nondimensionalized destruction of mean mechanical energy and dissipation function are employed to analyze the loss mechanism. The slotted profile broadens the low loss range towards the positive incidence range. The slotted profile allows a higher diffusion factor (DF) than the datum profile. It is hard to distinguish failure simply based on the DF values, whereas the Zweifel loading coefficient connects well with the low momentum deficit in the profile trailing edge. The peak of the V-shaped distributions in the Ψ - θ d e f plot could better suggest the design condition and determine the correct operating range despite the occurrence of bulk separation. The slotted profile gains the ability of the boundary layer flow near the suction surface to resist the adverse pressure gradient, hence, a reduced shear thickness and a uniformed downstream flow field is obtained.

show abstract

Control and Entropy Analysis of Corner Flow Separation in a Compressor Cascade Using Streamwise Grooves

Cited by 9 publications

References 38 publications

Control and Entropy Analysis of Tip Leakage Flow for Compressor Cascade under Different Clearance Sizes with Endwall Suction

Control and Entropy Analysis of Tip Leakage Flow for Compressor Cascade under Different Clearance Sizes with Endwall Suction

Entropy Generation of Secondary Flow in a Turning Passage with Different Boundary Layer Characteristics

Aerodynamic Investigation of Datum and Slotted Blade Profiles under Different Mach Number Conditions

Contact Info

Product

Resources

About