Development of New Casing Treatment Configuration

Liu

et al. 2021

JAFM

The development of high-performance aero engines put forward higher performance requirements for compressor components, and the improvement of aerodynamic performance of compressors has important engineering application value. The blade tip recess has great potential and advantages in improving the aerodynamic performance of compressors. In order to better understand the effect of the blade tip recess on the compressor aerodynamic performance, in this paper, the influence mechanism of the blade tip recess on the aerodynamic performance of the isolated rotor of a transonic axial compressor stage is discussed. Under the premise that the numerical method's results are almost consistent with the experimental test results, the full three-dimensional unsteady numerical results show that the main reason for the original blade rotor stall is the leading edge of the blade tip blockage, which is caused by blade tip clearance leakage vortex breakage. After adopting the measures of the blade tip recess, the study shows that the blade tip recess can increase the rotor stall margin by 2.10% without reducing the rotor efficiency and the total pressure ratio. A detailed analysis of the blade tip flow field shows that the blade tip recess can reduce the intensity of the tip clearance leakage flow by increasing the turbulence intensity of the blade tip near the casing wall, and reduces the leading edge of blade tip blockage, improves the rotor blade tip flow field, thereby achieving the purpose of enhancing rotor stability.

Section: Introductionmentioning

confidence: 99%

Investigation on the Mechanism of Blade Tip Recess Improving the Aerodynamic Performance of Transonic Axial Flow Compressor

Liu

et al. 2021

JAFM

“…But adopting the passive control methods while improving the SM of the compressor often causes the compressor efficiency to drop. [3][4][5][6][7][8][9][10][11][12][13] The blade tip recess (BTR) was used on the turbine blade to cool the turbine blade; it has been widely used and studied on the turbine blade. [14][15][16][17][18][19][20] While the application and research of the BTR on the compressor blade is relatively less, Gourdain and Leboeuf 21 conducted a study on the BTR to suppress the compressor rotating stall in the subsonic axial compressor and found that the BTR can increase the turbulent intensity near the casing and improve the SM of the compressor.…”

Section: Introductionmentioning

confidence: 99%

Investigation on the influence of the structure parameters of blade tip recess on the performance of axial flow compressor

Proceedings of the Institution of Mechanical Engineers, Part G:

2021

As one of the important components of an aero engine, the compressor plays an important role in improving the performance of the aero engine. The blade tip recess (BTR) has great potential and advantages in improving the performance of the compressor. It is very important to clarify the influence of the structure parameters of the BTR on the performance of the compressor. In this study, the two-dimensional results of the BTR were analyzed by using the method of variance analysis, and the two-dimensional calculation results of the BTR were used to guide the design of the BTR of axial flow compressor rotor. In the NASA Rotor 35, the influence rules of the structure parameters of BTR on the recess effect that was basically the same as the two-dimensional conditions. The optimization of the rotor BTR structure parameters may be achieved by the two-dimensional calculation. The flow field analysis showed the BTR can retard the growth rate of the blockage area of the leading edge of blade tip by weakening the tip clearance leakage flow intensity that delayed the occurrence of blade tip blockage and improved the aerodynamic stability of the rotor.

“…At present, the main casing treatment technologies include the circumferential groove casing treatment, the axial slot casing treatment, the self-circulating casing treatment (SCT), and so on. In the past scholars' research, Hembera et al 3 summarized and analyzed the research on the circumferential groove casing treatment done by Bailery et al [4][5][6][7][8][9][10][11][12] and found that while the casing treatment improves the stable working margin of the compressor, it is almost at the expense of compressor efficiency, and the efficiency loss is about 0.10-1.01%.Wilke and Kau 13,14 have done a lot of research on the improvement stability effect and mechanism of the casing treatment on different compressor models. The research mainly focuses on the circumferential groove casing treatment and the axial slot casing treatment on a transonic front stage of a modern high pressure compressor.…”

Section: Introductionmentioning

confidence: 99%

Influence of self-circulating casing treatment with double-bleed ports structure on compressor performance

Proceedings of the Institution of Mechanical Engineers, Part G:

2020

Casing treatment is an effective way to improve the stable working margin of the compressor and plays an important role in ensuring the stable and safe work of the compressor. On the premise that the numerical results are in agreement with the experimental values, the paper study on a new type of the self-circulating casing treatment with double-bleed ports structure was carried out on the NASA rotor 37 by numerical simulation. It is found that compared with the self-circulating casing treatment with single-bleed port structure, the self-circulating casing treatment with double-bleed ports structure is more favorable for improving the stall margin of the rotor, and the improvement of the stall margin obtained at the rotor design speed is as high as 9.57%. Compared with the other two self-circulating casing treatments with single-bleed port structure, the improvement of the stall margin is increased by 37.90 and 49.53%, respectively. The self-circulating casing treatment with double-bleed ports structure has a significant effect on the enhancing stability, but at the same time, it causes a greater efficiency loss, which reduces the design point efficiency of the rotor by 0.34%. Through detailed analysis of the flow field, it is found that the self-circulating casing treatment improves the flow capacity of the blade tip region, weakens the blockage degree of the blade tip region, and reduces the blade tip load, thereby improving the stall margin of rotor. Compared with the self-circulating casing treatment with single-bleed port structure, the self-circulating casing treatment with double-bleed ports structure is more advantageous for delaying the flow separation of the suction surface, delaying the occurrence of the blade tip stall to make the stability of rotor more favorable, and obtained stall margin improvement is the greatest.