请以SCI的标准帮我润色下面这段话：Combined with the magnified curve of 2% chord length of the leading edge of blade suction in Fig. 18, it is found that in the three characteristic blade height sections, the notch damage occurring in the range of characteristic blade height sections intensifies the intensity of the suction peak at the leading edge of the blade compared to the normal blade.  This is because the blunt deformation of the leading edge of the notched blade leads to a curvature maximum point at the connection between the leading edge and the blade body, which leads to an increase in the distance of the airflow along the blunt profile, and the airflow undergoes a local acceleration, resulting in a stronger suction peak phenomenon. In the height range of the blade without notch, the strength of the suction peak at the leading edge of the blade will be slightly weakened compared with the normal blade. As shown in Fig. 19, the radial distribution of gas flow density at the leading edge of the blade for different blade models, due to the notch damage will form a blunt structure, so the direction of the incoming gas in the region of the notch will be changed, and the flow rate of the gas through the region will be reduced compared with that of the normal blade, which leads to a weakening of the gas flow capacity in the region where the notch exists.  This part of the fluid that changes direction will move towards the blade height region where the notch does not occur, increasing the flow rate in the leaf height region where the notch does not occur, so that the reverse pressure gradient on the suction surface at the leading edge of the blade in this region is weakened, and the corresponding strength of the suction peak at the leading edge of the blade is also slightly weakened. In addition, it is observed that if the gas flow capacity in the region is enhanced, it will also cause the position of the surge on the blade surface to be delayed by a small amount, but this will not affect the overall decreasing trend of the static pressure coefficient on the blade surface. By comparing the distribution of blade surface static pressure coefficients along the chord length for different blade heights, it is found that the degree of decrease of blade suction and pressure surface static pressure coefficients is more obvious when notching occurs at the tip and the middle of the blade leading edge than when notching occurs at the root of the blade leading edge, which also proves the conclusion drawn above--among blade leading edge notching damages, notching occurs at the root of the blade leading edge to make the compressor aerodynamic performance degradation to the weakest extent. In addition, over the full range of blade heights, notching at the tip of the leading edge of the blade leads to the sharpest drop in static pressure coefficient at 20% of the chord length of the leading edge in front of the blade pressure, as observed in Fig. 18. Combining Figures 18 and 19, it can be deduced that when the gas flow rate increases, the notching at the tip of the leading edge of the blade causes more gas separation loss at the leading edge of the pressure. To a certain extent, it proves that when the flow rate increases, the notch at the tip of the leading edge of the blade will aggravate the flow loss of the compressor and cause the greatest degradation of the aerodynamic performance of the compressor.