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Sumanta Acharya layer and interacts with the boundary layer fluid downstream of the hole. Thus, the coolant jets significantly influence the endwall pressure field and the cross-pitch flow in the blade passage. As the coolant jets also interact with the vortex flows, especially with the pressure side leg vortex and suction side leg vortex along the separation line, the secondary flow dynamics changes along with the total pressure losses across the passage. As mentioned in the beginning of Section 4.3-7 that the coolant film is lifted away from the endwall by these vortices, the separation lines in the passage is sometimes termed as the “lift- off” line. The physics of mixing and diffusion of the jets in the boundary layer and interactions between a coolant jet and the boundary layer or the vortices are frequently complicated by the action of neighboring coolant jets. Such physics are studied under the subject of “Jets in Cross Flow” and hence, will not be discussed here. The primary objective of this section is to discuss the effects of the film injection on the secondary flow field and not the dynamics of the jets. The arrangement of the coolant holes in figure 35 is expected to provide coverage for the entire passage endwall and hence, sometimes is termed as the full-coverage film cooling. The effective coverage of the endwall by the coolant depends on various factors like injection angle, coolant hole orientation, coolant hole shape, hole size, L/D ratio, relative locations of the holes, and mass flux or local blowing ratio from individual hole. These are also the fundamental characteristics of the coolant holes and must all play the role together when the coolant holes are employed. The local blowing ratio is defined as the ratio of the mass flux of the coolant to the mass flux of the passage flow. It is not always easy to measure the mass flux of individual holes with accuracy. Thus, an inlet blowing ratio, Minlet is defined based on coolant flow through an idealized, loss free hole at the passage inlet condition65. P−P o, plenum o,inlet M inlet = 0,inlet inlet P−P Here, Po,plenum is the stagnation pressure of the coolant supply plenum, Po,inlet is the stagnation pressure at the passage inlet, and Pinlet is the static pressure at the passage inlet. The boundary layer is energized and strengthened with the properly ejected coolant jets. This enables the boundary layer fluid to withstand the pitchwise pressure gradient in the passage and cross-pitch flow is weakened as a consequence. Thus, with proper design and configuration the endwall film injection can also provide an effective structural modification that reduces the secondary flows and aerodynamic losses. It is difficult to generalize the flow field at the endwall when the coolant jets are ejected. Each geometric configuration and flow parameter associated with the coolant holes just mentioned can alter the endwall boundary layer uniquely. On the other hand, the secondary and cross flows affect the coolant jets. The illustrations that are going to be presented next do not represent a typical behavior of the near wall flow. The readers will have some understanding about the relative importance of the coolant jet configuration and secondary flows. Fig. 36. Coolant jet locations downstream of injection holes in a linear vane passage. Source: See Note 66. Figure 36 shows the measured locations of the coolant jets as they travel downstream from their ejection points in a linear vane passage66. The configuration of the coolant holes is also shown in the figure. The holes are ejecting at 35 degree 383 with respect to the endwall surface. Data are presented nearPDF Image | Turbine Blade Aerodynamics
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