blade passage मीनिंग इन हिंदी

उदाहरण वाक्य

1. The ratios of the flow rate ( q / q ) are 1 . 4 1 . 0 0 . 6 respectively . three blade - to - blade passage and the three cross - section along the axial direction at each of the passages were selected for measurements
2. The hub leakage flows were modeled and calculated in two different ways : the flow fields inside hub axial gap were calculated together with blade passage flow in an integrated manner , and the leakage flows due to the hub axial gap were modeled as inlet boundary conditions
3. One cooling method that has gained increasing importance is endwall film - cooling , where coolant air is discharged though discrete holes in the inner and outer endwalls of a turbine blade passage . after leaving the holes , the coolant forms a protective layer between the hot mainstream gas and the surface that is to be protected
4. Measured hole mass flows and a constant static pressure mixing analysis , together with the measured losses , allowed the decomposition of the losses into three distinct entropy generation mechanisms : loss generation within the hole , loss generation due to the mixing of the coolant with the mainstream , and change in secondary loss generation in the " blade passage
5. In this paper , based on the navier - stokes equation and the k - turbulent model , the numerical simulation of the 3d turbulent flow in a centrifugal impeller , of which specific speed is 93 . the distribution of the velocity and pressure in the blade - to - blade passage are presented at the design and off - design operating conditions . the simulation results were verifiable with the results measured by piv
6. The effect of leakage flow due to the upstream hub axial gap on the rotor performance and the mechanism of interaction between the hub leakage flow and the rotor blade passage flow were studied based on the numerical simulations of the flow fields of a transonic compressor rotor with upstream hub leakage
7. Results from this investigation show that the loss generation within the coolant holes is substantial and that ejection into regions of low static pressure increases the loss per unit coolant mass flow . the results also reveal strong interactions between endwall coolant ejection and secondary flow in the blade passage . the secondary flow has a strong influence on coolant trajectories and coolant ejection delays the three - dimensional separation of the inlet boundary layer on the endwall , chang the secondary flow and reduces its associated losses