200 likes | 211 Views
Design of Passive (Adiabatic) Control Volumes. P M V Subbarao Professor Mechanical Engineering Department. A Comprehensive Design Method for Overall Fuel Savings …. Geometric Design of Intakes & Nozzles. One–Dimensional Frictional Flow through Variable Area.
E N D
Design of Passive (Adiabatic) Control Volumes P M V Subbarao Professor Mechanical Engineering Department A Comprehensive Design Method for Overall Fuel Savings…..
Conservation of Mass Applied to 1 D Steady Flow Conservation of Mass: Conservation of Mass for Steady Flow: Integrate from inlet to exit :
One Dimensional Stead Flow A, V r A+dA, V+dV r+dr dl
Governing Equations for 1D Steady flow Non reaction, no body forces, viscous work negligible Conservation of mass for steady flow: Conservation of momentum for frictional steady flow: Conservation of energy for ideal steady flow:
Additional Equations Ideal Gas law : Mach number equation :
Wall Shear Stress & Friction Factor Convenient to write the friction induced shear force, x, in terms of a friction factor Darcy Friction Factor Hydraulic Diameter
Design Equations for 1D Steady flow Non reaction, no body forces, viscous work negligible Conservation of mass for steady flow: Conservation of momentum for frictional steady flow: Conservation of energy for ideal steady flow:
Other Equations Ideal Gas law : Mach number equation :
Design Equation for Variable Area Conduit Combine conservation, state equations– to get design equations for steady one dimensional frictional flow : So we have three ways to change the Mach number of a flow – area change (dA): – friction: f > 0, same effect as –dA – heat transfer: heating, q’’’ > 0, like –dA cooling, q’’’ < 0, like +dA
Effect of Shape of duct on Flow Consider an isentropic flow through a variable area duct: Pure shape effects :
Control of Mach Number in Subsonic Flows Subsonic Diffuser : M <1 Subsonic Nozzle: M <1 dA < 0 dA > 0 So, dV > 0 & dp <0 So, dV < 0 & dp>0
Control of Mach Number in Supersonic Flows Supersonic Nozzle Supersonic Diffuser dA < 0 & M >1 So, dV < 0 & dp >0 dA > 0 & M >1 So, dV >0 & dp<0
Generation of High Pressure from Supersonic velocity : Isentropic Devices
Occurrence of Maximum Allowable Velocity Section At M =1 Minimum Area = A* : Also called throat For a given mass flow rate: