isentropic expansion वाक्य
उदाहरण वाक्य
मोबाइल
- The results are sometimes also known as the isentropic expansion factor.
- It is sometimes also known as the isentropic expansion factor.
- The high-pressure steam then undergoes an isentropic expansion in a conventional steam turbine.
- "' Isentropic expansion "'waves are created when a supersonic flow is redirected along a curved surface.
- An example of such an exchange would be an isentropic expansion or compression that entails work done on or by the flow.
- The Otto cycle consists of isentropic compression, heat addition at constant volume, isentropic expansion, and rejection of heat at constant volume.
- This is the ratio of the blade velocity and the isentropic gas velocity that would be obtained in its isentropic expansion through the stage pressure ratio.
- With an air pressure of only 40 bar ( 4 MPa ), Claude achieved an almost isentropic expansion resulting in a lower temperature than had before been possible.
- The refrigerant liquid flows through the turboexpander where it is vaporized and the vapor undergoes an isentropic expansion which results in a low-temperature mixture of vapor and liquid.
- The resulting high-pressure vapor flows to the turboexpander where it undergoes an isentropic expansion and exits as a vapor-liquid mixture which is then condensed into a liquid by heat exchange with the available cooling medium.
- I think the anwers above are unclear, the throttling explanation seems to be about the temperature of the exiting gas after expansion, the question was about the temperature of the can and that has more to do with boiling and maybe isentropic expansion . talk ) 00 : 21, 20 May 2010 ( UTC)
- The gas stream from the gas-liquid separator enters the turboexpander where it undergoes an isentropic expansion from an absolute pressure of 62 bar to 21 bar ( 6.2 to 2.1 MPa ) that lowers the gas stream temperature from about " 51 �C to about " 91 �C as it enters the demethanizer to serve as distillation reflux.
- As an example calculation using the above equation, assume that the propellant combustion gases are : at an absolute pressure entering the nozzle " p " = 7.0 MPa and exit the rocket exhaust at an absolute pressure " p " e = 0.1 MPa; at an absolute temperature of " T " = 3500 K; with an isentropic expansion factor " ? " = 1.22 and a molar mass " M " = 22 kg / kmol.
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