Effect of Coolant Flow Distribution on Transient Side-Load of Film Cooled Nozzles

A numerical study is performed to study the effect of nozzle wall cooling on transition between two different shock structures such as free shock separation and restricted shock separation in an axisymmetric thrust-optimized contour nozzle. In this study, cooling of nozzle wall which is associated to the first half of nozzle length is concerned, and at different cooling rates, the transition between shock structures, hysteresis cycle, and also plateau pressure ratio at which the transition occurs are characterized. To do this, a two-dimensional numerical calculation is accomplished utilizing the commercial CFD software, FLUENT. Validity of current numerical model is confirmed by comparison of nozzle wall pressure, hysteresis cycle, and plateau pressure ratio with experimental and previously published works as well as applying simple energy balance. Numerical results show that the increase in cooling rate causes the transition between shock structures and thus hysteresis cycle to appear at lower values of pressure ratio. It is found that, in the case of nozzle wall cooling, a single point could be realized for transition between shock structures. It is also shown that the effect of nozzle wall cooling is to reduce the plateau pressure ratio at which the transition happens.

show abstract

Transient Side-Load Analysis of Out-of-Round Film-Cooled Nozzle Extensions

Wang

Lin

Guidos

2013

Journal of Propulsion and Power

Self Cite

View full text Add to dashboard Cite

scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.

Contact Info

customersupport@researchsolutions.com

10624 S. Eastern Ave., Ste. A-614

Henderson, NV 89052, USA

Blog Terms and Conditions API Terms Privacy Policy Contact Cookie Preferences Do Not Sell or Share My Personal Information

Made with 💙 for researchers

Part of the Research Solutions Family.

Effect of Coolant Flow Distribution on Transient Side-Load of Film Cooled Nozzles

Cited by 8 publications

References 24 publications

Computational investigation of flow separation in a thrust-optimized parabolic nozzle during high-altitude testing

Computational investigation of flow separation in a thrust-optimized parabolic nozzle during high-altitude testing

Numerical study of wall cooling effects on transition between shock structures in a rocket propulsion nozzle

Transient Side-Load Analysis of Out-of-Round Film-Cooled Nozzle Extensions

Contact Info

Product

Resources

About