STUDY OF EQUIVALENCE RATIO AND PROPELLANT EFFECTS ON A REACTIVE FLOW WITH LOW RESIDENCE TIME AND HIGHLY VARIABLE TEMPERETURE AND PRESSURE

Q: How can I download an article?

To download an article from SID, first log in to the site, search for the article title, and click on the 'Download Article' option.

Q: How can I download an ISI article?

To download an ISI article on SID, enter the keyword or article title in the search bar, view the relevant results, click on the desired article, and select the 'Download Article' option.

Q: How can I access the SID database?

To access the SID database, visit SID.ir, create an account, and log in to access scientific resources.

Q: Is downloading articles from SID free?

Some articles on SID are available for free, while others require payment. Details are specified on the article's page.

ABDOLLAHPOUR MOHAMMAD SALEH; MARDANI AMIR; REZAEI VAHID

مرکز اطلاعات علمی Scientific Information Database (SID) - Trusted Source for Research and Academic Resources

Journal Paper

Paper Information

Journal: FUEL AND COMBUSTION Year:2014 | Volume:7 | Issue:2 Page(s): 77-95

Download Full-Text

Persian Verion

View:

1,321

Download:

Cites:

Information Journal Paper

Title

STUDY OF EQUIVALENCE RATIO AND PROPELLANT EFFECTS ON A REACTIVE FLOW WITH LOW RESIDENCE TIME AND HIGHLY VARIABLE TEMPERETURE AND PRESSURE

Author(s)

ABDOLLAHPOUR MOHAMMAD SALEH | MARDANI AMIR | REZAEI VAHID | Issue Writer Certificate

Keywords

COMBUSTIONQ2

EQUIVALENCE RATIOQ2

COMPUTATIONAL FLUID DYNAMICSQ1

KEROSENEQ2

HYDROGENQ2

Abstract

Gas aerothermodynamics is the thermodynamics of a gas in high velocity associated with heat transfer. One of the devices which takes advantage of this field is a rocket system. High velocity flow filed with intensely varying pressure and temperature along the nozzle axis leads to reduction of residence time. This means the balance between chemical and flow time scales is changing in the flow stream. In this study, reacting flow composition variations in COMBUSTION chamber and nozzle of a liquid rocket engine is numerically investigated for HYDROGEN and KEROSENE fuels regarding COMBUSTION efficiency and performance of the engine. Numerical modeling has been conducted with the aid of commercial code FLUENT. K- e turbulence and EDC COMBUSTION models have been used to consider turbulence effects on the flow field. 9-step and 14-step skeletal mechanisms have been utilized to represent chemical oxidation of KEROSENE and HYDROGEN, respectively. Results show a reasonable accuracy in comparison with experimental measurements. As a result of this study, it can be concluded that in COMBUSTION chamber and convergent nozzle, the frozen and finite rate modeling have almost same results in all EQUIVALENCE RATIOs. However, in divergent section of the nozzle some reactions proceed in finite rate regarding to fuel type. Finally, it can be noted that maximum Damkohler number occurs in the same axial position for both KEROSENE and HYDROGEN fuels.

Cites

No record.

References

No record.

Cite

APA: Copy

ABDOLLAHPOUR, MOHAMMAD SALEH, MARDANI, AMIR, & REZAEI, VAHID. (1393). مطالعه اثرات نسبت هم ارزی و نوع سوخت بر روی یک جریان واکنشی با فشار و دمای متغیر و زمان اقامت کوتاه. سوخت و احتراق, 7(2), 77-95. SID. https://sid.ir/paper/138619/en

Vancouver: Copy

ABDOLLAHPOUR MOHAMMAD SALEH, MARDANI AMIR, REZAEI VAHID. مطالعه اثرات نسبت هم ارزی و نوع سوخت بر روی یک جریان واکنشی با فشار و دمای متغیر و زمان اقامت کوتاه. سوخت و احتراق[Internet]. 1393;7(2):77-95. Available from: https://sid.ir/paper/138619/en

IEEE: Copy

MOHAMMAD SALEH ABDOLLAHPOUR, AMIR MARDANI, and VAHID REZAEI, “مطالعه اثرات نسبت هم ارزی و نوع سوخت بر روی یک جریان واکنشی با فشار و دمای متغیر و زمان اقامت کوتاه,” سوخت و احتراق, vol. 7, no. 2, pp. 77–95, 1393, [Online]. Available: https://sid.ir/paper/138619/en

Related Journal Papers