NUMERICAL SIMULATION OF INLET VORTEX NEAR THE INLET AIR DUCT OF AN AIRCRAFT ENGINE IN HEADWIND CONDITION

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.

MIHANDOUST ATIYEH; JAHANIAN OMID; HASSANZADEH HAMID

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

Journal Paper

Paper Information

Journal: Modares Mechanical Engineering Year:2017 | Volume:17 | Issue:6 Page(s): 90-100

Download Full-Text

Persian Verion

View:

749

Download:

Cites:

Information Journal Paper

Title

NUMERICAL SIMULATION OF INLET VORTEX NEAR THE INLET AIR DUCT OF AN AIRCRAFT ENGINE IN HEADWIND CONDITION

Author(s)

MIHANDOUST ATIYEH | JAHANIAN OMID | HASSANZADEH HAMID | Issue Writer Certificate

Keywords

COMPUTATIONAL FLUID DYNAMICQ1

GROUND VORTEXQ1

INLET VORTEXQ1

JET ENGINEQ2

FOREIGN OBJECT DAMAGE (FOD)Q1

Abstract

The JET ENGINEs working near the ground, with low speed and high thrust, can experience flow separation between ground and inlet which would lead to vortices called GROUND VORTEX that have harmful effects on engine performance and can disrupt integrity of inlet flow. Deep understanding of the physics of this phenomenon could omit the injuries of foreign objects damages, engine surge, compressor stall, and fan vibration. In this study, the GROUND VORTEX formation near the inlet air duct of an aircraft engine is investigated using COMPUTATIONAL FLUID DYNAMICs. Simulations are performed for a 1: 30 scale. The fluid flow is assumed to be compressible air, three-dimensional and steady. The k-w SST model is employed for incorporating turbulent characteristics. After mesh study, the boundary of Vortex or No-Vortex for results of this study compared with a theoretical and an empirical correlation by Murphy which showed good agreement. Moreover, despite free stream existence, decreasing nondimensional velocity ratio causes the movement of vortex core and by approaching the critical nondimensional velocity ratio the GROUND VORTEX would gradually disappear. For U*=33, 44, 66, 132 GROUND VORTEX is formed, but for U*=26.4 GROUND VORTEX disappears. The computational method has subsequently been applied to configurations that are difficult to test experimentally including headwind flows. According to this study, the formation of the vortical flow field permanently affects the total pressure distortion on the engine fan face. In this paper, DC60 is calculated under headwind condition. These coefficients are 0.39, 0.391, 0.447 and 0.3957 at U*=33, 44, 66, 132 respectively.

Cites

No record.

References

No record.

Cite

APA: Copy

MIHANDOUST, ATIYEH, JAHANIAN, OMID, & HASSANZADEH, HAMID. (2017). NUMERICAL SIMULATION OF INLET VORTEX NEAR THE INLET AIR DUCT OF AN AIRCRAFT ENGINE IN HEADWIND CONDITION. MODARES MECHANICAL ENGINEERING, 17(6 ), 90-100. SID. https://sid.ir/paper/179225/en

Vancouver: Copy

MIHANDOUST ATIYEH, JAHANIAN OMID, HASSANZADEH HAMID. NUMERICAL SIMULATION OF INLET VORTEX NEAR THE INLET AIR DUCT OF AN AIRCRAFT ENGINE IN HEADWIND CONDITION. MODARES MECHANICAL ENGINEERING[Internet]. 2017;17(6 ):90-100. Available from: https://sid.ir/paper/179225/en

IEEE: Copy

ATIYEH MIHANDOUST, OMID JAHANIAN, and HAMID HASSANZADEH, “NUMERICAL SIMULATION OF INLET VORTEX NEAR THE INLET AIR DUCT OF AN AIRCRAFT ENGINE IN HEADWIND CONDITION,” MODARES MECHANICAL ENGINEERING, vol. 17, no. 6 , pp. 90–100, 2017, [Online]. Available: https://sid.ir/paper/179225/en

Related Journal Papers