Effective Boundary Conditions and Numerical Method for Flow Characteristics of Aeroengine Compressor at High Mach Flight

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.

Lin a.q.; ZHOU J.; Tian x.j.; ZHENG Q.; ZHANG H.

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

Journal Paper

Paper Information

Journal: JOURNAL OF APPLIED FLUID MECHANICS (JAFM) Year:2019 | Volume:12 | Issue:3 Page(s): 845-855

Download Full-Text

View:

180

Download:

183

Cites:

Information Journal Paper

Title

Effective Boundary Conditions and Numerical Method for Flow Characteristics of Aeroengine Compressor at High Mach Flight

Author(s)

Keywords

Aeroengine compressor

High Mach

Similarity criterion

Parametric definition

Abstract

Flow characteristics inside the compressor are of great importance for aeroengine performance under the high adverse pressure gradient. To meet the need for quick performance estimation, the numerical simulation is a meaningful investigation method to predict the similarity flow characteristics of Aeroengine compressor at High Mach flight. Thus, this paper aims to satisfy the accuracy of compressor flow field at high altitude based on the Similarity criterion. The accuracy for solution results by the application of the Similarity criterion and the derivation of compressor boundary conditions is verified with the experimental data. Then, the Parametric definitions of air intake are put forward to get the inlet boundary conditions of compressor. The comparative simulation results are conducted between similarity and prototype flow fields at design boundary conditions. The results show that among the most important dimensionless criterion is Mach number at high-speed flow, so the same equivalent mass flow and equivalent speed are recommended. In addition, the flow characteristics of the compressor at high altitude and High Mach number have a good similarity. Consequently, it can extend to further study compressor performance of aeroengine at different flight altitudes and Mach numbers.

Cites

No record.

References

No record.

Cite

APA: Copy

Lin, a.q., ZHOU, J., Tian, x.j., ZHENG, Q., & ZHANG, H.. (2019). Effective Boundary Conditions and Numerical Method for Flow Characteristics of Aeroengine Compressor at High Mach Flight. JOURNAL OF APPLIED FLUID MECHANICS (JAFM), 12(3), 845-855. SID. https://sid.ir/paper/307938/en

Vancouver: Copy

Lin a.q., ZHOU J., Tian x.j., ZHENG Q., ZHANG H.. Effective Boundary Conditions and Numerical Method for Flow Characteristics of Aeroengine Compressor at High Mach Flight. JOURNAL OF APPLIED FLUID MECHANICS (JAFM)[Internet]. 2019;12(3):845-855. Available from: https://sid.ir/paper/307938/en

IEEE: Copy

a.q. Lin, J. ZHOU, x.j. Tian, Q. ZHENG, and H. ZHANG, “Effective Boundary Conditions and Numerical Method for Flow Characteristics of Aeroengine Compressor at High Mach Flight,” JOURNAL OF APPLIED FLUID MECHANICS (JAFM), vol. 12, no. 3, pp. 845–855, 2019, [Online]. Available: https://sid.ir/paper/307938/en

Related Journal Papers

No record.

Related Seminar Papers

No record.

Related Plans

No record.

Recommended Workshops