Hybrid thermal analysis on film cooled ramjet combustor

J. Song; M. G. Oh; M. S. Yu; H. H. Cho; K. Y. Hwang

Hybrid thermal analysis on film cooled ramjet combustor

J. Song, M. G. Oh, M. S. Yu, H. H. Cho, K. Y. Hwang

Department of Mechanical Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Abstract

Thermal analysis has been conducted numerically on a film cooled ramjet combustor with combining experimental data. The film cooling effectiveness and heat transfer coefficient on the exposed combustor wall were taken experimentally in a cold flow test to obtain the thermal boundary conditions. Distributions of temperature and thermal stresses on the combustor liner were calculated by using the boundary conditions from experimental data and a commercial code, ANSYS. The high thermal stress appears after the stabilizer wall. That is also the region attached by combustion flame. Thermal fracture will occur on the region of high thermal stress due to high temperature difference. The present results of temperature and stress distributions provide a guide line for thermal design in a film cooled ramjet combustor.

Original language	English
Title of host publication	44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Publication status	Published - 2008
Event	44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Hartford, CT, United States Duration: 2008 Jul 21 → 2008 Jul 23

Publication series

Name	44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Other

Other	44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Country	United States
City	Hartford, CT
Period	08/7/21 → 08/7/23

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Control and Systems Engineering
Space and Planetary Science
Energy(all)
Electrical and Electronic Engineering
Mechanical Engineering

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@inproceedings{ef9840e235c24898ae132cde7ff7244e,

title = "Hybrid thermal analysis on film cooled ramjet combustor",

abstract = "Thermal analysis has been conducted numerically on a film cooled ramjet combustor with combining experimental data. The film cooling effectiveness and heat transfer coefficient on the exposed combustor wall were taken experimentally in a cold flow test to obtain the thermal boundary conditions. Distributions of temperature and thermal stresses on the combustor liner were calculated by using the boundary conditions from experimental data and a commercial code, ANSYS. The high thermal stress appears after the stabilizer wall. That is also the region attached by combustion flame. Thermal fracture will occur on the region of high thermal stress due to high temperature difference. The present results of temperature and stress distributions provide a guide line for thermal design in a film cooled ramjet combustor.",

author = "J. Song and Oh, {M. G.} and Yu, {M. S.} and Cho, {H. H.} and Hwang, {K. Y.}",

year = "2008",

language = "English",

isbn = "9781563479434",

series = "44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit",

booktitle = "44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit",

}

TY - GEN

T1 - Hybrid thermal analysis on film cooled ramjet combustor

AU - Song, J.

AU - Oh, M. G.

AU - Yu, M. S.

AU - Cho, H. H.

AU - Hwang, K. Y.

PY - 2008

Y1 - 2008

N2 - Thermal analysis has been conducted numerically on a film cooled ramjet combustor with combining experimental data. The film cooling effectiveness and heat transfer coefficient on the exposed combustor wall were taken experimentally in a cold flow test to obtain the thermal boundary conditions. Distributions of temperature and thermal stresses on the combustor liner were calculated by using the boundary conditions from experimental data and a commercial code, ANSYS. The high thermal stress appears after the stabilizer wall. That is also the region attached by combustion flame. Thermal fracture will occur on the region of high thermal stress due to high temperature difference. The present results of temperature and stress distributions provide a guide line for thermal design in a film cooled ramjet combustor.

AB - Thermal analysis has been conducted numerically on a film cooled ramjet combustor with combining experimental data. The film cooling effectiveness and heat transfer coefficient on the exposed combustor wall were taken experimentally in a cold flow test to obtain the thermal boundary conditions. Distributions of temperature and thermal stresses on the combustor liner were calculated by using the boundary conditions from experimental data and a commercial code, ANSYS. The high thermal stress appears after the stabilizer wall. That is also the region attached by combustion flame. Thermal fracture will occur on the region of high thermal stress due to high temperature difference. The present results of temperature and stress distributions provide a guide line for thermal design in a film cooled ramjet combustor.

UR - http://www.scopus.com/inward/record.url?scp=77957839130&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=77957839130&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:77957839130

SN - 9781563479434

T3 - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

BT - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

T2 - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Y2 - 21 July 2008 through 23 July 2008

ER -