Zobrazeno 1 - 10
of 17
pro vyhledávání: '"Won-Kook Cho"'
Publikováno v:
Journal of the Korean Society for Aeronautical & Space Sciences. 47:517-524
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::78996aea3ddd2477e769324b0efe342e
https://doi.org/10.5139/jksas.2019.47.7.517
https://doi.org/10.5139/jksas.2019.47.7.517
Publikováno v:
Journal of the Korean Society for Aeronautical & Space Sciences. 44:675-685
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0a940acb171e67cd90408fd799ee75ee
https://doi.org/10.5139/jksas.2016.44.8.675
https://doi.org/10.5139/jksas.2016.44.8.675
Publikováno v:
Journal of Thermal Science. 21:428-434
A design method for a kerosene fuel-rich gas-generator of a liquid rocket engine using turbopumps to supply propellant was performed at a conceptual level. The gas-generator creates hot gases, enabling the turbine to operate the turbopumps. A chemica
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d4166ff6a3d08ed9b031cefd4c71e776
https://doi.org/10.1007/s11630-012-0564-z
https://doi.org/10.1007/s11630-012-0564-z
Publikováno v:
Transactions of the Korean Society of Mechanical Engineers B. 36:563-569
An energy balance analysis is conducted for a 30 t thrust level liquid rocket engine. The relations between thrust and combustion pressure, between thrust and propellant flow rate, and between combustion pressure and fuel pump pressure rise are compa
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::91b68bc4ddbdf1c8fe744cde26f8994e
https://doi.org/10.3795/ksme-b.2012.36.5.563
https://doi.org/10.3795/ksme-b.2012.36.5.563
Publikováno v:
Journal of Thermal Science. 20:467-473
An integrated program was established to design a combustor for a liquid rocket engine and to analyze regenerative cooling results on a preliminary design level. Properties of burnt gas from a kerosene-LOx mixture in the combustor and rocket performa
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::f2550595805aafbf4c860b8ea5db07ef
https://doi.org/10.1007/s11630-011-0497-y
https://doi.org/10.1007/s11630-011-0497-y
Publikováno v:
Transactions of the Korean Society of Mechanical Engineers B. 34:443-448
In this paper, the changes in performance parameters, e.g., the combustor pressure, turbine power, engine mixture ratio, temperature of gas generator, and product gas, of a liquid rocket engine employing gas generator cycle with the variations in pro
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::c45fd72bed7772b385f0f676a012a30e
https://doi.org/10.3795/ksme-b.2010.34.4.443
https://doi.org/10.3795/ksme-b.2010.34.4.443
Publikováno v:
Journal of the Korean Society for Aeronautical & Space Sciences. 33:107-113
A calorimeter of 2-ton thrust level rocket engine chamber has been developed to measure the wall heat flux. The liner of the chamber is made of copper-chromium alloy to maximize the heat transfer performance and structural strength. 1-D design code b
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::3b6b5dbeca9f10d546fe9b15ff9c4a38
https://doi.org/10.5139/jksas.2005.33.3.107
https://doi.org/10.5139/jksas.2005.33.3.107
Autor:
Won Kook Cho, Chul-Sung Ryu
Publikováno v:
International Journal of Aeronautical and Space Sciences. 5:1-5
The discharge performance of an impinging-type injector for cavitating flow has been evaluated. The predicted discharge coefficient for cavitating flow agrees well with the measured data showing less than 2% discrepancy. For the case of non-cavitatin
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::09e506f89f9d68149b17f8c72dc550f2
https://doi.org/10.5139/ijass.2004.5.1.001
https://doi.org/10.5139/ijass.2004.5.1.001
Publikováno v:
Journal of the Korean Society for Aeronautical & Space Sciences. 32:67-72
A regenerative cooling system has been designed through empirical 1-D analysis for a liquid rocket engine of 30-ton-level thrust. The hot-gas-side wall temperature from 1-D analysis shows 100K difference compared to 3D CFD analysis. Two variations of
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8f816fd7e78c3580e4c5503211886836
https://doi.org/10.5139/jksas.2004.32.4.067
https://doi.org/10.5139/jksas.2004.32.4.067
Publikováno v:
Journal of the Korean Society for Aeronautical & Space Sciences. 32:111-117
An analytical study was carried out to evaluate the regenerative cooling characteristics in the liquid rocket engine of a 10tf-thrust level using kerosene as a fuel. As a supplementary cooling method, a radiative cooling was applied to the nozzle ext
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::3a4dfe11d5af46b93a9b52e590e22cea
https://doi.org/10.5139/jksas.2004.32.4.111
https://doi.org/10.5139/jksas.2004.32.4.111