Modeling of the break-up of liquid oxygen droplets for application in a cryogenic rocket engine simulation code
38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2002, Indianapolis, IN, Amerika Birleşik Devletleri, 7 - 10 Temmuz 2002, (Tam Metin Bildiri)
- Yayın Türü: Bildiri / Tam Metin Bildiri
- Basıldığı Şehir: Indianapolis, IN
- Basıldığı Ülke: Amerika Birleşik Devletleri
- Orta Doğu Teknik Üniversitesi Adresli: Evet
Özet
From an original experimental study, a secondary atomization model for liquid oxygen droplets has been developed. The first part of this paper is a short review of experimental results and their use for the elaboration of the model. This model has been used, first, in a very simple configuration, which corresponds to the breakup of an initial single spherical droplet in a high speed and high pressure helium jet. In a second step, this model has been used in a more realistic configuration which corresponds to the MASCOTTE test bench operated by ONERA. MASCOTTE is a single co-axial injector combustor burning LOX and GH2. For this simulation, the results concern mainly the spray structure (number and size of droplets, length of the spray), and the compound mass fractions (hydrogen, liquid and gaseous oxygen) in the whole computational domain. These results are obtained for two kinds of simulation, one for which the secondary atomization model is not activated, and one for which the presently developed model is used. The comparison between these computations gives insight on the importance of the secondary atomization process for the mixing properties of a simplified co-axial LOX/GH2 injector. © 2002 by the authors.