- Tytuł:
- Combustor liner cooling methods - numerical simulation
- Autorzy:
-
Lazarczyk, M.
Domański, R. - Powiązania:
- https://bibliotekanauki.pl/articles/247755.pdf
- Data publikacji:
- 2010
- Wydawca:
- Instytut Techniczny Wojsk Lotniczych
- Tematy:
-
aircraft engines
engine combustion chamber
combustor cooling
CFD - Opis:
- The objective of this thesis is to compare various methods of combustor wall cooling and to evaluate advantages and disadvantages of each applied cooling methods. It was determined that the flrst task was to verify how much air is coming through singe radial hole with 2.5% pressure drop between hot and cold part ofcombustion chamber. Flowcheck was calculated also to see how geometry of cooling hole affects hole effective area. Second task was to generale 3d model and mesh of both calculated types of cooling. Each model mesh was covered with boundary layer in order to better simulate conditions near the combustion chamber walls and obtain accurate results. In order to run back-to-back analysis, all created models have the same number of mesh elements, same materials used, samefluent settings, same operating and boundary conditions. Geometry of all models described above was created using Unigraphics NX4 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization was done in commercial pre-processor GAMBITŽ. The airflow and conjugated heat transfer analysis was calculated in program FLUENTŽ. The goal of this thesis was to obtain temperature fields and distribution in the combustion chamber domain (lip and panel wall) and to evaluate if applied cooling is sufficient to cool down heat loaded part of the combustor chamber.
- Źródło:
-
Journal of KONES; 2010, 17, 4; 277-286
1231-4005
2354-0133 - Pojawia się w:
- Journal of KONES
- Dostawca treści:
- Biblioteka Nauki
Artykuł