Influence of geometry and type of cooling holes on thermal load of combustion chamber

• Autorzy: Swiatek M. , Domański R.
• Języki publikacji: EN

Abstrakty

EN

The objective of this thesis is to compare various methods of combustor wall cooling and their effectiveness by numerical simulations. It was determined that the first task was to verify how much air is coming through single axial hole with 3.5% pressure drop between hot and cold part of combustion chamber. The results from this flow check serve as a base template for generating more accurate and precise models of single axial hole cooling as well as calculation of hole diameter for multihole cooling. Second task was to generate more sophisticated single hole model with boundary layer in order to better simulate the conditions in areas near the combustion chamber walls and get more accurate results. The same method was used to create multihole model. In order to compare efficiency, all created domains in every model have the same volume, model settings, operating and boundary conditions. Geometry of all models described above is created using SIMENS NX4 and SIMENS NX5 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization into a structural finite volume grid took place in commercial pre-processor GAMBITŽ (GAMBIT and FLUENT - commercial CFD codes from Ansy s Inc). The airflow andheat exchange will be calculated using program FLUENTŽ. The results were shown in the thesis in terms of several comparative pictures of the temperature fields in the combustion chamber domain, and graphs representing difference in temperature fields on cooling wall of the combustion chamber.

Słowa kluczowe

EN

aircraft engines; engine combustion chamber; combustor cooling; CFD

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2010
• Tom: Vol. 17, No. 4
• Strony: 485--494
• Opis fizyczny: Bibliogr. 3 poz., rys.

Twórcy

autor

Swiatek M.

autor

Domański R.

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.:[phone],fax: [phone],

Bibliografia

• [1] Łazarczyk, M., Influence of geometry and type of cooling holes on thermal load of combustion chamber, Proceedings of the Warsaw University of Technology, Faculty of Power and Aeronautical Engineering, Warsaw 2009.
• [2] Łapucha, R., Komory spalania silników turbinowo-odrzutowych, Proceedings of Institute of Aviation, Warsaw 2005
• [3] Lefebvre, A., Gas turbine combustion, Proceedings of Taylor & Francis, Philadelphia, PA 19106, 1988.