Zobrazeno 1 - 10
of 13
pro vyhledávání: '"Miklos Gerendas"'
Autor:
Scott Yandt, Mahtab Salehii, Miklos Gerendas, Donna Riedel, Lucas Delaby, Ali Shanian, Mitch Kibsey, Matthew Christopher Innes, Megan Schaenzer, Minh Quan Pham, Benoit Villien, David Backman
Publikováno v:
Journal of Engineering Materials and Technology. 144
A novel patterned-void structure is developed to improve the fatigue life compared with conventional circular cooling holes typically used in gas turbine components exposed to high temperatures. The distinctive S-shape of the voids and their specific
Autor:
Minh Quan Pham, Thomas Scarinci, Scott Yandt, Christopher Booth-Morrison, Katia Bertoldi, Matthew Christopher Innes, Ahmad Rafsanjani, Farhad Javid, Megan Schaenzer, Ali Shanian, Jia Liu, Miklos Gerendas, David Backman
Publikováno v:
Extreme Mechanics Letters. 16:13-17
Many components of gas turbines, including the combustion liners, ducts, casings and sealing structures, comprise metallic sheets perforated with arrays of circular cooling holes. These parts are highly prone to fatigue failure due to the stresses in
Autor:
Farhad Javid, Ali Shanian, Mahtab Salehii, Tobias Meis, Dieter Peitsch, Scott Yandt, Friedrich Bake, François-Xavier Jette, Miklos Gerendas, David Backman, Andrew J. Gross, Karsten Knobloch, Katia Bertoldi, Minh Quan Pham, Megan Schaenzer, Genevieve Bourgeois
Publikováno v:
Advanced Engineering Materials. 21:1900084
Mechanical metamaterials have attracted great interest due their ability to attain material properties outside the bounds of those found in natural materials. Many promising mechanical metamaterials have been designed, fabricated, and tested, however
Effusion Cooled Combustor Liner Tiles with Modern Cooling Concepts: A Comparative Experimental Study
Advanced combustion techniques in aero engines require highly effective cooling schemes of combustor liners. One parameter affecting the cooling performance is the geometry of the cooling holes themselves. So far, the freedom in the design of cooling
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::f1f0d136741d9b50bda8fe53a4f6a0dc
https://elib.dlr.de/104947/
https://elib.dlr.de/104947/
Publikováno v:
Volume 5C: Heat Transfer.
An experimental and numerical study is presented that deals with the impact of the swirled hot gas main flow on the penetration behaviour and cooling performance of a starter cooling film.Within modern combustion chambers designed for lean combustion
Autor:
Miklos Gerendas, Sigmar Wittig
Publikováno v:
Journal of Engineering for Gas Turbines and Power. 123:580-588
The presented work is concerned with two-phase flows similar to those in prefilming airblast atomizers and combustors employing film vaporization. Correlations for the multicomponent mixture properties and models for the calculations of the multicomp
Autor:
Jürgen Göring, Thomas Behrendt, Kamen Tushtev, Dietmar Koch, Erich Werth, Eike Volkmann, Severin Hofmann, Christian Wilhelmi, Miklos Gerendas, Thays Machry, Ralf Knoche
In the framework of the High Performance Oxide Ceramics program (HiPOC), three different oxide/oxide ceramic matrix composite (CMC) materials are studied for a combustion chamber application in continuation of the work reported in Gerendas et al. [1]
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::2121cec9569f78513dcf3d3d8016e840
https://elib.dlr.de/82756/
https://elib.dlr.de/82756/
Publikováno v:
Volume 3B: Heat Transfer.
Based on experimental results on a liner of a modern direct lean injection combustion chamber using coolant ejection from both effusion cooling holes and a starter film, a method is presented that allows the assessment of the cooling performance of t
Publikováno v:
Journal of Applied Mechanics. 79
The design of critical components for aerospace applications involves a number of conflicting functional requirements: reducing fuel consumption, cost, and weight, while enhancing performance, operability and robustness. As several materials systems
Publikováno v:
Volume 4: Heat Transfer, Parts A and B.
The thermal management of aero gas turbine engine combustion systems commonly employs effusion-cooling in combination with various cold-side convective cooling schemes. The combustor liner incorporates many small holes which are usually set in stagge