Results 131 to 140 of about 512 (187)
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Experimental Investigation of Fuel Cooled Combustor
52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016Hydrocarbon propelled scramjet engines are suitable for high-speed hypersonic flight. Yet, when flight velocities increase over Mach 5, vehicle thermal protection becomes very critical, as the incoming air cannot be used to cool down the engine. Consequently, scramjet engines cooling must be obtained by using the fuel as a coolant.
Lucio Taddeo +6 more
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Journal of Turbomachinery, 2021
Abstract One of the most effective ways to cool the combustor liner is through effusion cooling. Effusion cooling (also known as full-coverage effusion cooling) involves uniformly spaced holes distributed throughout the combustor liner wall. Effusion cooling configurations are preferred for their high effectiveness, low-pressure penalty,
Shoaib Ahmed +4 more
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Abstract One of the most effective ways to cool the combustor liner is through effusion cooling. Effusion cooling (also known as full-coverage effusion cooling) involves uniformly spaced holes distributed throughout the combustor liner wall. Effusion cooling configurations are preferred for their high effectiveness, low-pressure penalty,
Shoaib Ahmed +4 more
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Prediction of Combustor Liner Cooling
Volume 3: Heat Transfer, Parts A and B, 2006Effective cooling of combustor liners is an important and integrated part of jet engine combustor design, as the liner temperature directly impacts the durability of the combustor. Cooling air jet, usually around 1000–1200 °F, is inserted into slots at the onset of each liner panel. These slots and feedholes are together called nuggets.
Jiankun Yuan +3 more
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Combustor Cooling Wiggle Strip and Geometrical Simplification
Volume 3: Combustion Science and Engineering, 2008The flow fields of a combustor cooling wiggle strip and its corresponding simplified slot with conjugate heat transfer have been studied numerically. The effects of geometrical simplification on the flow fields have been analysed qualitatively and quantitatively.
Jiang, L. Y., Bird, Jeffrey
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Cooling Efficiency for Assessing the Cooling Performance of an Effusion Cooled Combustor Liner
Volume 3B: Heat Transfer, 2013Based 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 the liner.
Wurm, B. +3 more
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Radiatively cooled scramjet combustor
2009The construction of combustion chambers for scramjets that can survive the heating loads and dissipate the energy of a flight effectively remains a great challenge. In addition to surviving the conditions of supersonic combustion, the structure must be designed to minimise weight to optimise the performance of the engine.
Morgan, R. G., Zander, F.
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Cooling Requirements for an Ultra-Compact Combustor
50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2012Abstract : Over the past several years, AFIT and the Air Force Research Laboratory have collaboratively investigated a novel combustor system that is compact in design and has potential use in an inter-turbine burner system. The ultra-compact combustor (UCC) design wraps the combustion section circumferentially around the axial core flow and exploits ...
Donald Johnson, Marc Polanka
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Manufacturing of Effusion Cooled Combustors
SAE Technical Paper Series, 1991<div class="htmlview paragraph">Effusion cooled combustor designs for gas turbine engines offer improvements over traditional cooling approaches. The effusion technique, also known as transpiration, or multi-hole, employs minute cooling passages through the wall to be cooled.
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Novel Jet Impingement Cooling Geometry for Combustor Liner Backside Cooling
Journal of Thermal Science and Engineering Applications, 2009Impinging jets are commonly used to enhance heat transfer in modern gas turbine engines. Impinging jets used in turbine blade cooling typically operate at lower Reynolds numbers in the range of 10,000–20,000. In combustor liner cooling, the Reynolds numbers of the jets can be as high as 60,000.
E. I. Esposito +3 more
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Impact of Swirl Flow on the Cooling Performance of an Effusion Cooled Combustor Liner
Volume 4: Heat Transfer, Parts A and B, 2012An experimental study on combustor liner cooling of modern direct lean injection (DLI) combustion chambers using coolant ejection from both effusion cooling holes and a starter film has been conducted. The experimental setup consists of a generic scaled three sector planar rig in an open loop hot gas wind tunnel, which has been described earlier in ...
Wurm, B. +3 more
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