The Use of an Ultra-Compact Combustor as an Inter-Turbine Burner for Improved Engine Performance
Author:
Affiliation:
1. Air Force Institute of Technology
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2014-0458
Reference9 articles.
1. A critical analysis of the thermodynamic advantages of reheat in gas turbines
2. Performance Cycle Analysis of Turbofan Engine with Interstage Turbine Burner
3. Turbojet and Turbofan Engine Performance Increases Through Turbine Burners
4. Ultra-Compact Combustion Technology Using High Swirl for Enhanced Burning Rate
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1. Effect on Fuel Supply Angle on Outlet Temperature Distribution and NOx Emission in a Micro Trapped Vortex Combustor;Environmental Science and Engineering;2024
2. Optimal Architectures for Dry and Wet Gas-Turbine Engines;Journal of Engineering for Gas Turbines and Power;2018-06-15
3. Measurements of Temperature, Pressure, Velocity, and Frequency in an Ultra Compact Combustor;2018 AIAA Aerospace Sciences Meeting;2018-01-07
4. Development and Testing of a Variable Geometry Diffuser in an Ultra-Compact Combustor;55th AIAA Aerospace Sciences Meeting;2017-01-05
5. Parametric Cycle Analysis of a Turbofan with Core Engine Replaced by Revolutionary Innovative Turbine Engine;52nd AIAA/SAE/ASEE Joint Propulsion Conference;2016-07-22
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