Experimental Investigation of Shape Transition Effects on Isolator Performance
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G. Chandra Bose
Abstract
Isolator is a critical component in supersonic air breathing engine and it is usually situated between the inlet and the combustor of a dual-mode ramjet/scramjet engine. In the present study, shape transition effects on isolator performance have been studied by carrying out experimental investigations on square, square to circular and square to elliptical transition ducts. The length of the isolator chosen in this study is 180 mm and the cross-sectional area of 900 mm2 is maintained constant along the length for all the ducts. Experiments were carried out for isolator inlet Mach 2, using a contoured nozzle. Varying the pressure of the settling chamber varied the expansion level at the nozzle exit, which run the nozzle. The wall static pressure along the length of the isolator and the Pitot pressure at the exit plane of the isolator were measured for all the configurations. Shadowgraph technique was employed for visualizing the shock-train in the isolator. The square to circular transition isolator is found to be more efficient in achieving the static pressure rise across the isolator than the square and square to elliptical transition ducts.
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© 2018 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Editorials
- Reasons for Triple-Funding of the Jet-Engine-Industry to Meet 2020–2040 6th-Gen-Challenge: Counter-Air Penetration, CAP
- Reasons for triple-funding of the jet-engine-industry to meet 2020-2040 6TH-Gen-Challenge: Counter-Air Penetration, CAP
- Original Research Articles
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Experimental Investigation of Shape Transition Effects on Isolator Performance
- Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor
- Gas Turbine Engine Gas-path Fault Diagnosis Based on Improved SBELM Architecture
- The Effects of Turbulent Burning Velocity Models in a Swirl-Stabilized Lean Premixed Combustor
- Inverse Simulation for Gas Turbine Engine Control through Differential Algebraic Inequality Formulation
- Aerodynamic Optimization of Turbine Based Combined Cycle Nozzle
- Nonlinear System Modeling based on System Equilibrium Manifold
- Numerical Study on Heat Transfer Enhancement of Swirl Chamber on Gas Turbine Blade
Articles in the same Issue
- Frontmatter
- Editorials
- Reasons for Triple-Funding of the Jet-Engine-Industry to Meet 2020–2040 6th-Gen-Challenge: Counter-Air Penetration, CAP
- Reasons for triple-funding of the jet-engine-industry to meet 2020-2040 6TH-Gen-Challenge: Counter-Air Penetration, CAP
- Original Research Articles
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Experimental Investigation of Shape Transition Effects on Isolator Performance
- Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor
- Gas Turbine Engine Gas-path Fault Diagnosis Based on Improved SBELM Architecture
- The Effects of Turbulent Burning Velocity Models in a Swirl-Stabilized Lean Premixed Combustor
- Inverse Simulation for Gas Turbine Engine Control through Differential Algebraic Inequality Formulation
- Aerodynamic Optimization of Turbine Based Combined Cycle Nozzle
- Nonlinear System Modeling based on System Equilibrium Manifold
- Numerical Study on Heat Transfer Enhancement of Swirl Chamber on Gas Turbine Blade
