Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
-
S. Gopinath
,
M. Sundararaj
Abstract
Effects of swirling secondary flow on the decay characteristics of non-circular under-expanded supersonic primary jets were experimentally studied. Primary jet is issuing from a convergent-divergent nozzle with different exit geometry such as circle, cruciform, triangle and rectangle. In this study, two different methods were used to impart swirl on the secondary flow as follows, (i) introduction of- angular vanes inside the secondary flow duct and (ii) using tangential inlets at the secondary flow duct. This swirling secondary flow influences the boundary condition of the primary jet and results in reduction of jet core length and shock train length, it also enhances the jet decay rate. Maximum shock train length reduction of 70 % is achieved when swirling secondary flow (tangential injection method) is introduced over the circular primary jet.
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Articles in the same Issue
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
Articles in the same Issue
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
