Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser
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Stanisław Antas
Abstract
The application of radial and axial-centrifugal compressors in turboprop, turboshaft and turbofan engines may require the construction of small diameters diffuser in order to obtain lower weight and smaller frontal area. Conventional exhaust diffusers typically have large outlet diameters for exit Mach numbers lower than 0,2 and low swirl flow to the combustor, hence the design of channel of the low-diameter diffusers called controlled-contour, fishtail-shaped diffuser or diffusing trumpet is complex. The cross-sectional shape of these channels is varied from circular to oval to elliptic and to rectangular. The paper presents an original method for determining the flow parameters in the channel and at the outlet section of the downstream diffusing trumpet for a pipe diffuser, which constitutes the downstream duct of the radial or axial-centrifugal compressor with the pipe diffuser. It also illustrates a new method for determining the geometrical parameters of the diffuser. Mentioned methods (for conceptual design of a compressor with pipe diffuser) are based on Pythagorean theorem, properties of ellipse, equation of continuity, energy equation, first law of thermodynamics, Euler’s moment of momentum equation, gasdynamics functions and definitions used in theory of turbo-machines.
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Articles in the same Issue
- Frontmatter
- Original Research Articles
- Numerical Study of Combinations of Strut and Cavity in a Round Supersonic Combustor
- Design and Numerical Analysis of a Forepart Rotation Vane for a Variable Nozzle Turbine
- Aerodynamic Efficiency Optimization of the 1st Stage of Transonic High Pressure Turbine through Lean and Sweep Angles
- The Effect of Dilution Air Jets on Aero-Engine Combustor Performance
- Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications
- Effects of Non-axisymmetric Casing Grooves Combined with Airflow Injection on Stability Enhancement of an Axial Compressor
- Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser
- Advanced Exergy Analysis of a Turbofan Engine (TFE): Splitting Exergy Destruction into Unavoidable/Avoidable and Endogenous/Exogenous
- A Preliminary Design System for Turbine Discs
- Tensile Behavior and Microstructural Evolution of the Polycrystalline Nickel-Based Superalloy Applied in Turbine Disk
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Numerical Study of Combinations of Strut and Cavity in a Round Supersonic Combustor
- Design and Numerical Analysis of a Forepart Rotation Vane for a Variable Nozzle Turbine
- Aerodynamic Efficiency Optimization of the 1st Stage of Transonic High Pressure Turbine through Lean and Sweep Angles
- The Effect of Dilution Air Jets on Aero-Engine Combustor Performance
- Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications
- Effects of Non-axisymmetric Casing Grooves Combined with Airflow Injection on Stability Enhancement of an Axial Compressor
- Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser
- Advanced Exergy Analysis of a Turbofan Engine (TFE): Splitting Exergy Destruction into Unavoidable/Avoidable and Endogenous/Exogenous
- A Preliminary Design System for Turbine Discs
- Tensile Behavior and Microstructural Evolution of the Polycrystalline Nickel-Based Superalloy Applied in Turbine Disk
