Effect of bypass ratio on sonic underexpanded co-flow jets with finite lip thickness
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Naren Shankar Radha Krishnan
,
Sathish Kumar Kumar
,
Vijayaraja Kengaiah
Abstract
The characteristics of a sonic under-expanded coaxial jet with lip thickness 1.5D p (where D p is the exit diameter of primary jet equals 10 mm) with the primary jet operating at nozzle pressure ratio (NPR) of 3, 4 and 5. For NPR 3 operating primary jet, the secondary jet operates at NPR 2.5, 1.4 and 1.27. For primary jet NPR 4, the secondary jet operating NPR is 3.2, 1.6 and 1.4. For NPR 5 primary jet, the secondary jet NPR is 3.8, 1.89 and 1.52. The study is performed using a co-flow nozzle of bypass ratio (BR) 6.4, 1.4 and 0.7. The core length of the primary jet is used as a measure to quantify the mixing of the primary jet in the presence of coaxial jet. The shock structure present in the near field was viewed using shadowgraph technique. Centreline pitot pressure distribution, radial spread and waves present in the jet core were analyzed. The results show that the mixing associated with the high bypass coaxial jet is superior to the low bypass coaxial jet. This mixing superiority associated with high bypass coaxial jet prevails all levels of expansion.
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Research funding: This research received no specific grant from any funding agency.
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© 2022 Walter de Gruyter GmbH, Berlin/Boston
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Articles in the same Issue
- Frontmatter
- The International Journal of Turbo and Jet Engines
- The aerothermodynamic cycle optimal design of a turbofan engine
- Multi-condition design optimization of groove flow control technique in an axial-flow pump
- Analysis on impulse characteristics of pulse detonation engine with nozzles
- Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor
- Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine
- Applicability of correlational data-mining to small-scale turbojet performance map generation
- Effect of multi-zone effusion cooling on an adiabatic flat plate for gas turbine application
- Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence
- Modeling and analysis of 3D radiative heat transfer in combustor
- A creep-fatigue life prediction model considering multi-factor coupling effect
- Optimization-based transient control of turbofan engines: a sequential quadratic programming approach
- Investigations on the interaction between the front and aft purge flow and the downstream vane of 1.5-stage turbine
- A study on design optimization for compressor blisks
- Exploration of an unconventional validation tool to investigate aero engine transonic fan flutter signature
- Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
- Predicting remaining useful life of turbofan engines using degradation signal based echo state network
- Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
- Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
- Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
- Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
- Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
- Performance enhancement and flow separation control in an S-duct by air injection
- Gas dynamic analysis of the modern single shaft gas turbine engine flow path
- Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
- Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils
- The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall
- Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade
- Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor
- Research on temperature rise characteristics of end V-groove ring seal
- Research on the influence of honeycomb cell blockage on the seal leakage characteristics
- Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation
- Development and application of a profile loss model considering the low-Re effect in low-pressure turbine
- Optimization of ACE mode transition control schedule considering geometric adjustment speed
- Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps
- The design method of the V-shaped groove piston ring
- Control of subsonic jets using vanes as vortex generators
- Impact investigation of inlet environmental changes on the rated condition performance of a high-pressure compressor
- Research on new integral squeeze film damper vibration control of micro turbojet engine at high speed
- Effect of the distribution of the upstream probe support on performance of compressor cascade
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- Machine learning augmented multi-sensor data fusion to detect aero engine fan rotor blade flutter
- CFD analysis of flow control in compressor cascade using MVGs
- Quantitative investigation of the evaporation and resistance characteristics of inlet jet precooling
- Study on laser de-weight and dynamic balance technology of rotating machines
- Integrated design and analysis of inlet and missile with two side layout
- Research on turboprop engine control method based on linear parameter varying model
- Modeling and validation of the volume effect on the axial fan transient performance
- Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications
- Multidisciplinary sensitivity analysis for turbine blade considering thickness uncertainties
- Accurate measurement and evaluation method of axial compressor efficiency under the influence of multiple factors
- Control mechanism of secondary flow in a turbine cascade with non-axisymmetric endwall profiling under Co-rotating incoming vortex
- Infrared simulation of aircraft rear fuselage based on a coupled CFD method
- Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application
- Numerical study of transition process in different zones of a compressor cascade channel
