Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
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Hano van Eck
and
Theodor W. von Backström
Abstract
The use of micro gas turbines (MGTs) for once-off and unique applications means that a rapid turnaround design process is required. The development of a MATLAB® application-based program for the initial design and performance analysis of radial and mixed flow compressors is discussed. The program code is based on one dimensional (1D) mean line flow and loss model theory. For verification, 18 test compressors were developed, covering a wide range of design velocities, mass flow rates and meridional exit angles. Predicted performance results were verified using Numeca/FINE™ Turbo software. Initial comparisons between 1D and Computational Fluid Dynamics (CFD) results did not match well. The 1D software over-predicted compressor performance and provided poor choke prediction. Consequently, empirical models to correct these deviations were derived and implemented into the 1D Application code. The updated 1D code provided a mean choke prediction difference of 1.59% compared to an initial 14.98% difference at the design point. Mean total-to-total isentropic efficiency and pressure ratio reduced to differences of 0.74 and 1.24% from values of 11.23 and 9.31% respectively.
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: None declared.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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- 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
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- 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
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