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Optimization-based transient control of turbofan engines: a sequential quadratic programming approach

  • Jiqiang Wang EMAIL logo , Huan Hu , Weicun Zhang and Zhongzhi Hu
Published/Copyright: December 29, 2021
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International Journal of Turbo & Jet-Engines
From the journal International Journal of Turbo & Jet-Engines Volume 40 Issue s1

Abstract

Engine transient control has been challenging due to its stringent requirements from both performance and safety. Many methodologies have been proposed such as conventional schedule-based methods, linear parameter varying, multiobjective optimization and evolutionary computations etc. These approaches have been well-established and led to a series of significant results. However, they are either not providing limit protection or requiring exhaustive computational resources, particularly when generating results into full flight envelope applications. Consequently a compromise between limit protection and computational complexity is necessitated. This note considers a sequential quadratic programming (SQP)-based method for full flight envelope investigations. The proposed method can provide important design guidance and the corresponding claims are validated through detailed analysis and simulations.

Keywords: engine transient control; limit protection control; optimization-based method; SQP approach
Corresponding author: Jiqiang Wang, Ningbo Institute of Materials Technology & Engineering, Chinese Academy of Sciences, Room 507, Building IAMT (South), 1219 Zhongguan West Road, Zhenhai District, Ningbo, 315201, China, E-mail:

Funding source: Central Military Commission http://dx.doi.org/10.13039/501100001849

Award Identifier / Grant number: 2019-JCJQ-JJ-347, 20-163-00-TS-009-096-01, 80910010102 and 201919052001

  1. Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.

  2. Research funding: This work is supported by the Central Military Commission Foundation to Strengthen Program Technology Fund (No. 2019-JCJQ-JJ-347); Central Military Commission Special Fund for Defense Science, Technology & Innovation (20-163-00-TS-009-096-01); Central Military Commission Advanced Research Funds for Equipment Development (80910010102); Aviation Science Fund of China-Xi’an 631 Research Institute (No. 201919052001).

  3. Conflict of interest statement: The authors declare no conflicts of interest regarding this article.

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Received: 2021-12-07
Accepted: 2021-12-12
Published Online: 2021-12-29

© 2021 Walter de Gruyter GmbH, Berlin/Boston

Articles in the same Issue

  1. Frontmatter
  2. The International Journal of Turbo and Jet Engines
  3. The aerothermodynamic cycle optimal design of a turbofan engine
  4. Multi-condition design optimization of groove flow control technique in an axial-flow pump
  5. Analysis on impulse characteristics of pulse detonation engine with nozzles
  6. Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor
  7. Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine
  8. Applicability of correlational data-mining to small-scale turbojet performance map generation
  9. Effect of multi-zone effusion cooling on an adiabatic flat plate for gas turbine application
  10. Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence
  11. Modeling and analysis of 3D radiative heat transfer in combustor
  12. A creep-fatigue life prediction model considering multi-factor coupling effect
  13. Optimization-based transient control of turbofan engines: a sequential quadratic programming approach
  14. Investigations on the interaction between the front and aft purge flow and the downstream vane of 1.5-stage turbine
  15. A study on design optimization for compressor blisks
  16. Exploration of an unconventional validation tool to investigate aero engine transonic fan flutter signature
  17. Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
  18. Predicting remaining useful life of turbofan engines using degradation signal based echo state network
  19. Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
  20. Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
  21. Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
  22. Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
  23. Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
  24. Performance enhancement and flow separation control in an S-duct by air injection
  25. Gas dynamic analysis of the modern single shaft gas turbine engine flow path
  26. Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
  27. Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils
  28. The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall
  29. Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade
  30. Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor
  31. Research on temperature rise characteristics of end V-groove ring seal
  32. Research on the influence of honeycomb cell blockage on the seal leakage characteristics
  33. Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation
  34. Development and application of a profile loss model considering the low-Re effect in low-pressure turbine
  35. Optimization of ACE mode transition control schedule considering geometric adjustment speed
  36. Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps
  37. The design method of the V-shaped groove piston ring
  38. Control of subsonic jets using vanes as vortex generators
  39. Impact investigation of inlet environmental changes on the rated condition performance of a high-pressure compressor
  40. Research on new integral squeeze film damper vibration control of micro turbojet engine at high speed
  41. Effect of the distribution of the upstream probe support on performance of compressor cascade
  42. Effect of bypass ratio on sonic underexpanded co-flow jets with finite lip thickness
  43. Machine learning augmented multi-sensor data fusion to detect aero engine fan rotor blade flutter
  44. CFD analysis of flow control in compressor cascade using MVGs
  45. Quantitative investigation of the evaporation and resistance characteristics of inlet jet precooling
  46. Study on laser de-weight and dynamic balance technology of rotating machines
  47. Integrated design and analysis of inlet and missile with two side layout
  48. Research on turboprop engine control method based on linear parameter varying model
  49. Modeling and validation of the volume effect on the axial fan transient performance
  50. Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications
  51. Multidisciplinary sensitivity analysis for turbine blade considering thickness uncertainties
  52. Accurate measurement and evaluation method of axial compressor efficiency under the influence of multiple factors
  53. Control mechanism of secondary flow in a turbine cascade with non-axisymmetric endwall profiling under Co-rotating incoming vortex
  54. Infrared simulation of aircraft rear fuselage based on a coupled CFD method
  55. Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application
  56. Numerical study of transition process in different zones of a compressor cascade channel
https://doi.org/10.1515/tjj-2021-0072
Keywords for this article
engine transient control; limit protection control; optimization-based method; SQP approach

Articles in the same Issue

  1. Frontmatter
  2. The International Journal of Turbo and Jet Engines
  3. The aerothermodynamic cycle optimal design of a turbofan engine
  4. Multi-condition design optimization of groove flow control technique in an axial-flow pump
  5. Analysis on impulse characteristics of pulse detonation engine with nozzles
  6. Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor
  7. Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine
  8. Applicability of correlational data-mining to small-scale turbojet performance map generation
  9. Effect of multi-zone effusion cooling on an adiabatic flat plate for gas turbine application
  10. Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence
  11. Modeling and analysis of 3D radiative heat transfer in combustor
  12. A creep-fatigue life prediction model considering multi-factor coupling effect
  13. Optimization-based transient control of turbofan engines: a sequential quadratic programming approach
  14. Investigations on the interaction between the front and aft purge flow and the downstream vane of 1.5-stage turbine
  15. A study on design optimization for compressor blisks
  16. Exploration of an unconventional validation tool to investigate aero engine transonic fan flutter signature
  17. Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
  18. Predicting remaining useful life of turbofan engines using degradation signal based echo state network
  19. Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
  20. Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
  21. Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
  22. Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
  23. Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
  24. Performance enhancement and flow separation control in an S-duct by air injection
  25. Gas dynamic analysis of the modern single shaft gas turbine engine flow path
  26. Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
  27. Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils
  28. The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall
  29. Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade
  30. Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor
  31. Research on temperature rise characteristics of end V-groove ring seal
  32. Research on the influence of honeycomb cell blockage on the seal leakage characteristics
  33. Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation
  34. Development and application of a profile loss model considering the low-Re effect in low-pressure turbine
  35. Optimization of ACE mode transition control schedule considering geometric adjustment speed
  36. Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps
  37. The design method of the V-shaped groove piston ring
  38. Control of subsonic jets using vanes as vortex generators
  39. Impact investigation of inlet environmental changes on the rated condition performance of a high-pressure compressor
  40. Research on new integral squeeze film damper vibration control of micro turbojet engine at high speed
  41. Effect of the distribution of the upstream probe support on performance of compressor cascade
  42. Effect of bypass ratio on sonic underexpanded co-flow jets with finite lip thickness
  43. Machine learning augmented multi-sensor data fusion to detect aero engine fan rotor blade flutter
  44. CFD analysis of flow control in compressor cascade using MVGs
  45. Quantitative investigation of the evaporation and resistance characteristics of inlet jet precooling
  46. Study on laser de-weight and dynamic balance technology of rotating machines
  47. Integrated design and analysis of inlet and missile with two side layout
  48. Research on turboprop engine control method based on linear parameter varying model
  49. Modeling and validation of the volume effect on the axial fan transient performance
  50. Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications
  51. Multidisciplinary sensitivity analysis for turbine blade considering thickness uncertainties
  52. Accurate measurement and evaluation method of axial compressor efficiency under the influence of multiple factors
  53. Control mechanism of secondary flow in a turbine cascade with non-axisymmetric endwall profiling under Co-rotating incoming vortex
  54. Infrared simulation of aircraft rear fuselage based on a coupled CFD method
  55. Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application
  56. Numerical study of transition process in different zones of a compressor cascade channel
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