Deep residual ensemble model for predicting remaining useful life of turbo fan engines
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Sharanya Selvaraj
Abstract
Capturing degradation trends from the Condition monitored signals is a proven technique for predicting the Remining Useful Life (RUL) of the equipment, which has gained more prominence in Prognostics and Health Management (PHM) in Industry 4.0. However, this process is tiresome and comprehending all the physical parameters of the system to construct a Health Index that characterize the health state is a complex process, especially if multiple sensors are involved. This work proposes a Deep residual ensemble model which constructs Fused Health Index (FHI) by harnessing temporal property of signals. The proposed Residual network integrates Bi-directional Long Short Term Memory (Bi-LSTM) and Deep Neural Network (DNN) which absorbs individual residuals of both the forward and reverse LSTMs that acts as an important feature to improve the overall prediction process. The work validated using CMAPPS dataset using various unique performance metrics to portray the effectiveness of the model.
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Research ethics: Not Applicable.
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Author contributions: The authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Competing interests: The authors state no conflict of interest.
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Research funding: None declared.
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Data availability: Not applicable.
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© 2024 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Deep residual ensemble model for predicting remaining useful life of turbo fan engines
- Review of gliding arc plasma assisted ignition and combustion for gas turbine application
- Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
- Determination of the modern marine single shaft gas turbine rotor blades fatigue strength parameters
- Role of different cavity flame holders on the performance characteristics of supersonic combustor
- Thermal performance of teardrop pin fins and zig zag ribs in a wedge channel
- Investigation of varying tip clearance gap and operating conditions on the fulfilment of low-speed axial flow fan
- Upgraded one-dimensional code for the design of a micro gas turbine mixed flow compressor stage with various crossover diffuser configurations
- Performance evaluation of a scramjet engine utilizing varied cavity aft wall divergence with parallel injection in a reacting flow field
- Speed controller design for turboshaft engine using a high-fidelity AeroThermal model
- Multi-nozzle thrust matching control of STOVL engine
- Numerical analysis of brush seal hysteresis based on orthogonal test method
- Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition
- Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
- Flight trajectory optimization study of a variable-cycle turbine-based combined cycle engine hypersonic vehicle based on airframe/engine integration
- Constant temperature line identification on prototype gas turbine combustor with multi-colour change coating
- Sensitivity analysis of aero-engine performance optimization control system and its hardware test verification
- Compensator based improved model predictive control for Aero-engine
- Ignition experimental study based on rotating gliding arc
Articles in the same Issue
- Frontmatter
- Deep residual ensemble model for predicting remaining useful life of turbo fan engines
- Review of gliding arc plasma assisted ignition and combustion for gas turbine application
- Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
- Determination of the modern marine single shaft gas turbine rotor blades fatigue strength parameters
- Role of different cavity flame holders on the performance characteristics of supersonic combustor
- Thermal performance of teardrop pin fins and zig zag ribs in a wedge channel
- Investigation of varying tip clearance gap and operating conditions on the fulfilment of low-speed axial flow fan
- Upgraded one-dimensional code for the design of a micro gas turbine mixed flow compressor stage with various crossover diffuser configurations
- Performance evaluation of a scramjet engine utilizing varied cavity aft wall divergence with parallel injection in a reacting flow field
- Speed controller design for turboshaft engine using a high-fidelity AeroThermal model
- Multi-nozzle thrust matching control of STOVL engine
- Numerical analysis of brush seal hysteresis based on orthogonal test method
- Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition
- Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
- Flight trajectory optimization study of a variable-cycle turbine-based combined cycle engine hypersonic vehicle based on airframe/engine integration
- Constant temperature line identification on prototype gas turbine combustor with multi-colour change coating
- Sensitivity analysis of aero-engine performance optimization control system and its hardware test verification
- Compensator based improved model predictive control for Aero-engine
- Ignition experimental study based on rotating gliding arc
