scholarly journals Application of a Bank of Kalman Filters for Aircraft Engine Fault Diagnostics

2003 ◽  
Author(s):  
Takahisa Kobayashi ◽  
Donald L. Simon
Keyword(s):  
Kalman Filters ◽  
Aircraft Engine ◽  
Operating Conditions ◽  
Fault Detection And Isolation ◽  
Actuator Fault ◽  
Estimation Errors ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Correct Hypothesis ◽  
The One

In this paper, a bank of Kalman filters is applied to aircraft gas turbine engine sensor and actuator fault detection and isolation (FDI) in conjunction with the detection of component faults. This approach uses multiple Kalman filters, each of which is designed for detecting a specific sensor or actuator fault. In the event that a fault does occur, all filters except the one using the correct hypothesis will produce large estimation errors, thereby isolating the specific fault. In the meantime, a set of parameters that indicate engine component performance is estimated for the detection of abrupt degradation. The proposed FDI approach is applied to a nonlinear engine simulation at nominal and aged conditions, and the evaluation results for various engine faults at cruise operating conditions are given. The ability of the proposed approach to reliably detect and isolate sensor and actuator faults is demonstrated.

scholarly journals Evaluation of an Enhanced Bank of Kalman Filters for In-Flight Aircraft Engine Sensor Fault Diagnostics

2005 ◽  
Vol 127 (3) ◽  
pp. 497-504 ◽  
Author(s):  
Takahisa Kobayashi ◽  
Donald L. Simon
Keyword(s):  
Kalman Filter ◽  
Kalman Filters ◽  
Aircraft Engine ◽  
Propulsion System ◽  
Fault Detection And Isolation ◽  
Actuator Faults ◽  
Commercial Aircraft ◽  
Nonlinear Simulation ◽  
Turbine Engine ◽  
Correct Hypothesis

In this paper, an approach for in-flight fault detection and isolation (FDI) of aircraft engine sensors based on a bank of Kalman filters is developed. This approach utilizes multiple Kalman filters, each of which is designed based on a specific fault hypothesis. When the propulsion system experiences a fault, only one Kalman filter with the correct hypothesis is able to maintain the nominal estimation performance. Based on this knowledge, the isolation of faults is achieved. Since the propulsion system may experience component and actuator faults as well, a sensor FDI system must be robust in terms of avoiding misclassifications of any anomalies. The proposed approach utilizes a bank of m+1 Kalman filters where m is the number of sensors being monitored. One Kalman filter is used for the detection of component and actuator faults while each of the other m filters detects a fault in a specific sensor. With this setup, the overall robustness of the sensor FDI system to anomalies is enhanced. Moreover, numerous component fault events can be accounted for by the FDI system. The sensor FDI system is applied to a nonlinear simulation of a commercial aircraft gas turbine engine, and its performance is evaluated at multiple power settings at a cruise operating point using various fault scenarios.

scholarly journals Evaluation of an Enhanced Bank of Kalman Filters for In-Flight Aircraft Engine Sensor Fault Diagnostics

2004 ◽  
Author(s):  
Takahisa Kobayashi ◽  
Donald L. Simon
Keyword(s):  
Kalman Filter ◽  
Kalman Filters ◽  
Aircraft Engine ◽  
Propulsion System ◽  
Fault Detection And Isolation ◽  
Actuator Faults ◽  
Commercial Aircraft ◽  
Engine Simulation ◽  
Correct Hypothesis ◽  
Multiple Power

In this paper, an approach for in-flight fault detection and isolation (FDI) of aircraft engine sensors based on a bank of Kalman filters is developed. This approach utilizes multiple Kalman filters, each of which is designed based on a specific fault hypothesis. When the propulsion system experiences a fault, only one Kalman filter with the correct hypothesis is able to maintain the nominal estimation performance. Based on this knowledge, the isolation of faults is achieved. Since the propulsion system may experience component and actuator faults as well, a sensor FDI system must be robust in terms of avoiding misclassifications of any anomalies. The proposed approach utilizes a bank of (m+1) Kalman filters where m is the number of sensors being monitored. One Kalman filter is used for the detection of component and actuator faults while each of the other m filters detects a fault in a specific sensor. With this setup, the overall robustness of the sensor FDI system to anomalies is enhanced. Moreover, numerous component fault events can be accounted for by the FDI system. The sensor FDI system is applied to a commercial aircraft engine simulation, and its performance is evaluated at multiple power settings at a cruise operating point using various fault scenarios.

AeroEngineS: Multi-Platform Application for Aero Engine Simulation and Compressor Map Operating Point Prediction

2019 ◽  
Author(s):  
Evangelia C. Pontika ◽  
Anestis I. Kalfas ◽  
Ioanna Aslanidou
Keyword(s):  
Gas Turbine ◽  
Thermodynamic Cycle ◽  
Aircraft Engine ◽  
Design Tool ◽  
Operating Conditions ◽  
Operating Point ◽  
Engine Simulation ◽  
Aero Engine ◽  
Compressor Map ◽  
User Friendly

Abstract This paper presents the development of AeroEngineS (Aircraft Engine Simulation), a multi-platform app with graphical user interface for aero engine simulation and compressor map operating point prediction. Gas turbine performance simulation is a crucial part of the design process. It provides information about the required operating conditions of all the components and the overall performance of the engine so that engineers can determine whether the current engine configuration meets the performance requirements. Some gas turbine simulation programs have been developed in the last decades, however, there was a lack of an open-source, lightweight, user-friendly, but still very accurate, application which would be easily accessible from all platforms. AeroEngineS can be used as a user-friendly preliminary design tool, since, during this design phase, details about the geometry are not known yet. The main aim is to calculate simply and quickly the basic parameters of the thermodynamic cycle and the performance, in order to determine which design is able to meet the required specifications. AeroEngineS constitutes a free and simple app which can primarily serve educational purposes as it is easily accessible by students from any platform to assist them in aero engine technology courses. Secondarily, it has the potential to be used even by engineers as a quick tool accessible from all devices. The app consists of two basic stand-alone functions. The first function is aero engine simulation at Design Point which solves thermodynamic calculations. The second function is compressor map operating point prediction using a novel method of combining scaling techniques and Artificial Neural Networks.

Aero-Thermodynamic Modelling and Gas Path Simulation for a Twin Spool Turbo Jet Engine

2013 ◽  
Author(s):  
Balaji Sankar ◽  
Thennavarajan Subramanian ◽  
Brijeshkumar Shah ◽  
Vijayendranath Vanam ◽  
Soumendu Jana ◽  
...  
Keyword(s):  
Simulation Model ◽  
Gas Turbine ◽  
Simulation Models ◽  
Operating Conditions ◽  
Test Bed ◽  
Jet Engine ◽  
Turbine Engine ◽  
Design Point ◽  
Engine Simulation ◽  
Engine Components

The user community of civil and military aircraft powered by gas turbine engines has a significant interest on simulation models for design, development and maintenance activities. These play a crucial role in understanding the aircraft mission performance. The simulation models can be used to understand the behavior of gas turbine engine running at various operating conditions, which are used for studying the aircraft performance and also vital for engine diagnostics. Other significant advantage of simulation model is that it can generate required data at intermediate stages in gas turbine engine, which sometimes cannot be obtained by measurement. Thus engine simulation model / virtual engine building is one of the important aspects towards development of Engine Health Management (EHM) system. This paper describes in detail the engine simulation model development for a typical twin spool turbo jet engine using commercially available Gas turbine Simulation Program (GSP). The engine simulation model has been used for typical aero-engine to get aero-thermodynamic gas path performance analysis related to engine run at Design point, Off Design points and the engine Acceleration-Deceleration Cycles (ADC). Simulations at different operating conditions have been carried out using scaled up characteristic maps of engine components. Design point data as well as engine gas path data obtained from test bed has been used to develop scaled up characteristic maps of the engine components. The simulation results have been compared with various test bed data sets for the purpose of validation. Predicted results of engine parameters like engine mass flow rate and thrust are in good agreement with the test bed data. This validated model can be used to simulate faulty engine components and to develop the fault identification modules and subsequently an EHM system.

scholarly journals Optimal Tuner Selection for Kalman Filter-Based Aircraft Engine Performance Estimation

2009 ◽  
Vol 132 (3) ◽  
Author(s):  
Donald L. Simon ◽  
Sanjay Garg
Keyword(s):  
Kalman Filter ◽  
Estimation Error ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Operating Conditions ◽  
Performance Estimation ◽  
Experimental Simulation ◽  
Tuning Parameter ◽  
Estimation Accuracy ◽  
On Line

A linear point design methodology for minimizing the error in on-line Kalman filter-based aircraft engine performance estimation applications is presented. This technique specifically addresses the underdetermined estimation problem, where there are more unknown parameters than available sensor measurements. A systematic approach is applied to produce a model tuning parameter vector of appropriate dimension to enable estimation by a Kalman filter, while minimizing the estimation error in the parameters of interest. Tuning parameter selection is performed using a multivariable iterative search routine that seeks to minimize the theoretical mean-squared estimation error. This paper derives theoretical Kalman filter estimation error bias and variance values at steady-state operating conditions, and presents the tuner selection routine applied to minimize these values. Results from the application of the technique to an aircraft engine simulation are presented and compared with the conventional approach of tuner selection. Experimental simulation results are found to be in agreement with theoretical predictions. The new methodology is shown to yield a significant improvement in on-line engine performance estimation accuracy.

scholarly journals Recovery of Anthocyanins and Monosaccharides from Grape Marc Extract by Nanofiltration Membranes

Molecules ◽  
2021 ◽  
Vol 26 (7) ◽  
pp. 2003
Author(s):  
Paul Muñoz ◽  
Karla Pérez ◽  
Alfredo Cassano ◽  
René Ruby-Figueroa
Keyword(s):  
Functional Foods ◽  
General Trend ◽  
Value Added ◽  
Operating Conditions ◽  
Permeate Flux ◽  
Ultrasound Assisted Extraction ◽  
Grape Marc ◽  
Assisted Extraction ◽  
The One ◽  
By Products

Wastewaters and by-products generated in the winemaking process are important and inexpensive sources of value-added compounds that can be potentially reused for the development of new products of commercial interest (i.e., functional foods). This research was undertaken in order to evaluate the potential of nanofiltration (NF) membranes in the recovery of anthocyanins and monosaccharides from a clarified Carménère grape marc obtained through a combination of ultrasound-assisted extraction and microfiltration. Three different flat-sheet nanofiltration (NF) membranes, covering the range of molecular weight cut-off (MWCO) from 150 to 800 Da, were evaluated for their productivity as well as for their rejection towards anthocyanins (malvidin-3-O-glucoside, malvidin 3-(acetyl)-glucoside, and malvidin 3-(coumaroyl)-glucoside) and sugars (glucose and fructose) in selected operating conditions. The selected membranes showed differences in their performance in terms of permeate flux and rejection of target compounds. The NFX membrane, with the lowest MWCO (150–300 Da), showed a lower flux decay in comparison to the other investigated membranes. All the membranes showed rejection higher than 99.42% for the quantified anthocyanins. Regarding sugars rejection, the NFX membrane showed the highest rejection for glucose and fructose (100 and 92.60%, respectively), whereas the NFW membrane (MWCO 300–500 Da) was the one with the lowest rejection for these compounds (80.57 and 71.62%, respectively). As a general trend, the tested membranes did not show a preferential rejection of anthocyanins over sugars. Therefore, all tested membranes were suitable for concentration purposes.

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