Turbofan Engine Performance Deterioration Due To Fan Erosion

2019 ◽  
Vol 12 (2) ◽  
pp. 93
Author(s):  
H. Z. Hassan ◽  
M. H. Gobran ◽  
A. F. El-Saied
Keyword(s):  
Engine Performance ◽  
Turbofan Engine ◽  
Performance Deterioration

Effect of Time-Dependent Flight Loads on Turbofan Engine Performance Deterioration

1982 ◽  
Vol 104 (3) ◽  
pp. 692-697
Author(s):  
B. L. Lewis ◽  
A. Jay ◽  
E. G. Stakolich
Keyword(s):  
Engine Performance ◽  
Short Term ◽  
Propulsion Systems ◽  
Turbofan Engine ◽  
Jet Propulsion ◽  
Analytical Technique ◽  
Analytical Studies ◽  
Performance Deterioration ◽  
Flight Loads ◽  
Term Performance

A jet engine’s efficiency is strongly dependent upon clearances between rotating blades and the corresponding stationary gas-path seals. Analytical studies to examine the effects of various flight cycle loads on powerplant clearances suggest that rotor/seal interferences may contribute to the short-term performance deterioration exhibited by all high bypass jet propulsion systems. In prior analytical studies, flight cycle loads were treated in a quasi-steady, static manner, even though some flight cycle loadings are decidedly dynamic in nature. Gust encounters and aircraft landings are classical examples of dynamic flight loads found in typical airline service. An analytical technique for predicting the effects of aircraft dynamic flight loads on engine performance was developed and is described herein.

scholarly journals An Integrated Approach for Aircraft Engine Performance Estimation and Fault Diagnostics

2013 ◽  
Vol 135 (7) ◽  
Author(s):  
Donald L. Simon ◽  
Jeffrey B. Armstrong
Keyword(s):  
Kalman Filter ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Fault Isolation ◽  
Performance Estimation ◽  
Estimation Accuracy ◽  
Fault Diagnostics ◽  
Tuning Parameters ◽  
Performance Deterioration ◽  
Health Parameters

A Kalman filter-based approach for integrated on-line aircraft engine performance estimation and gas path fault diagnostics is presented. This technique is specifically designed for underdetermined estimation problems where there are more unknown system parameters representing deterioration and faults than available sensor measurements. A previously developed methodology is applied to optimally design a Kalman filter to estimate a vector of tuning parameters, appropriately sized to enable estimation. The estimated tuning parameters can then be transformed into a larger vector of health parameters representing system performance deterioration and fault effects. The results of this study show that basing fault isolation decisions solely on the estimated health parameter vector does not provide ideal results. Furthermore, expanding the number of the health parameters to address additional gas path faults causes a decrease in the estimation accuracy of those health parameters representative of turbomachinery performance deterioration. However, improved fault isolation performance is demonstrated through direct analysis of the estimated tuning parameters produced by the Kalman filter. This was found to provide equivalent or superior accuracy compared to the conventional fault isolation approach based on the analysis of sensed engine outputs, while simplifying online implementation requirements. Results from the application of these techniques to an aircraft engine simulation are presented and discussed.

Analysis of Effect of Advanced Technique Configurations on Overall Performance of High Bypass Turbofan Engine

2014 ◽  
Author(s):  
Liu Jian Jun
Keyword(s):  
Air Flow ◽  
Engine Performance ◽  
Performance Model ◽  
Direct Drive ◽  
Nozzle Throat ◽  
Advanced Technique ◽  
Turbofan Engine ◽  
Overall Performance ◽  
Cooling Air Flow ◽  
Cooling Air

An analytical study was undertaken using the performance model of a two spool direct drive high BPR 300kN thrust turbofan engine, to investigate the effects of advanced configurations on overall engine performance. These include variable bypass nozzle, variable cooling air flow and more electric technique. For variable bypass nozzle, analysis on performance of outer fan at different conditions indicates that different operating points cannot meet optimal performance at the same time if the bypass nozzle area kept a constant. By changing bypass nozzle throat area at different states, outer fan operating point moves to the location where airflow and efficiency are more appropriate, and have enough margin away from surge line. As a result, the range of variable area of bypass nozzle throat is determined which ensures engine having a low SFC and adequate stability. For variable cooling airflow, configuration of turbine cooling air flow extraction and methodology for obtaining change of cooling airflow are investigated. Then, base on temperature analysis of turbine vane and blade and resistance of cooling airflow, reduction of cooling airflow is determined. Finally, using performance model which considering effect of cooling air flow on work and efficiency of turbine, variable cooling airflow effect on overall performance is analyzed. For more electric technique, the main characteristic is to use power off-take instead of overboard air extraction. Power off-take and air extraction effect on overall performance of high bypass turbofan engine is compared. Investigation demonstrates that power offtake will have less SFC.

Entropy, Energy and Exergy for Measuring PW4000 Turbofan Sustainability

2019 ◽  
Vol 0 (0) ◽  
Author(s):  
Hakan Aygun ◽  
Onder Turan
Keyword(s):  
Thrust Force ◽  
Engine Performance ◽  
Sustainable Growth ◽  
Performance Parameters ◽  
Turbofan Engine ◽  
Effect Factor ◽  
Energy And Exergy ◽  
And Performance ◽  
Engine Components ◽  
Main Engine

Abstract This study focuses on for a PW4000 high-bypass turbofan engine using energy, exergo-sustainable and performance viewpoint. For this aim, irreversibility and performance analyses are firstly performed for five main engine components at ≈260 kN maximum take-off thrust force. Besides, overall efficiency of the turbofan is determined to be 33 %, while propulsive and thermal efficiency of the turbofan are 72 % and 46 % respectively at 0.8 M and 288.15 K flight conditions. Secondly, calculation component-based exergetic assessment is carried out using exergetic indicators. According to the calculation, the exergetic efficiency of the engine is 32 %, while its waste exergy ratio is 0.678. Furthermore, exergetic sustainability measure is obtained as 0.473, while enviromental effect factor is 2.112. These indicators are also anticipated to help comprehend the connection between engine performance parameters and worldwide dimensions such as environmental effect and sustainable growth.

scholarly journals Scale effects on conventional and intercooled turbofan engine performance-CORRIGENDUM

2017 ◽  
Vol 121 (1242) ◽  
pp. 1186-1186
Author(s):  
A. Rolt ◽  
V. Sethi ◽  
F. Jacob ◽  
J. Sebastiampillai ◽  
C. Xisto ◽  
...  
Keyword(s):  
Scale Effects ◽  
Engine Performance ◽  
Turbofan Engine ◽  
Correct Equation ◽  
Image Position

In the article by Rolt(1), there was an error in Equation (2). The correct equation is republished here. 2$$\begin{equation} {W_c} = \ \frac{{{W_{\it cref}}\left( {{T_{\it grel}} - {T_{\it cref}}} \right){{({W_4}/{W_{\it 4ref}})}^{0.65}}}}{{\left( {{T_{\it gref}} - {T_c}} \right)}}\ \ \ \ \ \ \ \end{equation}$$

Modeling Particle Deposition Effects in Aircraft Engine Compressors

2017 ◽  
Vol 139 (5) ◽  
Author(s):  
Felix Döring ◽  
Stephan Staudacher ◽  
Christian Koch ◽  
Matthias Weißschuh
Keyword(s):  
Gas Turbines ◽  
Particle Deposition ◽  
Axial Compressor ◽  
Pressure Rise ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Deposition Process ◽  
Aircraft Engines ◽  
Blade Row ◽  
Performance Deterioration

Airborne particles ingested in aircraft engines deposit on compressor blading and end walls. Aerodynamic surfaces degrade on a microscopic and macroscopic scale. Blade row, compressor, and engine performance deteriorate. Optimization of maintenance scheduling to mitigate these effects requires modeling of the deterioration process. This work provides a deterioration model on blade row level and the experimental validation of this model in a newly designed deposition test rig. When reviewing previously published work, a clear focus on deposition effects in industrial gas turbines becomes evident. The present work focuses on quantifying magnitudes and timescales of deposition effects in aircraft engines and the adaptation of the generalized Kern and Seaton deposition model for application in axial compressor blade rows. The test rig's cascade was designed to be representative of aircraft engine compressor blading. The cascade was exposed to an accelerated deposition process. Reproducible deposition patterns were identified. Results showed an asymptotic progression of blade row performance deterioration. A significant increase in total pressure loss and decrease in static pressure rise were measured. Application of the validated model using existing particle concentration and flight cycle data showed that more than 95% of the performance deterioration due to deposition occurs within the first 1000 flight cycles.

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