CF6 jet engine performance deterioration

1979 ◽  
Author(s):  
R. WULF
Keyword(s):  
Engine Performance ◽  
Jet Engine ◽  
Performance Deterioration

Prediction of the Jet Engine Performance Deterioration

2012 ◽  
Author(s):  
Maryam Gholamhossein ◽  
Ameneh Vatani ◽  
Najmeh Daroogheh ◽  
K. Khorasani
Keyword(s):  
Moving Average ◽  
Engine Performance ◽  
Multivariate Methods ◽  
Jet Engine ◽  
Turbine Engine ◽  
Vector Autoregressive ◽  
Autoregressive Integrated Moving Average ◽  
Multivariate Modelling ◽  
Performance Deterioration ◽  
Modelling Methods

This paper deals with performance deterioration modelling of a single spool gas turbine engine based on time-series methods. Towards this end, two univariate and multivariate methods, namely the Autoregressive Integrated Moving Average (ARIMA) and the Vector Autoregressive (VAR) schemes are applied to predict the Turbine Entry Temperature (TET) evolution during the flight cycles for maintenance purposes. In the VAR scheme, two engine process parameters i.e. the Turbine Entry Temperature (TET) and the Compressor Temperature are employed to achieve this prediction goal. The results show that employing multivariate modelling methods lead to better prediction horizons. For each method two scenarios are considered to demonstrate the effectiveness of the models.

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.

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.

scholarly journals Online Water Wash Tests of GE J85-13

2007 ◽  
Vol 129 (1) ◽  
pp. 136-142 ◽  
Author(s):  
Elisabet Syverud ◽  
Lars E. Bakken
Keyword(s):  
Air Force ◽  
Droplet Size ◽  
Pressure Sensors ◽  
Engine Performance ◽  
Jet Engine ◽  
Additional Information ◽  
Droplet Sizes ◽  
Temperature And Pressure ◽  
Visual Observations

This paper reports the results of a series of online water wash tests of a GE J85-13 jet engine at the test facilities of the Royal Norwegian Air Force. The engine performance was deteriorated by injecting atomized saltwater at the engine inlet. The engine was then online washed with water injected at three different droplet sizes (25, 75, and 200μm) and at water-to-air ratios ranging from 0.4% to 3% by mass. Engine performance was measured using standard on-engine instrumentation. Extra temperature and pressure sensors in the compressor section provided additional information of the propagation of deposits in the aft stages. The measurements were supported by visual observations. The overall engine performance improved rapidly with online wash. The buildup of deposits in the aft stages was influenced both by the droplet size and the water-to-air ratio. The water-to-air ratio was the most important parameter to achieve effective online washing.

I221 The influence of chevron nozzle on jet engine performance

2014 ◽  
Vol 2014 (0) ◽  
pp. _I221-1_-_I221-2_
Author(s):  
Ryosuke Matsuda ◽  
Toshiaki Tuchiya
Keyword(s):  
Engine Performance ◽  
Jet Engine ◽  
Chevron Nozzle

Performance deterioration and durability issues while running a diesel engine with crude palm oil

2002 ◽  
Vol 216 (9) ◽  
pp. 785-792 ◽  
Author(s):  
S Bari ◽  
C W Yu ◽  
T H Lim
Keyword(s):  
Diesel Engine ◽  
Palm Oil ◽  
Engine Performance ◽  
Cylinder Liner ◽  
Diesel Emissions ◽  
Maximum Power ◽  
Crude Palm Oil ◽  
Carbon Deposits ◽  
Injection Pump ◽  
Performance Deterioration

Short-term performance tests using crude palm oil (CPO) as fuel for a diesel engine showed CPO to be a suitable substitute, with a peak pressure about 5 per cent higher and an ignition delay about 3° shorter compared with diesel. Emissions of NO and CO were about 29 and 9 per cent higher respectively for CPO. However, prolonged use of CPO as fuel caused the engine performance to deteriorate. After 500 h cumulative running with CPO, the maximum power was reduced by about 20 per cent and the minimum brake specific fuel consumption (b.s.f.c.) was increased by about 26 per cent. Examination of the different parts after the engine was dismantled revealed heavy carbon deposits in the combustion chamber; traces of wear on the piston rings, the plunger and the delivery valve of the injection pump; slight scuffing of the cylinder liner; and uneven spray from the nozzles. The affected parts were installed in a new identical engine one by one to evaluate the performance of each respectively. Tests revealed that the main reason for engine performance deterioration was ‘valve sticking’, caused by carbon deposits on the valve seats and stems. This resulted in leakage during the compression and power strokes and a reduced effective compression ratio and subsequently affected the power and fuel economy. Valve sticking alone contributed about 18 and 23 per cent to the deterioration in maximum power and minimum b.s.f.c. respectively.

Performance Deterioration in Industrial Gas Turbines

1992 ◽  
Vol 114 (2) ◽  
pp. 161-168 ◽  
Author(s):  
I. S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

Sign in / Sign up

Export Citation Format

Share Document