Measuring-Diagnostic System for Monitoring and Evaluating the Operational Reliability of Rotor Blades for Aircraft Gas Turbine Engines by Acoustic Emission Method

2020 ◽  
Vol 897 ◽  
pp. 190-194
Author(s):  
Margarita Urbaha ◽  
Alexander Urbah ◽  
Mukharbiy Banov ◽  
Vladimir Shestakov ◽  
Pavel Pogorodny
Keyword(s):  
Acoustic Emission ◽  
Gas Turbine ◽  
Early Stage ◽  
Diagnostic System ◽  
Operational Reliability ◽  
Rotor Blades ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Acoustic Emission Method ◽  
Emission Method

Diagnostics of the rotor blades of aircraft gas turbine engines at pre-operational stage and later on during repairs is carried out by instrumental methods of non-destructive testing. The requirements for increasing operational reliability and safety of flights require a search for new solutions in assessing the strength of rotor blades at an early stage of damage development. For these purposes, one of the perspective directions is the development of acoustic emission methods. This article represents an experimental setup and a measuring-diagnostic system for assessing the operational reliability of rotor blades by the acoustic emission method. It also discusses the results of testing.

Developing and Deploying ICAS-Capable CBM Software Modules: Best Practices and Lessons Learned

2005 ◽  
Author(s):  
Matthew J. Watson ◽  
Carl S. Byington ◽  
Bryan Donovan ◽  
Greg Kacprzynski ◽  
Assaad Krichene ◽  
...  
Keyword(s):  
Best Practices ◽  
Gas Turbine ◽  
Diagnostic System ◽  
Lessons Learned ◽  
Assessment System ◽  
Third Party ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Electrical Systems ◽  
Software Modules

The U.S. Navy’s Integrated Condition Assessment System (ICAS) is a shipboard monitoring system that helps enable the Navy’s Condition Based Maintenance (CBM) initiative. ICAS is installed on a large number of Navy Surface Combatants and provides data acquisition, display, and logging, as well as equipment diagnostic analysis for troubleshooting and maintenance tasking of hull mechanical and electrical systems. In recent years, it has been desirable to integrate specialized, third party diagnostic or prognostic software as plug ‘n play modules within the ICAS environment. A specific effort focused on such modules for shipboard LM2500 and Allison 501K gas turbine engines is well underway. Over the course of this three-year Prognostic Enhancement to Diagnostic System (PEDS) program, many lessons have been learned, best practices for ICAS integration have been identified, and the important steps required to field ICAS-capable modules have been realized. This paper summarizes these lessons and processes for future 3rd party integration efforts and provides specific examples for the developed gas turbine modules. The successful deployment of these modules aboard Navy ships is used to validate the ideas presented.

Multipoint Non-Linear Method for Enhanced Component and Sensor Malfunction Diagnosis

2006 ◽  
Author(s):  
Philippos Kamboukos ◽  
Kostas Mathioudakis
Keyword(s):  
Gas Turbine ◽  
Linear Method ◽  
Computational Cost ◽  
Diagnostic System ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Engine Component ◽  
Malfunction Diagnosis ◽  
Operating Points ◽  
Health Parameters

Operating gas turbine engines are usually equipped with a limited number of sensors. This situation is the common issue of gas turbine diagnostics where the absence of sufficient measurements from the engine gas path reduces the effectiveness of the applied methods. In addition the installed sensors of the engine deteriorate with time or present abrupt malfunctions which are not always detectable. One way to overcome this problem is the exploitation of information from a number of different operating points by constructing a multipoint diagnostic procedure. Information from different operating points is combined in order to increase the number of measurements and thus to form a well determined diagnostic system for the estimation of engine component health parameters. The paper presents the extension of the method in order to be able to assess both engine and sensors state. Initially the ability of the method to estimate the condition of a high bypass turbofan engine, exploiting information from different instances of its flight envelop is depicted. The problem of selecting the appropriate operating points is analyzed on the basis of the numerical condition of the formed diagnostic system. The method is also applied to a single shaft turbojet, for estimation of engine component health parameters and sensors state. Finally a number of aspects related to the formulation of the method are examined. These are the comparison between full method and its linear approximation, the effect of measurement noise on the derived estimation and the computational cost.

Analysis of fatigue failure of rotor blades of gas turbine engines made of cast nickel-chrome alloys of the ZhS type

1987 ◽  
Vol 19 (1) ◽  
pp. 52-57
Author(s):  
I. A. Makovetskaya ◽  
O. I. Marusii ◽  
B. A. Gryaznov ◽  
Yu. S. Nalimov
Keyword(s):  
Gas Turbine ◽  
Fatigue Failure ◽  
Rotor Blades ◽  
Turbine Engines ◽  
Gas Turbine Engines

Using the Similarity Theory in the Design of Gas Turbine Engines

2021 ◽  
pp. 48-57
Author(s):  
V.D. Molyakov ◽  
B.A. Kunikeev
Keyword(s):  
Gas Turbine ◽  
Rotor Blade ◽  
Similarity Theory ◽  
Rotor Blades ◽  
Design Flow ◽  
Fourth Generation ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Temperature ◽  
Turbine Stage

At present, in the promising development of gas turbine engines compared to at least the fourth generation products, there have been significant changes in the approaches to the design of engine. First of all, it is an increase in maximum values of temperature, gas pressure and circumferential flow speeds, an increase in power of the turbine stage, as well as improvement of the turbine manufacturing technology. All these factors lead to the fact that when designing the flow parts of the gas turbine, it is necessary at the fixed design flow rate of the working medium in the engine, i.e. at the fixed diameters, lengths of the nozzle and rotor blades forming the outline of the inter-blade channels, to increase the blade chords with the corresponding reduction of the number of blades in the row. The increase in turbine stage power associated with the increase in temperature, pressure (density), and circumferential velocity increases the bending stresses leading to the need to increase chords at a fixed blade length. Significant reduction of number of blades in stages, simplifies technology of blades manufacturing. A substantial increase in the maximum gas temperature, in the perspective of more than 2000 K, also leads to the need to increase the blade chords, due to the need to place cooling cavities in the blades. As a result, contradictions arise with the use of similarity theory in the design of stages of turbines of different purpose, as some of the main requirements of similarity are violated — geometric similarity of blade channels of the flow part and then the use of the generally accepted number Re by the chord of blades loses meaning. Therefore, it is necessary to carry out detailed investigations of all flow parameters in four stages of turbines with detection of influence of change of rotor blade chords at equal length of blades. And justify the effect of change of rotor blade chords on physical processes in flow parts of turbines in engines of various purpose.

scholarly journals Automated Diagnostic System for Engine Maintenance

1983 ◽  
Author(s):  
Frank Fanuele ◽  
Richard A. Rio
Keyword(s):  
Gas Turbine ◽  
Air Force ◽  
Gas Turbines ◽  
Diagnostic System ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Data Set ◽  
Jet Engine ◽  
Vibration Data ◽  
Engine Maintenance

The rapidly increasing costs of maintenance, the demand for increased equipment utilization, fuel costs and the difficulty of correctly diagnosing internal mechanical problems in operating gas turbine engines has stressed the requirement for more effective monitoring and diagnostic equipment. Such equipment must be capable of performing three functions: 1. Acquiring condition data from operating gas turbines, 2. Analyzing the acquired data, and 3. Associating the cause and effect relationship to an incipient malfunction. This paper describes the MTI Automated Vibration Diagnostic System (AVID) developed for the U. S. Air Force jet engine overhaul centers. The AVID concept is to automate troubleshooting procedures for fully assembled gas turbine engines. The System extracts high-frequency vibration data from existing, standard instrumentation to provide input to a specialized Symptom/Fault Matrix. This Symptom/Fault Matrix is configured to analyze the incoming data and assign a particular malfunction (or malfunctions) to a specified data set. This diagnosis is then printed out to provide maintenance personnel with exact knowledge of what the problem is and how to correct it. This System, plus the growing awareness on the part of personnel of the capabilities of such automated equipment, will enable the Air Force to significantly reduce expenses at their jet engine overhaul facilities.

scholarly journals A Review of the Bases of Predicting Heat Transfer to Gas Turbine Rotor Blades

1974 ◽  
Author(s):  
A. Brown ◽  
B. W. Martin
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Turbine Rotor ◽  
Rotor Blades ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Mainstream Flow ◽  
Streamwise Pressure Gradient

This paper reviews the methods for predicting boundary-layer behavior on flat and curved surfaces under conditions experienced in gas turbine engines and the resultant heat transfer to the turbine rotor blades. Particular attention is given to the effects of streamwise pressure gradient and the intensity of mainstream turbulence on transition phenomena. The time-mean heat transfer across a boundary-layer under unidirectional oscillatory mainstream flow, such as might be initiated in a combustion chamber, is considered. The relevance of flat plate predictions and correlations to rotating turbine blades is also discussed.

scholarly journals ACOUSTIC EMISSION TESTING OF FIBERGLASS PIPES AND FITTINGS

2021 ◽  
pp. 12-25
Author(s):  
S. V. Elizarov ◽  
D. A. Terentyev ◽  
K. A. Medvedev ◽  
V. I. Ivanov ◽  
A. G. Halimov ◽  
...  
Keyword(s):  
Acoustic Emission ◽  
Residual Life ◽  
Early Stage ◽  
Experimental Studies ◽  
Operating Mode ◽  
Acoustic Emission Method ◽  
Emission Method ◽  
Dimensional Inspection ◽  
Emission Testing ◽  
Acoustic Emission Testing

Experimental studies was carried out. The purpose was to develop a method to test fiberglass pipelines in operating mode. The acoustic emission method was chosen as the main method of nondestructive testing, and visual and dimensional inspection was chosen as an additional method. Acoustic parameters and acoustic emission properties of fiberglass pipes were determined. It was found that acoustic emission sensors can be installed at distances of up to 9-18 m from each other. A series of loading tests was carried out to refine the methodology. Every loading case was performed until leakage registration. In most cases, leakage occurred near the fillet at pressures of 2.2…3.0 from the working pressure, which indicates a large margin of safety for fiberglass pipes. It is confirmed that the acoustic emission method allows early defect detection. Based on the acoustic emission data, 4 main stages of fiberglass pipes degradation were identified. Visual and dimensional inspection was informative only at stages III – IV. Stage IV in most cases corresponds to the leakage. Even early stage of depressurization was registered as continuous acoustic emission. Signals with amplitudes exceeding 60…80 dB were registered at all loading stages. The location map became informative after filtering events by acoustic emission parameters. A methodology for the testing of fiberglass pipes and fittings in operating mode was developed. It contains, in contrast to the currently valid standards, specific numerical values of various quantities related to both the preparation and carrying out of acoustic emission testing and the classification of the identified sources of acoustic emission according to the degree of danger and allows to evaluate the residual life of fiberglass pipelines. The most informative parameter was the activity of acoustic emission; therefore, it is recommended to carry out loading without holding the pressure. It is planned to carry out additional experiments to clarify the mechanisms of fracture acting at each of the 4 identified stages of degradation.

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