Fast Response Wall Pressure Measurement as a Means of Gas Turbine Blade Fault Identification

1991 ◽  
Vol 113 (2) ◽  
pp. 269-275 ◽  
Author(s):  
K. Mathioudakis ◽  
A. Papathanasiou ◽  
E. Loukis ◽  
K. Papailiou
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Pressure Field ◽  
Fast Response ◽  
Gas Turbine Blade ◽  
Unsteady Pressure ◽  
Rotating Blade ◽  
Processing Techniques ◽  
Industrial Gas Turbine ◽  
Unsteady Pressure Measurements

The distortions of the pressure field around rotating blades of turbomachinery components due to alterations of their shape can be utilized for the identification of faults related to the blading. Measurement of the unsteady pressure field near the wall provides information on such flow and pressure distortions and can thus be used for diagnostic purposes. An experimental investigation of the compressor rotating blade pressure field of an industrial gas turbine has been undertaken, in order to demonstrate the feasibility of the abovementioned principle. Various realistic gas turbine blade faults have been examined. Application of the appropriate processing techniques demonstrates that unsteady pressure measurements can be used to identify the occurrence of minor blade faults (not traceable by standard techniques) as well as the kind of fault. The proposed methodology has the potential for being incorporated in a computerized engine health monitoring system.

Fast Response Wall Pressure Measurement as a Means of Gas Turbine Blade Fault Identification

1990 ◽  
Author(s):  
K. Mathioudakis ◽  
A. Papathanasiou ◽  
E. Loukis ◽  
K. Papailiou
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Pressure Field ◽  
Fast Response ◽  
Gas Turbine Blade ◽  
Rotating Blades ◽  
Unsteady Pressure ◽  
Processing Techniques ◽  
Industrial Gas Turbine ◽  
Unsteady Pressure Measurements

The distortions of the pressure field around rotating blades of turbomachinery components due to alterations of their shape, can be utilized for the identification of faults related to the blading. Measurement of the unsteady pressure field in the wall proximity, provides information on such flow and pressure distortions and can thus be used for diagnostic purposes. An experimental investigation of the compressor rotating blades pressure field of an industrial gas turbine has been undertaken, in order to demonstrate the feasibility of the above mentioned principle. Various realistic gas turbine blade faults have been examined. The application of the appropriate processing techniques, demonstrates that unsteady pressure measurements can be used to identify the occurrence of minor blade faults (not traceable by standard techniques) as well as the kind of the fault. The proposed methodology has the potential for being incorporated in a computerized engine health monitoring system.

Design Modification of a Heavy Duty Industrial Gas Turbine Blade for Life Improvement

2012 ◽  
Author(s):  
Chris Hutchison ◽  
Anthony Chan ◽  
Dan Stankiewicz
Keyword(s):  
Crack Initiation ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Low Cycle Fatigue ◽  
Inlet Temperature ◽  
Gas Turbine Blade ◽  
Heavy Duty ◽  
Trailing Edge ◽  
Design Modification ◽  
Industrial Gas Turbine

Cracking at the trailing edge of a heavy duty industrial gas turbine blade has been observed on a number of serviced parts. The cracking usually occurs within 1.0″ of the platform. The trailing edge (TE) cracks have been found to propagate through the airfoil, leading to airfoil separation and severe engine damage. Liburdi Turbine Services has undertaken an independent metallurgical and stress analysis of the blade to determine the cause of the cracking. This paper covers the stress and low cycle fatigue (LCF) analysis of a platform undercut modification designed to mitigate crack initiation and thus increase part life. A finite element model of the blade was developed. Thermal loading was applied from a conjugate heat and mass transfer analysis between the blade, gas path flow and internal cooling flow. Base load conditions were used at turbine inlet temperature 2482°F. Results showed that the peak stress was present in the TE cooling slot corner, and was large enough to cause local yielding and LCF. The geometry of the modification was shown to strongly influence stress in the TE airfoil region and in the undercut region. Thus a balance was found to provide sufficiently low stresses in both regions and still be practical for machining. The modification was found to decrease stress in the TE cooling slot by a factor of 0.71 relative to that of the current OEM design, and increase life by 1.79 times. A viable modification has been demonstrated to extend blade life by reducing local stress and thus mitigating crack initiation at the airfoil TE.

Casing Vibration and Gas Turbine Operating Conditions

1989 ◽  
Author(s):  
K. Mathioudakis ◽  
E. Loukis ◽  
K. D. Papailiou
Keyword(s):  
Gas Turbine ◽  
Transfer Functions ◽  
Parametric Identification ◽  
Fast Response ◽  
Operating Conditions ◽  
Rotor Blades ◽  
Unsteady Pressure ◽  
Signal Features ◽  
Surface Vibrations ◽  
Industrial Gas Turbine

The results from an experimental investigation of the compressor casing vibration of an industrial Gas Turbine are presented. It is demonstrated that statistical properties of acceleration signals can be linked with engine operating conditions. The power content of such signals is dominated by contributions originating from the stages of the compressor, while the contribution of the shaft excitation is secondary. Using non-parametric identification methods, accelerometer outputs are correlated to unsteady pressure measurements taken by fast response transducers at the inner surface of the compressor casing. The transfer functions allow reconstruction of unsteady pressure signal features from the accelerometer readings. A possibility is thus provided, for “seeing” the unsteady pressure field of the rotor blades without actually penetrating through the casing, but by simply observing its external surface vibrations.

Conjugate Heat Transfer Simulation of an Industrial Gas Turbine Blade With Harmonic Balance Method

2021 ◽  
Author(s):  
Kim Zwiener ◽  
Cassie Carpenter ◽  
Justin Hodges
Keyword(s):  
Heat Transfer ◽  
Unsteady Flow ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Harmonic Balance ◽  
Harmonic Balance Method ◽  
Transient Simulation ◽  
Gas Turbine Blade ◽  
Heat Transfer Simulation ◽  
Industrial Gas Turbine

Abstract The performance of turbomachines is often dependent on the unsteady flow fields they naturally produce, owing primarily to row-to-row interactions from both moving and stationary components, as well as the unsteady nature of the turbulent flow. When it comes to computational fluid dynamics, a disparity exists between steady state and transient simulation as far as accuracy is concerned, albeit the computational cost of transient simulation on fully complex industrial hardware can be overwhelming. This study bridges the gap by presenting a harmonic balance conjugate heat transfer simulation approach in Simcenter STAR-CCM+, to model the unsteady flow phenomena while also providing accurate temperature predictions throughout the gas turbine blade solid bodies. The harmonic balance method used is a mixed time domain and frequency domain technique, which is suitable for periodic unsteady flows and is much less expensive than transient simulation. With this method, the impact of capturing these unsteady flow structures, such as the wake interactions and secondary cooling flows, is quantified on the resulting metal temperature distribution. Such is investigated and characterized throughout an industrial gas turbine blade with fully complex internal cooling passages, as well as film cooling for the external blade surface. Comparisons to steady simulation and transient simulation are also made to quantify the relative fidelity of each approach. Regarding the final resulting blade heat transfer, analysis is also provided to differentiate between important sources: the unsteadiness in the primary gas path flow and the classical unsteady nature of turbulence. Often these effects are lumped together when analyzing the resulting heat transfer, which is incorrect and can be better understood with more detailed analysis.

Internal Damage Accumulation and Imminent Failure of an Industrial Gas Turbine Blade: Interpretation and Implications

1996 ◽  
Author(s):  
M. I. Wood
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Internal Oxidation ◽  
Damage Accumulation ◽  
New Technologies ◽  
Gas Turbine Blade ◽  
Internal Damage ◽  
Service Experience ◽  
Industrial Gas Turbine

The row 1 blade from a heavy industrial gas turbine has been examined after ∼21,000 fired hours to assess the level and nature of the damage originating from the cooling holes. This consisted primarily of creep cracking/voiding coupled with deep internal oxidation/nitridation. The difficulties the manufacturer had in addressing the problem are discussed within the context of component assessment methodologies and the ‘new’ technologies which are being incorporatd into new unit types, but for which little service experience has yet been generated.

Casing Vibration and Gas Turbine Operating Conditions

1990 ◽  
Vol 112 (4) ◽  
pp. 478-485 ◽  
Author(s):  
K. Mathioudakis ◽  
E. Loukis ◽  
K. D. Papailiou
Keyword(s):  
Gas Turbine ◽  
Transfer Functions ◽  
Fast Response ◽  
Operating Conditions ◽  
Rotor Blades ◽  
Unsteady Pressure ◽  
Signal Features ◽  
Power Content ◽  
Surface Vibrations ◽  
Industrial Gas Turbine

The results from an experimental investigation of the compressor casing vibration of an industrial gas turbine are presented. It is demonstrated that statistical properties of acceleration signals can be linked with engine operating conditions. The power content of such signals is dominated by contributions originating from the stages of the compressor, while the contribution of the shaft excitation is secondary. Using nonparametric identification methods, accelerometer outputs are correlated to unsteady pressure measurements taken by fast response transducers at the inner surface of the compressor casing. The transfer functions allow reconstruction of unsteady pressure signal features from the accelerometer readings. A possibility is thus provided for “seeing” the unsteady pressure field of the rotor blades without actually penetrating through the casing, but by simply observing its external surface vibrations.

scholarly journals An alternative coating material for gas turbine blade for aerospace applications

2020 ◽  
Vol 1706 ◽  
pp. 012183
Author(s):  
Yajnesh M Poojari ◽  
Koustubh S Annigeri ◽  
Nilesh Bandekar ◽  
Kiran U Annigeri ◽  
Vinayak badiger ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Coating Material ◽  
Gas Turbine Blade ◽  
Aerospace Applications

Defect assessment in gas turbine blade coatings using non-contact thermography

2020 ◽  
Author(s):  
M. Mahesh Kumar ◽  
A.H.V. Pavan ◽  
R. Markandeya ◽  
Kulvir Singh
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Gas Turbine Blade ◽  
Defect Assessment
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