Heißgaskorrosion an Gasturbinenschaufeln unter echten und simulierten Flugbetriebsbedingungen / Corrosion of Gas Turbine Blades by hot Gases under normal and simulated Operating Conditions

1976 ◽  
Vol 13 (9) ◽  
pp. 426-434
Author(s):  
Karlheinz G. Schmitt-Thomas ◽  
Heinrich Meisel ◽  
Hans-Joachim Dorn
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Operating Conditions ◽  
Gas Turbine Blades

Rejuvenation Heat Treatment of Single Crystal Gas Turbine Blades

2017 ◽  
Author(s):  
J. Kuipers ◽  
K. Wiens ◽  
B. Ruggiero
Keyword(s):  
Heat Treatment ◽  
Single Crystal ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Damage Mechanism ◽  
Operating Conditions ◽  
Gas Turbine Blades ◽  
Full Solution ◽  
Fatigue Endurance ◽  
Root Surfaces

Thermal degradation of precipitation-hardened nickel based superalloys has been demonstrated to be reversible through full solution rejuvenation heat treatment processing. The specific concern with full solution rejuvenation heat treatment of single crystal alloys is the formation of recrystallized grains on surfaces with residual stress. The threshold temperature for recrystallization and the effect of heat treatment temperature and time on recrystallization depth were evaluated on service run industrial gas turbine blades comprised of nickel based single crystal alloys René N5 and RR2000. Recrystallization of rejuvenated blades was observed on the root surfaces of blades which had been shot peened at original manufacture and/or during a prior repair. Blades which did not receive peening at manufacture were free of recrystallization in critical areas following full solution rejuvenation heat treatment. Given that gas turbine blade roots operate at relatively low temperatures compared to the airfoil, creep is not considered a life limiting damage mechanism for this region of the blade. Rather, high cycle fatigue is considered the primary damage mechanism of concern. As such, fatigue testing of shot peened and heat treated (recrystallized) René N5 specimens was carried out at 650°C at various stress levels in comparison with baseline (non-recrystallized) specimens to determine the extent to which recrystallization would limit fatigue endurance at blade root operating conditions. It was found that recrystallization did not reduce the fatigue endurance relative to baseline samples at the tested conditions. The findings indicate that repair including full solution rejuvenation heat treatment of previously peened blades comprised of René N5 alloy is feasible provided that recrystallization be limited to root surfaces.

scholarly journals Turbulent Flow and Heat Transfer in Gas Turbine Blade Cooling Passages

1992 ◽  
Author(s):  
F. J. Cunha
Keyword(s):  
Heat Transfer ◽  
Turbulent Flow ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Operating Conditions ◽  
Temperature Fields ◽  
Air Cooling ◽  
Turbine Blade Cooling ◽  
Gas Turbine Blades ◽  
Analysis Methodology

A numerical analysis methodology has been created to predict the heat transfer within the air cooling passages of gas turbine blades. In this paper, the turbulent flow heat convection with developed velocity and temperature fields is studied for cavities with turbulators. The influence of Coriolis forces and rotational buoyancy effects were also included. The k-equation turbulence model was employed over most of the cross section while a modified Van Driest’s version of the mixing length hypothesis is used in the near-wall sublayer. This methodology was successfully benchmarked against experimental results for air cooling passages of turbine blades. Analytical results are presented in terms of the Reynolds, Rossby and rotational Rayleigh numbers for realistic operating conditions.

scholarly journals IEA Grimethorpe 2 × 2M PFBC Facility: Turbine Materials Testing in a Cascade Loop

1984 ◽  
Author(s):  
A. J. Minchener ◽  
P. J. Mainhardt ◽  
R. A. Mountford ◽  
G. Erbe ◽  
J. S. Anderson ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
International Energy Agency ◽  
Operating Conditions ◽  
Materials Testing ◽  
Fluidised Bed ◽  
Energy Agency ◽  
Gas Turbine Blades ◽  
Programme Design ◽  
Median Particle

The Grimethorpe pressurised fluidised bed combustor (PFBC) facility of the International Energy Agency is equipped with an off-gas loop in which gas turbine blades are being exposed to assess the potential for erosion, corrosion, or deposition in a PFBC gas turbine. The flue gas from the PFBC is passed through four stages of cyclones before entering the cascade test section. Depending on operating conditions, the loop passes between 5.0 and 6.4 kg/sec of gas, which allows aerofoils of about the same size as the General Electric MS 1002 turbine blading to be tested. The cascade contains four stages of nine blades each, as well as three erosion targets. The first three stages are impulse blades and experience a gas velocity in the range 200 to 230 m/sec, while the fourth stage of reaction aerofoils accelerates the gas to between 300 and 400 m/sec before it passes over the erosion targets. Both uncooled (700–850°C) and cooled (500–650°C) blades are used. Results from initial running of the cascade loop have indicated a dust loading to the cascade of the order of 100 ppm, with median particle sizes in the range of 1 to 2 microns, and an average alkali level (K plus Na) of 1.1 ppm. The blades exhibited the aerodynamically-expected pattern of behaviour, and the results are generally considered encouraging. The continuing overall test programme design is discussed.

Machine Learning Based Classification Model for Predicting Cyclic Failure in Radially Cooled Gas Turbine Blades

2021 ◽  
Author(s):  
Rishabh Shrivastava ◽  
Ankush Kapoor ◽  
Stuti Kaushal ◽  
Amit Yadav ◽  
Pavankumar Vodnala
Keyword(s):  
Machine Learning ◽  
Random Forest ◽  
Gas Turbine ◽  
Flow Rate ◽  
Turbine Blades ◽  
Operating Conditions ◽  
Classification Model ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Gas Turbine Blades

Abstract Gas turbine blades and vanes face very severe operating conditions - high temperature and pressure which necessitates the creation of complex cooling and component designs, resulting in high computational cost. The ability to predict cyclic failure in these components is therefore a critical activity that has been historically performed using 3D commercial finite element (FE) codes for baseload conditions. However, these codes take substantial time and resources which restricts their application in failure prediction at variable operating conditions. Newer data-driven techniques such as machine learning (ML) provide a valuable tool that can be utilized to predict the occurrence of cyclic failure for these conditions with minimal time and resource requirement. In this paper, a machine learning based surrogate model is developed to predict the cyclic failure of a radially cooled turbine blade. The features used as input to machine learning model are turbine inlet temperature, coolant inlet temperature, hot gas mass flow rate, cooling air mass flow rate and blade materials. The output for the model is a binary variable depicting the incident of component failure. 70% of the FE data points are used to train the ML model while the remaining are used for testing. A comparative study between Logistic Regression, Random Forest, K-nearest neighbor, and Support Vector Machine (SVM) was performed to select the most accurate algorithm for the classification model. Finally, the results show that the Random Forest and SVM algorithms predicts failure with the highest f-1 score of 0.92. The model also demonstrates that Turbine Inlet temperature has the highest importance amongst the input features followed by blade material. Additionally, this methodology offers a tremendous advantage for failure prediction by reducing analysis time from multiple hours to a few seconds, rendering this technique especially beneficial for time sensitive business decisions in the gas turbine industry.

Thermo Mechanical Fatigue Testing of GTD 111 Superalloy for Use in Gas Turbine Blades

2015 ◽  
Vol 830-831 ◽  
pp. 211-214 ◽  
Author(s):  
Brijesh Patel ◽  
Kalpit P. Kaurase ◽  
Anil M. Bisen
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Fatigue Testing ◽  
Material Selection ◽  
Turbine Blades ◽  
Operating Conditions ◽  
Limiting Factors ◽  
Test Results ◽  
Gas Turbine Blades ◽  
Mechanical Fatigue

Design of Turbo machinery is complex and efficiency is directly related to material performance, material selection is of prime importance. Temperature limitations are the most crucial limiting factors to gas turbine efficiencies. This paper presents the life of GTD 111 applied to gas turbine blade based on LCF and TMF test results. The LCF tests were conducted under various strain ranges based on gas turbine operating conditions. In addition, IP (in-phase) and OP (out of-phase) TMF tests were conducted under various strain ranges. The paper will focus light on above issues and each plays an important role within the Gas Turbine Material literature and ultimately influences on planning and development practices. It is expected that this comprehensive contribution will be very beneficial to everyone involved or interested in Gas Turbines.

Prediction of Remaining Useful Life for Used Gas Turbine Blades

2013 ◽  
Vol 774-776 ◽  
pp. 370-374
Author(s):  
Aklilu Tesfamichael Baheta ◽  
Brilianto Brioann Boni Johanis ◽  
Mohd Shahrizal Jasmani
Keyword(s):  
Service Life ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Remaining Useful Life ◽  
Operating Conditions ◽  
Creep Life ◽  
Gas Turbine Blades ◽  
Useful Life ◽  
Life Fraction ◽  
Scanning Electron

Used turbine blades are replaced by new once based on manufacturers recommended useful life. However, depending on the turbine operating conditions the blades might have different creep service life. Thus, the aim of this study was to predict the remaining creep life and investigating the microstructure of used gas turbine blades. This was done by using Larson-Miller parameter and Robinson life fraction rules under certain conditions of stress and temperature. The change in microstructure of the materials was analyzed by using the Field Emission Scanning Electron Microscope (FESEM). The result shows that turbine blades suffered from several microstructure changes based on their service life. The method used to predict the remaining useful life of used turbines could be an input to a decision to repair or replace used turbine blades. Keywords: Larson-Miller parameter,life fraction rule, microstructure, creep life, turbine blades.

Determination of Heat Transfer Coefficients Around a Blade Surface From Temperature Measurements

1979 ◽  
Author(s):  
D. K. Mukherjee
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Operating Conditions ◽  
Main Stream ◽  
Blade Surface ◽  
Transfer Coefficients ◽  
Gas Turbine Blades ◽  
Heat Transfer Coefficients

To design cooled gas turbine blades, heat transfer coefficients around its surface are required. The calculated heat transfer data under operating conditions in the turbine are often inaccurate and require experimental verification. A method is presented here to determine the heat transfer coefficients around the blade surface and in the coolant channels. This requires measurements of the main stream and coolant temperatures together with the outer surface temperature distribution at varying mass flows. In order to conduct these tests in a gas turbine, test blades have to be specially prepared allowing the variation and measurement of coolant mass flow.

UDIMET L-605

Alloy Digest ◽  
2004 ◽  
Vol 53 (12) ◽  
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Physical Properties ◽  
Tensile Properties ◽  
Gas Turbine ◽  
Oxidation Resistance ◽  
Turbine Blades ◽  
Heat Treating ◽  
Gas Turbine Blades ◽  
Temperature Performance

Abstract Udimet L-605 is a high-temperature aerospace alloy with excellent strength and oxidation resistance. It is used in applications such as gas turbine blades and combustion area parts. This datasheet provides information on composition, physical properties, and tensile properties as well as creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, and joining. Filing Code: CO-109. Producer or source: Special Metals Corporation.

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