scholarly journals A Study of Advanced Materials for Gas Turbine Coatings at Elevated Temperatures Using Selected Microstructures and Characteristic Environments for Syngas Combustion

2011 ◽  
Author(s):  
Ravinder Diwan ◽  
Patrick Mensah ◽  
Guoqiang Li ◽  
Nalini Uppu ◽  
Strphen Akwaboa ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Elevated Temperatures ◽  
Advanced Materials ◽  
Syngas Combustion ◽  
Gas Turbine Coatings

scholarly journals Advanced Coatings for Gas Turbine Materials

1981 ◽  
Author(s):  
J. J. Stiglich ◽  
R. A. Hozl ◽  
D. G. Bhat
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Elevated Temperatures ◽  
Advanced Materials ◽  
Carbon Composites ◽  
Thermal Barrier ◽  
Barrier Materials ◽  
Additional Protection ◽  
San Fernando

San Fernando Laboratories (a division of Dart Industries) has been involved in the development of advanced materials and coating systems for structural use at elevated temperatures. This paper describes these activities including development of additional protection for thermal barrier materials and the development of an extremely high performance SiC coating. Problems of utilizing these and other coatings with carbon-carbon composites are also described.

Characterization and Nozzle Test Experience of a Self Sealing Ceramic Matrix Composite for Gas Turbine Applications

2002 ◽  
Author(s):  
Eric P. Bouillon ◽  
Greg C. Ojard ◽  
G. Habarou ◽  
Patrick C. Spriet ◽  
Jean L. Lecordix ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Elevated Temperatures ◽  
Fatigue Testing ◽  
Low Cycle Fatigue ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Advanced Materials ◽  
Constant Thickness ◽  
Engine Testing

Advanced materials have the potential to improve gas turbine engine durability. One general area of concern for durability is in the hot section components of the engine. Ceramic matrix composites offer improvements in durability at elevated temperatures with a corresponding reduction in weight for nozzles of gas turbine engines. Building on past material efforts, a next generation SiC/SiC composite with a self-sealing matrix has been developed for gas turbine applications. An extensive baseline test characterization has been done that shows the overall material suitability. Prior to ground engine testing, a reduced test matrix was undertaken to aggressively test the material in a long-term hold cycle at elevated temperatures and environments. This tensile low cycle fatigue testing was done in air and a 90% steam environment. While the steam environment aggressively attacked the material, no appreciable debit in material life was noted. Nondestructive testing and post test characterization of this testing were performed. After completion of the aggressive testing effort, two nozzle seals of constant thickness were fabricated and installed in an F100-PW-229 engine for accelerated mission testing. The self sealing CMC seals were tested for over 250 hours in accelerated conditions without damage. The results of the engine testing will be shown and overall conclusions drawn.

Experimental Investigation of Ti-6Al-4V with a Biaxial Tensile Test Setup at Elevated Temperature

2014 ◽  
Vol 622-623 ◽  
pp. 273-278 ◽  
Author(s):  
Marion Merklein ◽  
Sebastian Suttner ◽  
Adam Schaub
Keyword(s):  
Elevated Temperature ◽  
Elevated Temperatures ◽  
Tensile Tests ◽  
Advanced Materials ◽  
Uniaxial Tensile ◽  
Plastic Yielding ◽  
Characterization Methods ◽  
Specific Strength ◽  
Biaxial Tensile ◽  
Stress States

The requirement for products to reduce weight while maintaining strength is a major challenge to the development of new advanced materials. Especially in the field of human medicine or aviation and aeronautics new materials are needed to satisfy increasing demands. Therefore the titanium alloy Ti-6Al-4V with its high specific strength and an outstanding corrosion resistance is used for high and reliable performance in sheet metal forming processes as well as in medical applications. Due to a meaningful and accurate numerical process design and to improve the prediction accuracy of the numerical model, advanced material characterization methods are required. To expand the formability and to skillfully use the advantage of Ti-6Al-4V, forming processes are performed at elevated temperatures. Thus the investigation of plastic yielding at different stress states and at an elevated temperature of 400°C is presented in this paper. For this reason biaxial tensile tests with a cruciform shaped specimen are realized at 400°C in addition to uniaxial tensile tests. Moreover the beginning of plastic yielding is analyzed in the first quadrant of the stress space with regard to complex material modeling.

Assessment of the Potential of Combined Micro Gas Turbine and High Temperature Fuel Cell Systems

2002 ◽  
Author(s):  
Dieter Bohn ◽  
Nathalie Po¨ppe ◽  
Joachim Lepers
Keyword(s):  
Fuel Cells ◽  
High Temperature ◽  
Fuel Cell ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Power Plants ◽  
Advanced Materials ◽  
Cell Systems ◽  
Micro Gas Turbine ◽  
Technological Assessment

The present paper reports a detailed technological assessment of two concepts of integrated micro gas turbine and high temperature (SOFC) fuel cell systems. The first concept is the coupling of micro gas turbines and fuel cells with heat exchangers, maximising availability of each component by the option for easy stand-alone operation. The second concept considers a direct coupling of both components and a pressurised operation of the fuel cell, yielding additional efficiency augmentation. Based on state-of-the-art technology of micro gas turbines and solid oxide fuel cells, the paper analyses effects of advanced cycle parameters based on future material improvements on the performance of 300–400 kW combined micro gas turbine and fuel cell power plants. Results show a major potential for future increase of net efficiencies of such power plants utilising advanced materials yet to be developed. For small sized plants under consideration, potential net efficiencies around 70% were determined. This implies possible power-to-heat-ratios around 9.1 being a basis for efficient utilisation of this technology in decentralised CHP applications.

An Assessment on the Benefits of Additive Manufacturing Regarding New Swirler Geometries for Gas Turbine Burners

2018 ◽  
Author(s):  
Fabrice Giuliani ◽  
Nina Paulitsch ◽  
Daniele Cozzi ◽  
Michael Görtler ◽  
Lukas Andracher
Keyword(s):  
Additive Manufacturing ◽  
Gas Turbine ◽  
Inconel 718 ◽  
Advanced Materials ◽  
Gas Turbine Combustor ◽  
Engineering Research ◽  
Know How ◽  
Current State ◽  
Research And Education ◽  
Near Future

In the near future, combustion engineers will shape the burner according to the flame, and not the opposite way anymore. In this contribution, this idea is explored with the help of additive manufacturing (AM). The focus is put on the design and the production of swirlers using advanced materials with the least possible efforts in terms of manufacturing. The material chosen for this study is Inconel 718. There are three motivations to this project. The first one is to design new shapes and assess these in comparison to conventional ones. The second motivation is to be able to manufacture them using additive manufacturing, and to gather know-how on selective laser melting. The third motivation is to elaborate a methodology involving engineering, research and education to promote — only if and when this is desirable — the production of series of premium parts such as high-end components of gas turbine combustor using AM. First-of-a-kind swirler shapes are explained and designed. These are unlikely to be produced using conventional manufacturing. They are then successfully produced in Inconel 718 using AM. The raw parts are directly submitted for testing with no surface post-processing. The paper states why at current state-of-the-art the raw surface quality still needs improvement, and highlights the benefits of the new swirler shape versus conventional.

Structure, Composition and Stability of Heterophase Boundaries

1997 ◽  
Vol 3 (S2) ◽  
pp. 673-674
Author(s):  
M. Rühle ◽  
T. Wagner ◽  
S. Bernath ◽  
J. Plitzko ◽  
C. Scheu ◽  
...  
Keyword(s):  
Electron Microscopy ◽  
Elevated Temperatures ◽  
Analytical Electron Microscopy ◽  
High Resolution Electron Microscopy ◽  
Advanced Materials ◽  
Bulk Crystals ◽  
Transmission Electron ◽  
Resolution Electron ◽  
The Stability

Heterophase boundaries play an important role in advanced materials since those materials often comprise different components. The properties of the materials depend strongly on the properties of the interface between the components. Thus, it is important to investigate the stability of the microstructure with respect to annealing at elevated temperatures. In this paper results will be presented on the structure and composition of the interfaces between Cu and (α -Al2O3. The interfaces were processed either by growing a thin Cu overlayer on α- Al2O3 in a molecular beam epitaxy (MBE) system or by diffusion bonding bulk crystals of the two constituents in an UHV chamber. To improve the adhesion of Cu to α -Al2O3 ultrathin Ti interlayers were deposited between Cu and α - Al2O3.Interfaces were characterized by different transmission electron microscopy (TEM) techniques. Quantitative high-resolution electron microscopy (QHRTEM) allows the determination of the structure (coordinates of atoms) while analytical electron microscopy (AEM) allows the determination of the composition with high spatial resolution.

Engine Test Experience and Characterization of Self Sealing Ceramic Matrix Composites for Nozzle Applications in Gas Turbine Engines

2003 ◽  
Author(s):  
Eric P. Bouillon ◽  
Patrick C. Spriet ◽  
Georges Habarou ◽  
Thibault Arnold ◽  
Greg C. Ojard ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Elevated Temperatures ◽  
Low Cycle Fatigue ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Turbine Engines ◽  
Matrix Composites ◽  
Gas Turbine Engines ◽  
Sic Fiber ◽  
Engine Testing

Advanced materials are targeting durability improvement in gas turbine engines. One general area of concern for durability is in the hot section components of the engine. Ceramic matrix composites offer improvements in durability at elevated temperatures with a corresponding reduction in weight for nozzles of gas turbine engines. Building on past material efforts, ceramic matrix composites using a carbon and a SiC fiber with a self-sealing matrix have been developed for gas turbine applications. Prior to ground engine testing, a reduced test matrix was undertaken to aggressively test the material in a long-term hold cycle at elevated temperatures and environments. This tensile low cycle fatigue testing was done in air and a 90% steam environment. After completion of the aggressive testing effort, six nozzle seals were fabricated and installed in an F100-PW-229 engine for accelerated mission testing. The C fiber CMC and the SiC Fiber CMC were respectively tested to 600 and 1000 hours in accelerated conditions without damage. Engine testing is continuing to gain additional time and insight with the objective of pursuing the next phase of field service evaluation. Mechanical testing and post-test characterization results of this testing will be presented. The results of the engine testing will be shown and overall conclusions drawn.

Paper 7: Advanced Nickel-Chromium Base Alloys

1965 ◽  
Vol 180 (4) ◽  
pp. 160-171
Author(s):  
C. H. White ◽  
J. Heslop
Keyword(s):  
High Temperature ◽  
Binary System ◽  
Gas Turbine ◽  
Elevated Temperatures ◽  
High Strength ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Nickel Chromium ◽  
Chromium Alloys ◽  
Resistance To Oxidation

Nickel-chromium alloys have been in use since early in this century for high temperature applications because of their resistance to oxidation. Since the advent of the gas-turbine engine, more complex alloys capable of maintaining high strength at elevated temperatures have been developed from the simple binary system. These complex alloys were initially mainly strengthened by the precipitation of the Ni3(Ti, Al) phase but more recent alloys have been further strengthened by additions of cobalt, tungsten, molybdenum, niobium, and tantalum. The properties and applications of these alloys are discussed.

Advanced Materials for Mercury™ 50 Gas Turbine Combustion System

2006 ◽  
Author(s):  
Jeffrey Price ◽  
Josh Kimmel ◽  
Xiaoqun Chen ◽  
Arun Bhattacharya ◽  
Anthony Fahme ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Ceramic Matrix Composite ◽  
Field Evaluation ◽  
Ceramic Composites ◽  
Advanced Materials ◽  
Combustion System ◽  
Fuel Injector ◽  
Ods Alloys ◽  
Gas Turbine Combustion

Solar Turbines Incorporated (Solar), under cooperative agreement number DE-FC26-00CH 11049, is improving the durability of gas turbine combustion systems while reducing life cycle costs. This project is part of the Advanced Materials in Advanced Industrial Gas Turbines program in DOE’s Office of Distributed Energy. The targeted engine is the Mercury™ 50 gas turbine, which was developed by Solar under the DOE Advanced Turbine Systems (ATS) program (DOE contract number DE-FC21-95MC31173). The ultimate goal of the program is to demonstrate a fully integrated Mercury 50 combustion system, modified with advanced materials technologies, at a host site for 4,000 hours. The program has focused on a dual path development route to define an optimum mix of technologies for the Mercury 50 turbine and future Solar products. For liner and injector development, multiple concepts including high thermal resistance thermal barrier coatings (TBC), oxide dispersion strengthened (ODS) alloys, continuous fiber ceramic composites (CFCC), and monolithic ceramics were evaluated. An advanced TBC system for the combustor was down-selected for field evaluation. ODS alloys were down-selected for the fuel injector tip application. Preliminary component and sub-scale testing was conducted to determine material properties and demonstrate proof-of-concept. Full-scale rig and engine testing were used to validate engine performance prior to field evaluation. Field evaluation of ceramic matrix composite liners in the Centaur® 50 gas turbine engine [1–3] which was previously conducted under the DOE sponsored Ceramic Stationary Gas Turbine program (DE-AC02-92CE40960), is continuing under this program. This paper is a status review of the program, detailing the current progress of the development and field evaluations.

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