Cast Iron-Nickel Alloy for Industrial Gas Turbine Engine Applications

2005 ◽  
Author(s):  
Jeffrey R. Neyhouse ◽  
Jose M. Aurrecoechea ◽  
J. Preston Montague ◽  
John D. Lilley
Keyword(s):  
Gas Turbine ◽  
Ductile Iron ◽  
Gas Turbine Engine ◽  
Austenitic Steels ◽  
Nickel Steel ◽  
Turbine Engine ◽  
Gas Turbine Exhaust ◽  
Nodular Graphite ◽  
Industrial Gas Turbine ◽  
Turbine Exhaust

Austenitic ductile iron castings have traditionally been used for gas turbine exhaust components that require castability, good machinability, low thermal expansion, and high strength at elevated temperatures. The achievement of optimum properties in austenitic ductile irons hinges on the ability of the foundry to produce nodular graphite in the microstructure throughout the component. In large, complex components, consistently producing nodular graphite is challenging. A high-nickel steel alloy that is suitable for sand castings has been recently developed for industrial gas turbine engine applications. The alloy exhibits similar mechanical and physical properties to austenitic ductile irons, but with improved processability and ductility. This alloy is weldable and exhibits no secondary graphite phase. This paper presents the results of a characterization program conducted on a 35% nickel, high-alloy steel. The results are compared with an austenitic ductile iron of similar composition. Tensile and creep properties from ambient temperature to 760°C (1400°F) are included, along with fabrication experience gained during the manufacture of several sand cast components at Solar Turbines Incorporated. The alloy has been successfully adopted for gas turbine exhaust system components and other applications where austenitic ductile irons have traditionally been utilized. The low carbon content of austenitic steels permits improved weldabilty and processing characteristics over austenitic ductile irons. The enhancements provided by the alloy indicate that additional applications, as both austenitic ductile iron replacements and new components, will arise in the future.

scholarly journals Industrial Gas Turbine Engine Catalytic Pilot Combustor-Prototype Testing

2010 ◽  
Author(s):  
Shahrokh Etemad ◽  
Benjamin Baird ◽  
Sandeep Alavandi ◽  
William Pfefferle
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Industrial Gas Turbine ◽  
Prototype Testing

CFD Analysis of Industrial Gas Turbine Exhaust Diffusers

2002 ◽  
Author(s):  
V. Vassiliev ◽  
S. Irmisch ◽  
S. Florjancic
Keyword(s):  
Gas Turbine ◽  
Measurement Data ◽  
Turbulence Models ◽  
Cfd Analysis ◽  
Cfd Modelling ◽  
Gas Turbine Exhaust ◽  
Key Aspects ◽  
Industrial Gas Turbine ◽  
Turbine Exhaust

The key aspects for the reliable CFD modelling of exhaust diffusers are addressed in this paper. In order to identify adequate turbulence models a number of 2D diffuser configurations have been simulated using different turbulence models and results have been compared with measurements. An automated procedure for a time- and resource-efficient and accurate prediction of complex diffuser configuration is presented. The adequate definitions of boundary conditions for the diffuser simulation using this procedure are discussed. In the second part of this paper, the CFD procedure is being applied to investigate the role of secondary flow on axial diffusers. Prediction results are discussed and compared with available measurement data.

An Experimental Analysis of Flow Through Annular Diffuser With and Without Struts

2006 ◽  
Author(s):  
R. Prakash ◽  
P. Sudhakar ◽  
N. V. Mahalakshmi
Keyword(s):  
Gas Turbine ◽  
Static Pressure ◽  
Structural Members ◽  
Pressure Development ◽  
Annular Diffuser ◽  
Fundamental Research ◽  
Flow Through ◽  
Gas Turbine Exhaust ◽  
Industrial Gas Turbine ◽  
Turbine Exhaust

This paper presents the static pressure development and the effect of struts on the performance of an annular diffuser. A typical exhaust diffuser of an industrial gas turbine is annular with structural members, called struts, which extend radially from the inner to the outer annulus wall. An annular diffuser model, primarily intended for fundamental research, has been tested on a wind tunnel. Similar conditions that prevail in an industrial gas turbine have been generated in the diffuser. Measurements were made using a five holed Pitot probe. The research had been carried out to make a detailed investigation on the effect of struts and to advance computational and design tools for gas turbine exhaust diffusers.

Differential Mobility Spectrometer Particle Emission Analysis for Multiple Aviation Gas Turbine Engine Exhausts at High and Low Power Conditions and a Simulated Gas Turbine Engine Exhaust

2014 ◽  
Author(s):  
David M. Walters ◽  
Yura A. Sevcenco ◽  
Andrew P. Crayford ◽  
Richard Marsh ◽  
Philip J. Bowen ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Fast Response ◽  
Gas Turbine Engine ◽  
Civil Aviation ◽  
Differential Mobility ◽  
Emission Analysis ◽  
Turbine Engine ◽  
Differential Mobility Spectrometer ◽  
Gas Turbine Exhaust ◽  
Mass Concentrations

This paper presents particulate matter (PM) size spectral measurements, analysed to determine number and mass concentration, taken using a fast response differential mobility spectrometer (DMS500). Exhaust samples from multiple commercially available large civil aviation gas turbine engines and an auxiliary power unit operating at high and low engine power conditions were studied, in addition to a simulated aviation gas turbine exhaust, which was operated to exhibit specific PM output. Results show all exhaust sources as having similar bi-modal PM size spectra with both number and mass concentrations highly dependent on the emission source and the sampling testing condition. When operating at high power levels all of the tested gas turbine emission sources, with the exception of the 2-stage combustor design, generally produced distributions of PM which exhibited larger average mean diameter particle sizes and higher number and mass concentrations.

Laser Raman and Fluorescence Measurements Applied to Gas Turbine Exhaust Emissions

1975 ◽  
Author(s):  
D. A. Leonard ◽  
P. M. Rubins
Keyword(s):  
Gas Turbine ◽  
Optical Method ◽  
Exhaust Emissions ◽  
Exhaust Emission ◽  
Emission Analysis ◽  
Turbine Engine ◽  
Laser Raman ◽  
Fluorescence Measurements ◽  
Gas Turbine Exhaust ◽  
Turbine Exhaust

The problems of gas turbine exhaust gas sampling by presently approved methods make an optical method attractive. Because of this, the Air Force has sponsored the development of laser. Raman for exhaust emissions measurement. Laser induced Raman and fluorescent measurements were made in the exhaust of a T53-L-13A gas turbine engine with a new field-portable instrument devised specifically for gas turbine exhaust emission measurements. The gas turbine exhaust was analyzed by conventional instruments for CO, CO2, NO, NOx total hydrocarbons, smoke, and temperature, and these data were used as a comparative standard for the evaluation of the laser Raman instrument. Results thus far indicate good to excellent correlations for CO2, O2, smoke, hydrocarbons, and temperature. NO detection was not sensitive enough, but the data analysis indicates that 100 ppm or less may be detectable with instrument improvements. Further NO sensitivity is possible with continued development of the method. CO analysis was not attempted, but it is expected that CO could be detected with further research. NO2 was not attempted because theoretical and experimental laboratory analysis indicated severe interferences with CO2. Temperature profiles from laser Raman were also compared with thermocouple data in the exhaust stream, and showed agreement within the radiation error of the thermocouples. With further development, laser Raman shows a good potential for an optical method of aircraft gas turbine emission analysis.

Three-Dimensional Structural Evaluation of a Gas Turbine Engine Rotor

2014 ◽  
Author(s):  
Partha S. Das
Keyword(s):  
Finite Element ◽  
Steady State ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Complex Geometries ◽  
Turbine Engine ◽  
Industrial Gas Turbine ◽  
Engine Rotor ◽  
Engine Rotors ◽  
Critical Locations

Engine rotors are one of the most critical components of a heavy duty industrial gas turbine engine, as it transfers mechanical energy from rotor blades to a generator for the production of electrical energy. In general, these are larger bolted rotors with complex geometries, which make analytical modeling of the rotor to determine its static, transient or dynamic behaviors difficult. For this purpose, powerful numerical analysis approaches, such as, the finite element method, in conjunction with high performance computers are being used to analyze the current rotor systems. The complexity in modeling bolted rotor behavior under various loadings, such as, airfoil, centrifugal and gravity loadings, including engine induced vibration is one of the main challenges of simulating the structural performance of an engine rotor. In addition, the internal structural temperature gradients that can be encountered in the transient state as a result of start-up and shutdown procedures are generally higher than those that occur in the steady-state and hence thermal shock is important factor to be considered relative to ordinary thermal stress. To address these issues, the current paper presents the steady-state & quasi-static analyses (to approximate transient responses) of two full 3-D industrial gas turbine engine rotors, SW501F & GE-7FA rotor, comprising of both compressor & turbine sections together. Full 3-D rotor analysis was carried out, since the 2-D axisymmetric model is inadequate to capture the complex geometries & out of plane behavior of the rotor. Both non-linear steady-state & transient analyses of a full gas turbine engine rotor was performed using the general purpose finite element analysis program ABAQUS. The paper presents in detail the FEA modeling technique, overall behavior of the full rotor under various loadings, as well as, the critical locations in the rotor with respect to its strength and life. The identification of these critical locations is needed to help with the repair of the existing rotors and to improve and extend the operational/service life of these rotors.

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