Thermal barrier systems have been the subject of vigorous research and development activities over the past few years, driven by the demands for enhanced reliability and substantially higher operating temperatures envisaged for the next generations of gas turbine engines. The menu of candidate materials and architectures has expanded considerably, including numerous concepts based on zirconia as well as radically different materials, multilayers and modulated distributions of porosity and chemical composition. Advances in deposition processes enable increased flexibility for tailoring composition and microstructure to local requirements within the coating system, e.g. for thermal insulation, control of interdiffusion, enhanced resistance against environmental degradation and condition monitoring. Many challenges remain but healthy and growing collaborations between the science and technology communities bode well for future progress in this area.

Emerging materials and processes for thermal barrier systems

http://pure.tudelft.nl/ws/files/11926671/1_s2.0_S0378775316308631_main.pdf

A review of fuel cell systems for maritime applications

https://research.birmingham.ac.uk/portal/files/53643809/APEN2017.pdf

Performance-based health monitoring, diagnostics and prognostics for condition-based maintenance of gas turbines: A review

An assessment of mine methane mitigation and utilisation technologies

Hybrid PSO–SVM-based method for forecasting of the remaining useful life for aircraft engines and evaluation of its reliability

This text was written primarily for gas turbine designers and emphasizes engine performance, presenting easy-to-read guidelines for engineers on how to achieve optimum fuel efficiency, stability, and emissions control in gas turbine systems. It discusses the effects of liquid, vapor and ice on gas turbines, and examines fuel and oil properties and their impact on performance. Contents include: gas turbine engine applications; the operational envelope; properties and charts for dry air, combustion products and other working fluids; dimensionless, quasidimensionless, referred and scaling parameter groups; gas turbine engine components; design point performance and engine concept design; off design performance; transient performance; starting; windmilling; engine performance testing; the effects of water-liquid, steam and ice; fuel and oil properties and their impact; appendices; and index.

Gas Turbine Performance

In order to regulate fuel flow to the combustor (36) of the combustion turbine engine (10) having a primary combustion zone (64) and at least one further combustion zone, the temperature of the inlet and outlet of the combustor (36) are determined, as are first and second values representing first and second properties, with the first property being one of: the total enthalpy rise in the combustor (36), the equivalence ratio of the combustor (36), the fuel/air ratio of said combustor (36), the fuel flow through the combustor, and the second property being one of: the enthalpy rise in the primary zone (64), the equivalence ratio of said primary zone (64), the fuel/air ratio of the primary zone(64); the temperature rise across the primary zone(64), or the fuel flow through the primary zone (64). The second property is determined from the first value and the current value of the ratio of the fuel to the primary zone (64) to the total fuel to the combustor (36). The temperature of the outlet of the primary zone (64) is thus determined from the inlet temperature and the second value, are compared with a predetermined temperature to generate a control signal dependent on the difference. The fuel to the primary zone (64) is then varied, to vary the control signal to reduce the difference. This use of ratios eliminates the need for a gas chromatograph, flow ratios and humidity sensors to determine the properties of the gas.

Method and system for controlling fuel supply in a combustion turbine engine

A significant addition to the literature on gas turbine technology, the second edition of Gas Turbine Performance is a lengthy text covering product advances and technological developments Including extensive figures, charts, tables and formulae, this book will interest everyone concerned with gas turbine technology, whether they are designers, marketing staff or users

Gas Turbine Performance: 2nd edition

A gas turbine engine comprises a centrifugal compressor ( 4 ), an air diffuser ( 8 ), a heat exchanger ( 10 ), combustion apparatus ( 12 ), and first and second turbines ( 14,18 ). The combustion chamber assembly ( 22 ) comprises a primary, a secondary and a tertiary fuel and air mixing ducts ( 54,78,98 ). The compressor ( 4 ), diffuser ( 8 ), primary and secondary fuel and air mixing ducts ( 54,78 ) and turbines ( 14,18 ) all comprise means ( 6,8,16,20 ) for varying the mass flow area at their inlets such that in operation the amount of air mass through each component may be independently variable. Under part power conditions the mass flow is reduced and under full power conditions the mass flow is increased thereby maintaining a substantially constant gas cycle throughout the engine.

Gas turbine engine and a method of controlling a gas turbine engine

A variable geometry combustor having a combustor liner that defines at least one dilution port in order to provide air to a dilution zone within the combustor. At least one valve is positioned adjacent the dilution port for controlling the flow of air through the dilution port wherein the valve is settable to maintain one of a plurality of different open configurations.

Philip Patrick Walsh

Papers

Gas Turbine Performance

Method and system for controlling fuel supply in a combustion turbine engine

Gas Turbine Performance: 2nd edition

Gas turbine engine and a method of controlling a gas turbine engine

Variable geometry combustor