Gas turbine

Gas turbines compete with Steam (Nuclear and Fossil Fuel) power plants to generate power around the globe. Historically gas turbines have suffered from low levels of efficiency and poor reliability, resulting in a reliance on the above mentioned alternatives to supply the consumer demand for electricity. Initial assumptions and original efficiency values will be based on the ideal Brayton Cycle, by replacing an open cycle Fig.1 with a closed cycle Fig. 2 (Huang & Gramoll, n.d.) This report will

The modern gas turbine was born from two early fields of technology: the steam turbine and the internal combustion engine. [1] In 1678, Ferdinand Verbiest designed a horseless carriage that relied on an early steam jet for power and propulsion, this is thought to be the first self-propelled automobile in history. Eventually, inventors attempted to create an alternative to the steam engine and the idea of the gas turbine was born. While the claim to inventing the gas turbine has never truly been

Gas turbines are often exposed to ingestion of particles suspended in the air such as dust, ash, salt, ice, water droplets, and sand particles during operation. These particles are the most important factor that cause blade fault in all types of gas turbines. The most common types of blade fault are fouling, erosion, tip clearance increase, water ingestion, and foreign object damage (FOD) [1]. Most of mentioned cases cause roughness over the blade surfaces that deteriorate the gas turbine performance

A gas turbine by definition is an engine in the centre of a power plant producing electric current [1]. It is also a rotary engine extracting energy from flow of combustion gas. Gas turbine is responsible for the conversion of natural gas or any other liquid fuels into mechanical energy. This energy can therefore be used to drive the generator to produce electrical energy [1-3]. Gas turbine is made up of components as shown in Figure 1 below. Figure 1: Gas turbine showing arrangements

Increased Efficiency Gas Turbine Engines Outline Abstract As 5th generations Turbine Engines are being retired, the sixth generation ones have the challenge to increase both speed and performance. Engines as a system needs to increase the thrust to weight ratio, decrease fuel consumption and reduce the super alloys that needed for the build. Successful development of an increase efficiency gas turbine engine will happen by using carbon fiber and epoxy resin composites instead of metal, improving

EFFECT OF GAS TURBINE BLADE TIP INJECTION ON THE FLOW CHARACTERISTICS AND THE DISTRIBUTION OF HEAT TRANSFER COEFFICIENT OVER BLADE SURFACES Ahmed A. Abdelsamee 1, Bassily Hanna 2, El-Batsh H.3, Mohammed R. Diab 4 1 Assistant Lecturer, Mechanical Engineering and energy Dep., Faculty of Engineering, South Valley University, Qena, Egypt 2Professor, Mechanical power engineering and energy Dep., Faculty of Engineering, Minia University, Minia, Egypt 3 Professor, Mechanical power Engineering and energy

Gas turbines are very sensitive to critical speeds affecting their low pressure blades. These critical speeds may be close to the rated operating speed leaving a small margin on the allowed frequency range before reaching a protective Changeover. Typically a protective instantaneous low-speed Changeover on gas turbines may be set at 96% of the nominal system frequency. Furthermore, system generation and stability are at risk as the frequency drops. This is specially the case for a thermal generation

This report is an investigation into the evolution and mechanical functionality of aeronautical propulsion systems, from the early attempts at propulsion to modern propulsion system such as propeller, internal combustion engine, ramjet engine and gas turbine. As this report will focus of aeronautical propulsion systems, rocket propulsion systems are almost exclusively involved in astronautics and will not be discussed. As an engineer will have to decide the best combination of engine and thrust device

TminTmax ratio, regenerator effectiveness, and compressor and turbine efficiencies, assuming the working fluid to be air at 100kPa and 300K at the compressor inlet. Model calculations are presented

[1] M. S. Nashed, “Acoustic Emission Monitoring of Propulsion Systems: A Laboratory Study of a Small Gas Turbine”, Doctoral Thesis, School of Engineering and Physical Sciences, Mechanical Engineering, Heriot-Watt University, United Kingdom, 2010. [2] R. K. Mobley, “An Introduction to Predictive Maintenance”, Elsevier Science, United States, 2nd Edition, 2002. [3] M. P. Appleby, “Wear Debris Detection and Oil Analysis Using Ultrasonic and Capacitance Measurements”, Master Thesis, Graduate Faculty