منابع مشابه
Metallic and Ceramic Thin Film Thermocouples for Gas Turbine Engines
Temperatures of hot section components in today's gas turbine engines reach as high as 1,500 °C, making in situ monitoring of the severe temperature gradients within the engine rather difficult. Therefore, there is a need to develop instrumentation (i.e., thermocouples and strain gauges) for these turbine engines that can survive these harsh environments. Refractory metal and ceramic thin film ...
متن کاملLow Emission Combustion Technology for Stationary Gas Turbine Engines
The need to control exhaust emissions from stationary power sources is dictated by environmental regulations that limit the amount of smoke (particulates), sulfur dioxide, carbon monoxide, hydrocarbons, and oxides of nitrogen or NOx that can be exhausted into the atmosphere. In areas where atmospheric pollution is a serious concern, as in the Los Angeles basin, very low emission levels are dema...
متن کاملGas Turbine Combustion and Ammonia Removal Technology of Gasified Fuels
From the viewpoints of securing a stable supply of energy and protecting our global environment in the future, the integrated gasification combined cycle (IGCC) power generation of various gasifying methods has been introduced in the world. Gasified fuels are chiefly characterized by the gasifying agents and the synthetic gas cleanup methods and can be divided into four types. The calorific val...
متن کاملNumerical simulation of steady state heat transfer in a ceramic-coated gas turbine blade
As gas turbine entry temperature (TET) increases, thermal loading on first stage blades increases and, therefore, a variety of cooling techniques and thermal barrier coatings (TBCs) are used. In the present work, steady state blade heat transfer mechanisms were studied via numerical simulations. Convection and radiation to the blade external surface were modeled for a super alloy blade with and...
متن کاملVerifiable Control System Development for Gas Turbine Engines
A control software verification framework for gas turbine engines is developed. A stability proof is presented for gain scheduled closed-loop engine system based on global linearization and linear matrix inequality (LMI) techniques. Using convex optimization tools, a single quadratic Lyapunov function is computed for multiple linearizations near equilibrium points of the closed-loop system. Wit...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Journal of Engineering for Gas Turbines and Power
سال: 1995
ISSN: 0742-4795,1528-8919
DOI: 10.1115/1.2815465