Civil Engine Data
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No notes for slide. Trent presentation 1. Indian institute of space science and technology Thiruvananthapuram Done by: Priyanka Ojha , K. In addition, this unique three-shaft technology improves engine operability. That is like hanging a freight train off each blade. The first generation of turbine blades had about 10 tons of force. The Compressor and Turbine have the following features: Three-shaft high bypass ratio Pressure Limits Fuel pressure kPa Minimum absolute inlet pressure measured at engine inlet: Low fan speed, life of engine blades, elliptical leading edge blades, low hub-to-tip ratio.
It does this by combining lower rotational speed with advanced aerodynamic profiles. The low hub diameter enables a more compact design and even lower weight to be achieved. It has to be done in an ultra-clean production facility through a process of diffusion bonding. The compression system of a Trent engine comprises the fan, eight intermediate pressure stages and six high pressure stages.
It then delivers this compressed air to the combustion system. The blades accelerate the air increasing its dynamic pressure, and then the vanes decelerate the air transferring kinetic energy into static pressure rises This is used in the last two stages of the HP compressor drum and HP turbine disc. Static pressure Total pressure Temperature Increasing pressure and temperature through compressors increasing Compressor stages Air is diffused around the outside of the combustion chamber, slowing it down; the speed at which the air leaves the compressor would blow out the flame were it to pass directly through.
In the illustration, blue shows the combustion feed air from the HP compressor, and white through yellow to red, the hot combustion gases in the burning zones being cooled before entering the turbine system. Cooling air and thermal barrier coatings are therefore used to protect the walls and increase component lives. Dilution air is used to cool the gas stream before entering the turbines.
Low risk, improved efficiency, low emissions, low noise. The tiles mean you need less cooling air to cool the combustor. With less cooling air, which takes up space, the same amount of fuel burns in a larger volume, lowering peak temperature.
The area exposed to high temperatures is lined with 2-byinch, overlapping, heat-resistant tiles. This lining can grow and shrink with temperature cycles, shielding the metal rings of the combustor from the full effects of the heat and reducing cracking stress. Like the compressor, the turbine comprises of a rotating disc with blades and static vanes, called nozzle guide vanes. The gas pressure and temperature both fall as it passes through the turbine.
This blade is grown as a single crystal of a Rolls-Royce alloy in a vacuum furnace. As it grows, it incorporates a complex series of air passages to cool the blade.
Then it needs external cooling holes created by incredibly accurate laser drilling. And on top of all that is a thermal barrier coating that surpasses that used to make the tiles on the space shuttle. It sits in a disc that rotates at more than 10, rpm These chevrons help to "premix" the core air and bypass air flows before they exit the aircraft.
Pressure and temperature stations for Trent This is a significant amount of the overall turbine power and will therefore have a significant effect on engine matching. Typical HP compressor map with constant speed and constant efficiency iso-lines Up to a point, fan efficiency increases with size. The Trent engine has a bypass ratio of 10 and a fan diameter of inches, compared to the predecessor Trent , which has diameter of 97 inches and a bypass ratio of 5.
The Trent increases fuel consumption efficiency by 13 to 14 percent, compared to the Trent The lower fan pressure ratio, and the resulting lower exhaust velocity, improve propulsive efficiency and SFC The higher the pressure, the better the efficiency. Rolls-Royce cites as critical technologies those that minimize the need for cooling air, improve cooling configurations for blades and improve materials and thermal barrier coatings.
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