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Jet Engine Basics, Metrics, and Technological Trends 19 cal challenges associated with thermally protecting these turbines, the RIT is a good indicator of the level of technology in a modern turbine engine.11 Figure 2.5 illustrates the process of turbine blade cooling. Figure 2.6 illustrates the steady and rapid increase in RIT for turbo- jets, turbofans, and turboshafts over the past five decades. Smaller engines, including turboshafts, normally have lower RITs. Engine component life is measured in expected hours of operation. Many factors, including high temperatures, aerodynamic and me- chanical stresses, erosion, corrosion, and other such factors, to which engine components are subjected can limit the length of time _____________________________________________________________ 1. Convection Cooling. Relatively cool high-pressure air, bled from the compressor, passes through internal ducts in the turbine blades to absorb energy from the blade walls. 2. Impingement Cooling. The internal air passages inside the blade are oriented such that the air is directed forcefully onto the hottest internal surfaces, providing localized enhanced cooling where it is needed. 3. Film Cooling. Multiple holes in the blade’s outer wall connect the blade’s internal cooling cavities with its outer surface, allowing cool air to pick up heat as it passes through the wall as well as providing a protective barrier (film) of relatively cool air flowing around the blade’s exterior. 4. Transpiration Cooling. Similar to film cooling except that it uses a huge number of tiny cooling holes. A porous blade material allows cooling air to ooze out through the blade’s walls, carrying away the heat and then forming the flowing film of cool air around the blade. The first three of these techniques have seen widespread use for several years. Notable improvements in cooling efficiency continue to be realized, through the implementa- tion of CFD to evaluate the effectiveness of various cooling passage geometries and to understand the heat transfer from the flowstream to the turbine blades. Implementation of transpiration cooling is limited by the availability of porous mate- rials that exhibit the necessary strength characteristics. 11An alternative to RIT is the turbine inlet temperature. This is the temperature of the combustion products as they enter the first row of stationary turbine blades, upstream of the rotor. This temperature is normally a few degrees hotter than the RIT because cooling air is passed into these stationary blades and then out through their walls to keep them cool (film cooling). When this air mixes with the combustion products, it lowers the temperature of the combustion products slightly, before they enter the ro- tor. While the temperature entering the vanes is hotter than that entering the rotor, these stationary blades do not have to withstand the high centripetal stresses associ- ated with the turbine rotor’s rotation. Therefore, it can be argued that the RIT is a bet- ter indication of the turbine’s level of technology.PDF Image | Military Jet Engine Acquisition Technology Basics and Cost-Estimating Methodology
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