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into a splined recess in the compressor rotor hub. The axial compressor engine may use either of these methods. There are various ways of attaching turbine blades or buckets, some similar to compressor blade attachment. The most satisfactory method used is the fir-tree design, shown in Figure 1-36. The blades are retained in their respective grooves by a variety of methods; some of the more common ones are peening, welding, locking tabs, and riveting. Figure 1-37 shows a typical turbine wheel using riveting for blade retention. A method of blade retention used quite frequently is peening, and it applies in various ways. Two of the most common applications of peening are described in the following paragraphs One method of peening requires that a small notch be ground in the edge of the blade fir-tree root before blade installation. The blade inserts into the disc. The notch is filled with the disc metal, which is “flowed” into it through a small punch mark made in the disc, adjacent to the notch. The tool used for this job is similar to a center punch, and is usually manufactured locally. Another method of peening is to construct the blade’s root in such a way as to contain all the elements necessary for its retention. This method is shown in Figure 1-38. The blade root has a stop on one end, while on the opposite end of the blade is a tang. The blade is inserted and moves in one direction only. The tang is peened over to secure the blade in the rotor disc. Turbine blades may be either forged or cast, depending on the composition of the alloys. Most blades are precision cast and finish-ground to the desired shape. Most turbines in use are open at the outer perimeter of the blades; however, there is a second type called the shrouded turbine. The shrouded turbine blades, in effect, form a band around the outer perimeter of the turbine wheel. This improves efficiency and vibration characteristics and permits lighter stage weights; on the other hand, it limits turbine speed and requires more blades shown in Figure 1-39. In turbine rotor construction, it may be necessary to use turbines of more than one stage. A single turbine wheel often cannot absorb enough power from the exhaust gases to drive the parts dependent on the turbine for its kinetic energy. In a turbojet engine, these parts are the compressor and engine-driven accessories. In the turboprop engine, these parts are the propeller and the reduction gear assembly. A turbine stage consists of a row of stationary vanes or nozzles, followed by a row of rotating blades. Some models of turboprop engines use as many as five turbine stages. You should remember that regardless of the number of wheels necessary for driving engine parts, there is always a turbine nozzle in front of each wheel. The occasional use of more than one turbine wheel is necessary in cases of heavy Figure 1-39 — Shrouded turbine blades. Figure 1-38 — Turbine bucket, featuring peening method of blade retention. 1-26PDF Image | JET ENGINE THEORY AND DESIGN
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