Blade verification plates and method of use
a technology of verification plate and blade, applied in the field of gas turbine engines, can solve the problems of time-consuming and expensive methods
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[0013]Referring to FIGS. 1 and 2, there illustrated are three adjacent rotor stages 100, 102, 104 stacked together such that the stages 100-104 are adjacent one another, for example, in a final assembly condition. Each stage 100-104 includes a plurality of blades or airfoils 106 placed around the outer periphery of the corresponding rotor 100-104. Typically, in modern rotors the blades 106 are in a clocked relationship as between any two stages 100-104. The stages 100-104 may comprise those of a turbine engine, such as a steam turbine engine or those that are a part of a compressor of a gas turbine engine. For description purposes, the turbine engine herein will refer to a gas turbine engine, however this is merely for descriptive purposes, and is not intended to limit the invention.
[0014]In accordance with an embodiment of the invention, three blade verification plates 108, 110, 112 are provided wherein each plate 108-112 is placed over a corresponding single blade 106 in each of t...
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