A Tip Loading Method for Crownless Hollow Single Crystal Turbine Blades
A turbine blade, hollow technology, applied in the direction of the blade's supporting element, machine/engine, engine function, etc., to achieve the effect of simple assembly, convenient use and low processing cost
Active Publication Date: 2019-04-16
BEIHANG UNIV
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Problems solved by technology
[0005] The technical problem solved by the present invention is to provide a tip loading method for crownless hollow single crystal turbine blades with low processing cost and convenient use for the tip loading of crownless hollow single crystal turbine blades. Fatigue test of turbine blade assessment section in the temperature range from room temperature to high temperature 1000°C
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[0013] figure 1 is a schematic diagram of a crownless hollow single crystal turbine blade, where B is the blade tip, C is the blade body, D is the edge plate, E is the extension root, and F is the tenon. In order to realize the assessment of the dangerous section of the turbine blade under laboratory conditions, it is necessary to realize Stable loading of crownless hollow single crystal turbine blade tips.
[0014] The present invention is a method for loading the tip of a crownless hollow single crystal turbine blade, and the specific implementation is as follows:
[0015] (1) Before the casting of the crownless hollow single crystal turbine blade, a crown wax pattern is welded on its wax pattern to form a combined wax pattern, and then the crowned blade test piece is cast using the combined wax pattern, such as figure 2 , where A is the cast shroud, C is the blade body, D is the edge plate, E is the extension root, and F is the tenon. This method makes the cast shroud par...
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The invention relates to a crown-free hollow single-crystal turbine blade tip loading method. The crown-free hollow single-crystal turbine blade tip loading method specially comprises the steps that before a crown-free hollow single-crystal turbine blade is casted, a blade crown wax mold is welded to a wax mold of the blade, a combined wax mold is formed, the combined wax mold is used for castinga crown blade test part, a casting blade crown of the crown blade test part is of an inverted trapezoidal structure, and an air flow channel for ensuring that cooling air flow in the hollow single-crystal turbine blade is smoothly discharged is arranged in the test part; the casting blade crown of the crown blade test part is connected with a half-split inner clamping block of a dedicated clamp, and then is loaded into an inverted trapezoidal cavity in the middle of a whole outer clamping block, and by means of the dedicated clamp, blade tip loading of the crown-free hollow single-crystal turbine blade is achieved. When the casting blade crown of the unified size cannot be adopted in the crown-free hollow single-crystal turbine blades with the large size difference, the half-split inner clamping block with the low cost is re-machined, and the whole outer clamping block with the higher cost does not need to be repeatedly machined.
Description
technical field [0001] The invention relates to a tip loading method for a crownless hollow single crystal turbine blade tip of an aero-engine, which is used for realizing stable loading of a crownless hollow single crystal turbine blade under laboratory conditions, and further performing specific assessment cross-sections of the crownless hollow single crystal turbine blade The high-temperature fatigue test belongs to the technical field of aerospace engines. Background technique [0002] The crownless hollow single crystal turbine blade is one of the core components widely used in current aero-engines. It works in a high-temperature environment, bears huge centrifugal force, and is prone to fatigue damage. Therefore, it is of great significance to carry out the high temperature fatigue test of the assessment section of the crownless hollow single crystal turbine blade. [0003] In terms of turbine blade tip loading, different turbine blades have different loading methods....
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IPC IPC(8): F01D5/14
CPCF01D5/147F05D2260/83
Inventor 胡殿印王荣桥张斌毛建兴马琦航崔金铎
Owner BEIHANG UNIV