Slotted air film cooling structure for guide blades of turbines
A technology of turbine guide vane and air film cooling, which is applied to stators, engine components, machines/engines, etc., can solve the problems of processing technology and manufacturing cost control, the impact of high temperature components on aerodynamic performance, and reduce engine efficiency, etc., to achieve high cooling. Efficiency, improving efficiency, reducing the effect of aerodynamic losses
Inactive Publication Date: 2014-07-09
BEIHANG UNIV
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Problems solved by technology
Changing the geometric shape and arrangement of air film holes has also become the main research direction to improve the coverage characteristics of air-conditioning and improve the efficiency of air-film cooling. However, many new air film holes such as air film holes with protruding pieces have relatively common The feature is that it is geometrically complex, such as air film holes with protruding pieces, etc. These concave or convex geometric features are very difficult to process and manufacture. If they are used on high-temperature components of real aero-engines , will bring difficulties to the processing technology and manufacturing cost control, which will greatly increase the cost of components using these technologies
If this geometric feature is not carefully studied and carefully designed, it may affect the aerodynamic performance of high-temperature components, or even increase the aerodynamic loss and reduce the engine efficiency. make higher demands
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[0011] The present invention will be further described in detail below in conjunction with the accompanying drawings.
[0012] refer to figure 1 , 2 As shown, the present invention is a novel film cooling structure suitable for a turbine guide vane of a gas turbine engine. The biggest feature of the novel film cooling structure is that the conventional film cooling holes are replaced by film slots (2). The blade base (1) has two exhaust film slits (2), which are respectively opened on the suction surface and the pressure surface of the blade. The air film slit (2) is an oblique slit forwardly inclined at an angle (α) along the mainstream direction, (α ) ranges from 30° to 40°, the air film slit (2) communicates with the tail cold air cavity (4), and is arranged at equal intervals along the blade height direction, and its outlet is located at a distance of 1 to the blade chord length from the blade tail edge (5) / 3 of the stepped surface (6), the height (p) of the stepped su...
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The invention discloses a novel slotted air film cooling structure for guide blades of turbines of gas turbine engines. The novel slotted air film cooling structure comprises a blade base, air film slots, connecting ribs and stepped planes, and is characterized in that the air film slots are oblique slots which are forwardly oblique along a mainstream direction, are communicated with a tail cooling air cavity and are equidistantly arrayed along the blade height direction, outlets of the air film slots are separated from a blade tail edge, and the connecting ribs and the air film slots are alternately distributed. The novel slotted air film cooling structure has the advantages that uniform and consistent cooling air films can be transversely formed by the novel blade structure, and outflow air films are high in stability; an eddy flow effect of outflow cooling air can be weakened, the cooling air films are large in coverage area, and accordingly the novel slotted air film cooling structure is high in cooling efficiency and simple in machining.
Description
technical field [0001] The invention relates to a novel air film cooling structure for high-temperature parts of a gas turbine engine, in particular to a slit air film cooling structure suitable for turbine guide blades. This structure can achieve a better cooling effect than the traditional air film hole cooling structure, and meets the cooling requirements of the turbine guide vane of the gas turbine engine. Background technique [0002] Turbine blades are important hot-end parts of gas turbine engines, especially the guide blades are directly washed by the high-temperature gas at the outlet of the combustion chamber. At present, the temperature of the front inlet of advanced engines has reached about 2000K, which is 400K higher than the melting point of the metal material of the compressor turbine blade, which shows the importance and urgency of cooling design. Advanced cooling keeps hot components at higher temperatures for longer engine life and reliability. [0003] ...
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IPC IPC(8): F01D9/02F01D25/12
Inventor 吴宏李育隆
Owner BEIHANG UNIV
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