Channel structure for internal cooling of gas turbine stationary blade and gas turbine stationary blade
A gas turbine and internal cooling technology, applied in the direction of machines/engines, mechanical equipment, engine functions, etc., can solve problems affecting the economy and safety of gas turbines, reduce the mechanical properties of metal blades, and large thermal stress, etc., to achieve the elimination of local hot spots , Improve thermal stress, increase the effect of temperature gradient
Active Publication Date: 2021-08-17
XI AN JIAOTONG UNIV
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Problems solved by technology
[0004] However, with the increase of the turbine inlet temperature of the gas turbine, it has far exceeded the allowable temperature of the metal material of the turbine blade. mechanical properties, and it will easily cause the blades to burn, which will seriously affect the economy and safety of gas turbine operation
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[0033] In order to enable those skilled in the art to better understand the solutions of the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only It is an embodiment of a part of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present invention.
[0034] It should be noted that the terms "first" and "second" in the description and claims of the present invention and the above drawings are used to distinguish similar objects, but not necessarily used to describe a specific sequence or sequence. It is to be understood that the data so used are interchangeable under appropriate ...
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The invention belongs to the field of gas turbines, and discloses a channel structure for internal cooling of a gas turbine stationary blade and the gas turbine stationary blade. The channel structure comprises a plurality of straight channels and a plurality of bent channels, wherein, the plurality of straight channels are arranged in parallel, and every two adjacent straight channels are connected through a bent channel; the wall surface on the upper side in the main flow direction in each straight channel is defined as a suction surface; the wall surface positioned on the lower side in the main flow direction is a pressure surface; a plurality of oblique ribs are arranged on the suction surface and the pressure surface; a plurality of transverse ribs are arranged on the wall face, connected with the downstream ends of the oblique ribs, in the straight channel, and the downstream ends of the oblique ribs are the ends, located on the downstream portion, of projections of the oblique ribs in the main flow direction; and one ends of the transverse ribs are connected with the oblique ribs on the suction surface, and the other ends of the transverse ribs are connected with the oblique ribs on the pressure surface. According to the channel structure, heat transfer of the downstream low Reynolds number area of fins can be effectively improved, temperature distribution is more uniform, local hot spots of the gas turbine stationary blade are eliminated, thermal stress is improved, the stability of the gas turbine stationary blade is improved, and the service life of the gas turbine stationary blade is prolonged.
Description
technical field [0001] The invention belongs to the field of gas turbines, and relates to a channel structure for internal cooling of gas turbine stator blades and the gas turbine stator blades. Background technique [0002] Gas turbine is a kind of power equipment with high cycle efficiency, compact structure, small size, light weight and high output power. It is widely used in important industrial fields such as aviation power, ship propulsion, and land power generation. It plays an important role in the civil field. [0003] The research shows that increasing the gas turbine inlet temperature is an effective way to improve the gas turbine cycle efficiency and output power. When the gas inlet temperature increases by 100°C, the cycle specific work can be increased by 20-25%, and the fuel consumption can be reduced by 6-7%. At present, with the continuous development of gas turbine technology, the turbine inlet temperature continues to increase. For land-use heavy-duty ga...
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IPC IPC(8): F01D25/12F01D9/02
CPCF01D25/12F01D9/02F05D2260/22141F05D2260/2212
Inventor 高铁瑜鹿家麒马晨曦龚建英李军
Owner XI AN JIAOTONG UNIV