A turbine blade with a spoiler structure based on an aero-engine
A technology of aero-engine and turbine blades, which is applied in the direction of engine components, machines/engines, mechanical equipment, etc. It can solve the problems of poor stability at the tail end of the blades, reduce the overall speed of the turbine, and lack of supporting structures for the blades, so as to facilitate disassembly and maintenance. , Increase the speed and avoid the effect of rigid bending
Active Publication Date: 2022-05-13
日照黎阳工业装备有限公司
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Problems solved by technology
[0005] In order to solve the above-mentioned technical problems, the present invention provides a turbine blade based on an aero-engine with a turbulence structure to solve the problem of poor stability at the tail end of the blade, the lack of a support structure between the blades, and when it is running, the overall rear end of the turbine has no The turbulence structure reduces the overall speed of the turbine, and it is inconvenient to disassemble and maintain
Method used
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[0038] as attached figure 1 to attach Figure 13 Shown:
[0039]The present invention provides a turbine blade with a spoiler structure based on an aero-engine, including a turbine assembly 1 and a support and reinforcement structure 3; The middle turbine 102 is inserted into the card slot 1031 on the top side of the lower turbine 103, the blade B1021 is inserted into the blade bayonet 1032, the threaded connection holes A1023 are opposite to the threaded connection holes B1034 up and down, and the middle through-pillar 104 is fixed and inserted in the lower In the middle of the turbine 103, the middle piercing post 104 also passes through the middle through hole 1022 upwards to pass through the middle turbine 102, and the top surface of the middle turbine 102 is also provided with a limit slot 1024, and the limit post 1015 on the bottom side of the upper turbine 101 is inserted Into the limit slot 1024, the blade A1011 is placed between the blades B1021, the inner end of th...
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The invention provides a turbine blade with a spoiler structure based on an aero-engine, including a turbine assembly and a support reinforcement structure; the turbine assembly is formed by connecting an upper turbine, a middle turbine, a lower turbine and a middle piercing column; The turbine is snapped into the slot on the top side of the lower turbine, and the middle piercing column is fixedly inserted in the middle of the lower turbine, and the middle piercing column also passes through the middle through hole upwards out of the middle turbine, and the top surface of the middle turbine is also provided with a limit position slot, and the limit post on the bottom side of the upper turbine is inserted into the limit slot, and twelve sets of outer connecting cylinders are connected to the outer wall of the lower turbine, and the support and reinforcement structures are respectively connected to the outer connecting cylinders And supported on blade A and blade B. When the turbine assembly rotates at a high speed, the airflow flows along the airflow hole in the middle of the airflow baffle A to the air passage and flows out through the spoiler tube, increasing the airflow around the turbine assembly, and improving the overall strength of the blade by setting a supporting reinforcement structure.
Description
technical field [0001] The invention belongs to the technical field of aero-engine turbines, and more specifically relates to a turbine blade with a turbulence structure based on an aero-engine. Background technique [0002] Turbine is one of the important parts of aviation gas turbine engine. Its function is to convert most of the available heat energy of gas into the mechanical work of turbine. As one of the key parts of the engine, the turbine blades rotate at high speed under high temperature and high pressure conditions. The air flow on its surface is very complicated, therefore, the quality of the design of the turbine blades is related to the performance of the entire engine. [0003] For example, the patent with the application number: CN201920201415.3 discloses an aero-engine turbine blade, which belongs to the technical field of aero-engine refrigeration and solves the problem of insufficient cooling of the existing aero-engine turbine blades. Aeroengine turbine b...
Claims
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IPC IPC(8): F01D5/02F01D5/22F01D5/30
CPCF01D5/02F01D5/22F01D5/30
Inventor 邹宗果毕克文卢玉章董加胜申健王威李祝雁朱辉潘月栋沙伟李莲鹏赵纪彬岳金玲
Owner 日照黎阳工业装备有限公司