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Adjustable turbine guiding device and forming method

A technology of turbine guide and forming method, which is applied in the field of adjustable turbine guide and forming adjustable turbine guide, and can solve problems such as low cycle life, difficulty in angle adjustment, turbine guide ablation, etc.

Active Publication Date: 2020-10-27
CHINA HANGFA SOUTH IND CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides an adjustable turbine guide and its forming method to solve the technical problems of the existing turbine guide, which are easy to be ablated due to gas leakage, low cycle life, and difficult to adjust the angle

Method used

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  • Adjustable turbine guiding device and forming method
  • Adjustable turbine guiding device and forming method
  • Adjustable turbine guiding device and forming method

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Embodiment Construction

[0030] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.

[0031] refer to figure 2 and image 3 , the preferred embodiment of the present invention provides an adjustable turbine guide, including: an annular inner ring assembly 10, an annular outer ring assembly 20 coaxially sleeved outside the inner ring assembly 10, and connected to the inner ring assembly 10. For the guide vane 30 between the ring assembly 10 and the outer ring assembly 20, the trailing edge end surface 302 of the guide vane 30 is provided with a deformation adjustment slot 304 extending toward its leading edge 303, and the deformation adjustment slot 304 communicates with the vane pot and the vane Back, the deformation adjustment slot 304 is used to form an adjustable aileron 305 with an adjustable angle on the trailing edge 301 on one side, so as ...

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PUM

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Abstract

The invention discloses an adjustable turbine guiding device and a forming method. The device comprises an annular inner ring assembly, an annular outer ring assembly and guiding blades, wherein the inner ring assembly is coaxially sleeved with the outer ring assembly, and the guiding blades are connected between the inner ring assembly and the outer ring assembly. The tail edge end faces of the guiding blades are provided with deformation adjusting seams extending towards the front edges of the guiding blades, the deformation adjusting seams communicate with blade basins and blade backs of the guiding blades, and the deformation adjusting seams are used for enabling the tail edges of one sides of the guiding blades to form angle-adjustable auxiliary wings for adjusting the direction of airflow flowing through the blade basins of the guiding blades and the flow area between every two adjacent guiding blades.

Description

technical field [0001] The invention relates to the field of aviation turbine engines, in particular to an adjustable turbine guide. In addition, the invention also relates to a molding method for the adjustable turbine guide. Background technique [0002] Existing small aero turbine engines have abnormal noises of metal microcracks during the cooling process after each operation. The sound comes from thermal stress release and microcrack propagation during the cooling process of hot end components, which is common in turbine guide cracks. A certain type of engine primary guide vane (such as figure 1 shown) has no cooling air and is prone to ablation due to gas leakage. The cycle life of existing turbine guides is low, mainly because the airfoil is a ruled surface (such as figure 1 As shown), the guide vane connects the outer ring and the inner ring radially and straightly, and the contraction margin is very small. [0003] Small aero turbine engines need to reduce manuf...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04F01D25/12B23P15/00
CPCF01D9/041F01D25/12B23P15/00Y02T50/60
Inventor 刘飞亭范丽萍雷霄玉阳剑吴学深
Owner CHINA HANGFA SOUTH IND CO LTD
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