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Cooling hole, engine combustion chamber and cooling hole processing method

A technology of cooling holes and diverging walls, which is applied in the field of aero-engines, can solve the problems of optical path interference in laser processing, insufficient wall processing space, and limitation of cooling hole inclination angle, etc., and achieve the effect of improving cooling effect, good cooling effect, and improving processing efficiency

Active Publication Date: 2020-08-04
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the certain inclination angle of the flame tube itself, for this type of pass formed by compounding multiple cylindrical holes, problems such as insufficient wall processing space or interference of laser processing optical paths have been caused, which has greatly affected the inclination angle of the cooling hole. limit

Method used

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  • Cooling hole, engine combustion chamber and cooling hole processing method
  • Cooling hole, engine combustion chamber and cooling hole processing method
  • Cooling hole, engine combustion chamber and cooling hole processing method

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Embodiment Construction

[0071] The present invention will be further described below in conjunction with specific embodiment and accompanying drawing, set forth more details in the following description so as to fully understand the present invention, but the present invention can obviously be implemented in many other ways different from this description, Those skilled in the art can make similar promotions and deductions based on actual application situations without violating the connotation of the present invention, so the content of this specific embodiment should not limit the protection scope of the present invention.

[0072] Note that Figures 1 through Figure 9 All are for example only, and they are not drawn in accordance with the same scale conditions, and should not be taken as limitations on the protection scope of the actual claims of the present invention.

[0073] Such as Figure 1A As shown, in the conventional impingement and divergence cooling structure, the wall structure 200 of ...

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Abstract

The invention aims to provide a cooling hole, an engine combustion chamber and a cooling hole processing method. The cooling hole comprises an inlet section, an expansion transition section, an expansion section and cylinder-like sections, wherein the inlet section, the expansion transition section, the expansion section and the cylinder-like sections are positioned between the inner wall surfaceand the outer wall surface, the cylinder-like sections enlarge the outlet area of a cooling channel on a divergent wall, so that the cooling effect of the cooling hole is improved; and in addition, the expansion transition section, the expansion section and the cylinder-like section are formed by translating a circular cross section in the central line direction (the hole axis direction) of the inlet section, so that when the cooling hole is processed by laser, the incident angle of the laser can be kept unchanged, and thus the processing efficiency of laser processing can be remarkably improved. The engine combustion chamber comprises the cooling hole, so that the engine combustion chamber has the advantages of simple processing process, high processing efficiency and good cooling effect.According to the cooling hole processing method, in the process of processing machining the cooling hole with a complex structure, the incident angle of the laser can be kept unchanged.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a cooling hole, an engine combustion chamber and a cooling hole processing method. Background technique [0002] The combustion chamber of an aero-engine is the part with the highest working temperature and the highest pressure in the entire engine. The flame tube of the combustion chamber is cooled to prevent the high-temperature gas from damaging the metal material, and at the same time improve the reliability and life of the combustion chamber. At present, the basic cooling methods of the flame cylinder of the aero-engine combustor are as follows: sweat cooling, laminate, tile structure, impact / air film cooling, impact / divergent cooling, divergent cooling and air film / divergent cooling, etc. Modern new aero-engines put forward more stringent requirements for emission and efficiency, which requires the minimum amount of air to cool the higher-temperature flame tube to make its reli...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/06
CPCF23R3/06F23R2900/03043
Inventor 沈涵罗昌金
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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