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Aircraft engine cooling device

An aero-engine and cooling device technology, applied in the field of aircraft accessories, can solve problems such as poor cooling effect and achieve the effect of optimizing cooling performance

Inactive Publication Date: 2018-10-12
ZHEJIANG UNIVERSITY OF SCIENCE AND TECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides an aero-engine cooling device, which aims to overcome the deficiency of poor cooling effect of the aero-engine cooling device in the prior art

Method used

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  • Aircraft engine cooling device
  • Aircraft engine cooling device
  • Aircraft engine cooling device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 2

[0033] Such as figure 1 , figure 2 , Figure 4 As shown, this embodiment is a further optimization of Embodiment 1. The outer rib 5 is also integrally provided with heat dissipation fins 13. The cross-sectional shape of the heat dissipation fins 13 is elliptical. The outer ring 2 and the middle ring 3 forms an outer duct 14, and the heat dissipation fins 13 are arranged along the flow direction of the airflow in the outer duct 14; the heat dissipation fins 13 are welded or integrally arranged on the outer ribs 5. The arrangement of the cooling fins 13 further increases the heat exchange area of ​​the outer rib 5 and improves the cooling efficiency of the lubricating oil.

[0034] Such as figure 1 , figure 2 As shown, the outer wall of the outer ring 2 is also integrally provided with annular heat dissipation ribs 17, the axis of the annular heat dissipation ribs 17 is coaxial with the axis of the outer ring 2, and the transverse direction of the annular heat dissipation ...

Embodiment 3

[0036] The difference between this embodiment and the first embodiment is that a flow guide structure is added in the oil inlet chamber 15, and the flow guide structure can be a flow guide frame or a flow guide device, and its function is to divert the water in the oil inlet chamber 15 Lubricating oil is evenly introduced into the first oil passage 10 to further optimize the cooling performance of the cooling device.

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Abstract

The invention provides an aeroengine cooling device. A lubricating oil inlet and a lubricating oil outlet are formed in an outer ring; cooling oil passages are arranged in outer bars; the cooling oil passages comprise a first oil passage and a second oil passage; the lubricating oil enters the first oil passage through the lubricating oil inlet, then enters the second oil passage through a transitional oil passage and finally is discharged from the lubricating oil outlet through the second oil passage; an outer duct is formed between the outer ring and a middle ring; an inner duct is formed between the middle ring and an inner ring; during the operation of an aeroengine, air flows through the outer duct and the inner duct; when the high-temperature lubricating oil flows through the first oil passage, the second oil passage and the transitional oil passage, the high-temperature lubricating oil exchanges heat with the air flow through the outer ring, the outer bars and the middle ring, and the heat can be taken away by the air flow, so that the temperature of the lubricating oil can be quickly reduced. Compared with the prior art, cooling medium adopted by the cooling device disclosed by the scheme is the air flowing through the outer duct and the inner duct, and the air does not heat other media on the aircraft when being used for cooling the lubricating oil.

Description

technical field [0001] The invention relates to aircraft accessories, in particular to an aircraft engine cooling device. Background technique [0002] The aero engine is known as the heart of the aircraft, and its structure is complex and precise. The cooling system of an aero-engine is an essential system to ensure the normal operation of the engine. During the operation of the aero-engine, its moving parts will generate a large amount of heat, which will cause the temperature of the parts to rise, and then reduce the mechanical properties of the parts. [0003] In the prior art, the aero-engine cools down the moving parts of the aero-engine through the lubricating oil system (ie, the lubricating system), that is, the lubricating oil is used to absorb the heat generated by the moving parts, and then the lubricating oil is cooled. In the prior art, heat exchange between aviation fuel and lubricating oil is used to reduce the temperature of lubricating oil. However, the t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/14F02C7/06
CPCF02C7/06F02C7/14
Inventor 王世娇段福斌戴敏朱建华李奇志
Owner ZHEJIANG UNIVERSITY OF SCIENCE AND TECHNOLOGY