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Method for controlling thermal effluents generated by an aircraft and cooling device for an aircraft implementing said method

A control method and technology of cooling device, applied in the cooling of engine, cooling system of power plant, cooling of turbine/propulsion device, etc., can solve the problems of harmful aircraft maintenance, complicated installation and disassembly process of propulsion device, etc. Energy consumption, effect of improving aerodynamic characteristics

Inactive Publication Date: 2011-02-09
AIRBUS OPERATIONS SAS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, the effect of this addition is to complicate the installation and removal process of the propulsion unit, which has been found to be detrimental to the maintenance of the aircraft

Method used

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  • Method for controlling thermal effluents generated by an aircraft and cooling device for an aircraft implementing said method
  • Method for controlling thermal effluents generated by an aircraft and cooling device for an aircraft implementing said method
  • Method for controlling thermal effluents generated by an aircraft and cooling device for an aircraft implementing said method

Examples

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Embodiment Construction

[0031] As mentioned above, an aircraft consists of an airframe and one or several propulsion units.

[0032] The body of an aircraft broadly refers to all parts of the aircraft except the propulsion device, especially the fuselage, side wings, and empennage of the aircraft.

[0033] exist Figures 2 to 6 In , the airframe of the aircraft is schematically indicated by 110 and the propulsion device by 112 . The other propulsion means are not shown and are generally the same.

[0034] In one widely adopted implementation, the propulsion units are generally suspended under the flanks by wing struts. However, the invention is not limited to this implementation and covers all solutions involving the connection between airframe and propulsion means. For the following description, the interface between airframe 110 and propulsion means 112 is indicated by numeral 114 and indicated by dashed lines.

[0035] Parts common to the prior art, used with figure 1 Add 100 to the same nota...

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PUM

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Abstract

The invention relates to a method for controlling the thermal effluents of an aircraft including an airframe (110) and at least one propulsion unit (112), wherein said at least one propulsion unit (112) includes a turbomachine (116) supplied with fuel via a fuel supply circuit (122) extending from a tank (124) provided at the airframe (110), said airframe (110) including at least one thermal effluent source (134), characterised in that it comprises scattering at least partially, at the level of at least one propulsion unit (112), the thermal effluents generated at the airframe (110) by using the fuel used for supplying the turbomachine (116) as a heat-carrier fluid.

Description

technical field [0001] The invention relates to a method of controlling the thermal emissions of an aircraft and to an aircraft cooling device allowing said method to be implemented. Background technique [0002] The aircraft includes an airframe and at least one propulsion unit. exist figure 1 In , the body is schematically represented by 10, and the propulsion device is represented by 12. [0003] The airframe broadly refers to all parts of the aircraft except the propulsion device, especially the aircraft fuselage, side wings, and empennage. [0004] According to a widely used embodiment, the propulsion devices are suspended under the flanks by means of wing struts. More generally, propulsion units are used in figure 1 The interface 14 indicated by the dotted line is connected to the body. [0005] The propulsion unit 12 comprises a turbine 16 equipped with a first engine cooling circuit 18 through which a heat transfer fluid, in particular oil, passes and circulates...

Claims

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Application Information

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IPC IPC(8): B64D37/34F02C7/18
CPCF02C7/224B64D37/34B64D2013/0659Y02T50/671B64D2013/0614Y02T50/54Y02T50/545B64D33/10Y02T50/50Y02T50/60
Inventor 纪尧姆·比兰扬·迪特马尔
Owner AIRBUS OPERATIONS SAS
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