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Aircraft cooling system

A cooling system and aircraft technology, applied in the cooling system of power plant, aircraft parts, aircraft control and other directions, can solve problems such as high cooling requirements, and achieve the effect of large heat exchange area and excellent cooling capacity

Active Publication Date: 2010-12-01
AIRBUS OPERATIONS GMBH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, fuel cells with high capacity to generate electricity also generate a lot of heat and therefore have high cooling requirements

Method used

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  • Aircraft cooling system
  • Aircraft cooling system
  • Aircraft cooling system

Examples

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Embodiment Construction

[0030] figure 1 shown suitable for use in Figure 2 to Figure 5 A cooling element 12 in an aircraft cooling system 10 is shown. The cooling element 12 includes a substantially cuboidal housing 14 . Cooling air inlets 18 are provided on the front side surface 16 of the cooling element 12 . A radial fan 20 is arranged in the region of the cooling air inlet 18 . A radial fan 20 is used in the direction of the cooling air inlet 18 (e.g. figure 1 Indicated by the arrow P in) sucking cooling air, and then radially outward with respect to the rotation axis 22 of the radial flow fan 20 (as figure 1 Shown by the arrow P in) to push the cooling air. On the side surfaces 24 , 26 , 28 , 30 of the cooling element 12 adjoining the front side surface 16 are provided heat exchangers 32 , 34 , 36 , 38 respectively. Cooling air flowing into the housing 14 of the cooling element 12 through the cooling air inlet 18 flows through the heat exchangers 32 , 34 , 36 , 38 and thereby transfers co...

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PUM

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Abstract

The invention relates to an aircraft cooling system (10) comprising a cooling element (12) that comprises a housing (14), a cooling air inlet (18) that is embodied in the housing (14) and a plurality of heat exchangers (32, 34, 36, 38) that are arranged on the lateral surfaces (24, 26, 28, 30) of the housing (14) and through which cooling air supplied to the cooling air inlet (18) flows. A cooling air supply channel (40, 40') joins a cooling air supply opening (44, 44') embodied in a tail section of the aircraft to the cooling air inlet (18) of the cooling element (12). A cooling air outlet channel (46) joins the heat exchanger (32, 34, 36, 38) of the cooling element (12) to a cooling air discharge opening (50).

Description

technical field [0001] The invention relates to an aircraft cooling system particularly suitable for cooling fuel cell systems installed on board aircraft. Background technique [0002] Fuel cell systems can generate electricity with low radiation and high efficiency. For this reason, efforts are currently being made to utilize fuel cell systems to generate electrical energy in various mobile applications such as, for example, automotive engineering and aeronautics. For example, it is conceivable to replace the electrical generators currently used to supply electrical power on board aircraft and driven by the main or auxiliary engines (APU) with fuel cell systems in aircraft. Furthermore, the fuel cell system can also be used to supply emergency power to the aircraft and replace the ram air turbine (RAT) that has been used as the emergency power system. [0003] In addition to electrical energy, the fuel cell also generates thermal energy during operation, which has to be ...

Claims

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Application Information

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IPC IPC(8): B64D33/10B64C21/04B64D13/00
CPCB64C21/06Y02T50/166B64D13/00B64D33/08Y02T50/50Y02T50/10
Inventor 托尔文·鲍姆加特阿尔夫-亨宁·斯托尔特沃克·皮尊卡乌韦·沃尔拉布
Owner AIRBUS OPERATIONS GMBH
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