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Arrangements for drawing in air and trapping foreign bodies in an aircraft propulsion assembly

一种推进组件、外来物体的技术，应用在涡轮/推进装置的冷却、涡轮/推进装置的进气口、飞机上动力装置等方向，达到俘获拖拽作用小化的效果

Active Publication Date: 2017-08-01
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, such protective systems also tend to restrict air flow at the exchanger

Method used

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  • Arrangements for drawing in air and trapping foreign bodies in an aircraft propulsion assembly
  • Arrangements for drawing in air and trapping foreign bodies in an aircraft propulsion assembly
  • Arrangements for drawing in air and trapping foreign bodies in an aircraft propulsion assembly

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0031] according to figure 1 The device 1 of the first embodiment illustrated in , comprises an air inlet duct 11, which is divided into two separate channels, one of which in the lower part (bypass channel 12) is formed as a channel for foreign bodies. The other channel (air inlet channel 13) is used to guide the air to the compressor.

[0032] With this arrangement, possible foreign objects 5 carried by the air flow 4 entering the air inlet arrangement of the propulsion assembly through the duct 11 are directed towards the bypass channel 12 forming the catch and do not enter into the air inlet channel 13 . Thus, the aircraft propulsion components are protected from potential damage caused by foreign objects 5 .

[0033] The device also comprises a surface type heat exchanger 6 (for example of the "SACOC" (Surface Air Cooler Oil Cooler) type) in a bypass channel 12, which is arranged in connection with said bypass The inner walls of a portion of the channel 12 are flush.

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PUM

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Abstract

The invention relates to an arrangement, in a pod of an aircraft propulsion assembly, for drawing in air and trapping foreign bodies. Said arrangement includes a main air inlet duct (11) separating into, on one hand, a channel (13) for leading air to a compressor and, on the other hand, a bypass channel (12) capable of trapping foreign bodies (5) that enter said main duct (11). Said arrangement comprises a heat exchanger (6) that extends along a section of the bypass channel (12). Said heat exchanger (6) carries out surface heat exchange along said section and is coupled with an external oil system in order to cool the oil thereof by heat exchange with the air (4) flowing in the bypass channel (12). Said bypass channel (12) has an air outlet (12a) acting as a means for discharging the foreign bodies (5).

Description

technical field [0001] The present invention relates to air inlets and foreign object capture devices in aircraft propulsion assemblies. [0002] The present application is advantageously the case of an aircraft turboprop, but this is not restrictive. Background technique [0003] Turbine engines generally have considerable lubrication needs. Especially in the case of turboprop engines of aircraft, the reduction gearbox positioned between the engine and the propeller of the turboprop engine causes considerable fuel consumption. However, the friction that occurs in the reduction gearbox generates a large amount of heat that must be dissipated. [0004] In order to cool the oil in the circuit near the air inlet casing of the turboprop nacelle, it has been proposed in patent application EP1,018,468 to provide, downstream of the air inlet, an air-oil heat exchanger that is delivered to a volumetric type (such as Radiator) to cool the oil circulating in it. The air inlet slot...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02F01D25/12F02C7/18F02C7/05F02C7/14
CPCB64D33/02F01D25/12F02C7/05F02C7/14F02C7/18F05D2260/213B64D2033/022Y02T50/60
Inventor 纪尧姆·泊亚亚历山大·库莱奥克斯尼古拉斯·瑟尔文
Owner SAFRAN AIRCRAFT ENGINES SAS