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Flow mixer duct for bleed system

A discharge system and piping technology, applied to the cooling system, pipes, rigid pipes, etc. of the power plant, can solve the problems of low efficiency, additional pressure loss, etc.

Pending Publication Date: 2020-10-20
空中客车西班牙有限责任公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] Unfortunately, both computational models and practical tests have shown that this solution is extremely ineffective in addition to creating turbulence that will cause additional pressure losses due to the production of effective airfoils that remain within the cross-section of the duct caused by restrictions

Method used

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  • Flow mixer duct for bleed system
  • Flow mixer duct for bleed system
  • Flow mixer duct for bleed system

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0073] figure 1 a to figure 1 c shows an embodiment of a duct according to the invention for an exhaust system of an aircraft. In these figures the ducts are shown in front view, longitudinal section and rear view respectively.

[0074] pipeline along figure 1 The longitudinal axis (z-z') shown in dashed line in (b) extends. According to this embodiment, the pipeline includes:

[0075] - an inlet section (2) for the fluid flow into the pipe (1);

[0076] - an outlet section (3) at a distance from the inlet section (2) through which the fluid flow leaves the pipe (1); and

[0077] - two continuous pieces (4, 5) arranged on and protruding from the inner wall of the duct;

[0078] wherein the continuous piece has a first end (4.1, 5.1) located close to the inlet section (2) and a second end (4.2, 5.2) located close to the outlet section, and

[0079] Wherein the continuous piece extends obliquely from the first end (4.1, 5.1) to the second end (4.2, 5.2) in the direction o...

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PUM

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Abstract

The invention provides a duct for a bleed system of an aircraft, wherein the duct extends from an inlet section to an outlet section along a longitudinal axis, and wherein it comprises a continuous piece arranged on and protruding from the internal wall of the duct. The duct is of application in duct subject to temperature gradients in order to reduce the temperature of the warmest airflow closerto the inner wall rather than rapidly mixture the airflow.

Description

technical field [0001] The invention belongs to the field of air systems and, in particular, to the field of protecting ducts in aircraft operating at high temperature gradients. [0002] More specifically, the present invention provides ducts with internal feature walls that help reduce the temperature of the hottest air streams closer to the internal walls, rather than where such incoming air streams have high temperature gradients Let the air stream mix rapidly. Background technique [0003] In a gas turbine engine, air is typically drawn in from a compressor stage upstream of the fuel combustor. This bleed air is therefore at high temperature and pressure, with typical temperature values ​​comprised in the range 200°C to 500°C when drawn from the engine and conditioned in the precooler in the range 200°C to 250°C , and the typical pressure value is 275kPa. Once inhaled, this bleed air is directed from the stages of said compressors of the engine to various locations w...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16L9/02F15D1/06B64D33/08
CPCF16L9/02F15D1/06B64D33/08F02C7/18F05D2250/25F05D2240/126F05D2240/127F05D2260/2212F05D2260/213F02C9/18Y02T50/60F02C7/14F05D2220/323F28F1/14F28F2210/10
Inventor 布里斯·勒努瓦
Owner 空中客车西班牙有限责任公司