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Dual flow turbine engine equipped with a precooler

一种涡轮发动机、预冷却器的技术，应用在机器/发动机、发动机功能、燃气轮机装置等方向，能够解决干扰涡轮发动机正常运行、增大飞行器阻力、空气动力学干扰增加等问题，达到避免空气动力学扰动的效果

Inactive Publication Date: 2011-07-06
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For this purpose, a heat exchanger is provided, usually called a precooler, in which the hot air drawn from the central generator of the turbojet engine is cooled by the cold air drawn from the duct of the cabin supercharger, i.e. Cold air cooling of the cold fluid from the turbine engine, thereby interfering with the normal operation of the turbine engine
Furthermore, the precooler is usually placed in the duct of the cabin supercharger, and this increases the aerodynamic disturbance to a disturbance level depending on the extraction of cold air
[0004] In addition, the cold air drawn from the cold flow of the turbine engine and used to cool the hot air drawn from the central generator results in a heated cold air flow that must be exhausted to the turbine outside the engine, thereby increasing the drag of the aircraft

Method used

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  • Dual flow turbine engine equipped with a precooler
  • Dual flow turbine engine equipped with a precooler
  • Dual flow turbine engine equipped with a precooler

Examples

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Embodiment Construction

[0032] Such as figure 1 , 2 Each of the Figures in and 3 shows a twin-flow turbine engine comprising a hollow engine nacelle 1 with a longitudinal axis L-L, provided with an air inlet 2 at the front and an air outlet 3 at the rear. The hollow engine nacelle 1 has a fairing 4 inside, preferably at least partially coated with a sound-attenuating protective layer ( d'atténuation acoustic) 5, the sound attenuation protective layer 5 is used to reduce the internal noise from the turbine engine.

[0033] Inside the hollow engine pod 1 there are arranged:

[0034] - a central heat flow generator 6, known to comprise a plurality of low-pressure and high-pressure compressors, a combustion chamber and a plurality of low-pressure and high-pressure turbines, and generating an axial heat flow 7 from said turbine engine;

[0035] - a nacelle supercharger 8 arranged axially in front of the central generator and generating an annular cold flow 9 from the turbine engine; and

[0036] - an...

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Abstract

The invention concerns a precooler (30) having an annular cross-sectional shape about the axis (L-L) of the pod and arranged inside the rear part (10R) of the inner shroud (10) in contact with a cold fluid (9) exiting the fan duct (13).

Description

technical field [0001] The invention relates to a double-flow turbine engine installed with a precooler. Background technique [0002] It is known that on board an aircraft it is necessary to provide hot air in order to perform certain functions, such as air conditioning the cockpit and passenger compartment or deicing certain mechanisms of the aircraft. [0003] It is also known that said hot air comes from the turbine engines of the aircraft and must undergo considerable cooling before it can be used. For this purpose, a heat exchanger is provided, usually called a precooler, in which the hot air drawn from the central generator of the turbojet engine is cooled by the cold air drawn from the duct of the cabin supercharger, i.e. The cold air from the cold fluid of the turbine engine cools, thereby interfering with the normal operation of the turbine engine. Furthermore, the precooler is usually placed in the duct of the cabin supercharger, and this increases the aerodynam...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D13/08F02K3/06F02K3/075F02K3/115F02C7/141
CPCF02K3/06F02C7/141F02K3/115F05D2260/208F02K3/075Y02T50/676Y02T50/60
Inventor A·波特D·普拉特
Owner AIRBUS OPERATIONS (SAS)
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