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Turbine engine nacelle with heat exchanger

A turbine engine and heat exchanger technology, applied in the direction of machines/engines, engine functions, engine components, etc., can solve the problems of difficult control of air inlet temperature, unsuitable for flight phase, difficult to adjust, etc.

Active Publication Date: 2016-05-18
AIRCELLE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0021] This results in cooling of the lubricant, and maintenance of the inlet temperature is difficult to control
[0022] as pointed out, the proposed system is difficult to adjust to the heat to be dissipated and the actual deicing needs and is not suitable for practical needs especially for the phase of flight

Method used

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  • Turbine engine nacelle with heat exchanger
  • Turbine engine nacelle with heat exchanger
  • Turbine engine nacelle with heat exchanger

Examples

Experimental program
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Embodiment Construction

[0054] The nacelle 1 of the turbine engine constitutes the casing of the turbine engine 2 and has a generally tubular structure comprising an external fairing 3 defining an external aerodynamic surface and an internal aerodynamic flow through said turbine engine and in particular a fan 5 Surface of the inner fairing4.

[0055] The outer cowling 3 and the inner cowling 4 are connected upstream by the wall forming the air intake lip 6 of the nacelle nose.

[0056] The outer cowling 3 and the inner cowling 4 of the nacelle delimit an inner space housing a cooling system cooling the motor lubricant of the turbine engine 2 .

[0057] The cooling system comprises a heat exchanger 10 of the air / oil type supplied on the one hand by lubricant to be cooled (second fluid) and on the other hand by air to be heated (first fluid).

[0058] The lubricant is sent to the exchanger by means of a pump system (not shown) of the turbine engine and a flow duct 111 through the support arm 2a of the...

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PUM

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Abstract

The invention relates to a nacelle (1) of a turbine engine (2), comprising at least one outer cowling (3) defining an outer aerodynamic surface and at least one inner cowling (4) defining an inner aerodynamic flow surface, said surface being Connected upstream by the leading edge forming the air intake lip (6), said turbine engine nacelle comprises at least one heat exchanger (10) associated with at least one flow duct (13) forming at least one A recirculation loop through the heat exchanger and comprising at least one flow-through area (13a) extending at least partially along the outer fairing in contact with at least one wall of said outer enclosure, so as to allow the passage of Heat exchange with the outside air of the cabin.

Description

technical field [0001] The invention relates to a turbine engine nacelle equipped with a system for cooling engine oil. Background technique [0002] Aircraft are propelled by one or several propulsion assemblies, each comprising a turbine engine housed in a tubular nacelle. Each propulsion assembly is secured to the aircraft by a mast typically located under or on the wing or on the fuselage. [0003] The nacelle usually has a structure comprising an air intake upstream of the electric motor, a middle part for surrounding the fan or compressor of the turbine engine and its casing, a space capable of accommodating thrust reversers and a combustion chamber for surrounding the turbine engine The downstream part, and the nacelle usually terminates at the nozzle, the outlet of which is located downstream of the turbine engine. [0004] Typically, a turbine engine includes a blade system (compressor and possibly a fan or unducted propeller) driven in rotation by a gas generator...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D33/10B64D15/02B64D15/04B64D15/06F02C7/047F02C7/12
CPCB64D15/04B64D33/10F02C7/047F02C7/12F02K3/06F05D2240/14F05D2260/213B64D33/02B64D2033/0233Y02T50/60F01D25/24
Inventor 皮埃尔·卡吕埃勒弗兰克·扎加内利帕特里克·哥诺迪克奥利维尔·凯尔布莱尓
Owner AIRCELLE