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Heat exchanger for turbomachine and associated manufacturing method

A technology for heat exchangers and turbines, applied in the field of oil cooling, which can solve problems such as impracticality, affecting fixation, and non-removability

Pending Publication Date: 2021-05-07
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, it is necessary to set up long and expensive quality control operations
Furthermore, the fixation of these connecting parts 34a, 34b makes them non-removable, which is impractical when it is desired to be able to simply inspect the first and second circuits 20, 26.
Finally, considering the position of the heat exchanger 12 of the annular air flow path, it is necessary to limit its radial dimensions so as not to modify the diameter of the casing, which must affect other parts fixed to it

Method used

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  • Heat exchanger for turbomachine and associated manufacturing method
  • Heat exchanger for turbomachine and associated manufacturing method
  • Heat exchanger for turbomachine and associated manufacturing method

Examples

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Embodiment Construction

[0034] Referring now to the representation of heat exchanger 12a according to the present invention Figures 4 to 6 . similar to reference image 3 As already described, the exchanger 12a comprises an annular portion 18 which also comprises a first fluid circuit 37 of oil comprising a plurality of first and second conduits 38, 40 substantially parallel to each other. . The first conduit 38 includes first and second portions 38b. The exchanger 12a also includes a second fluid thawing circuit 42 comprising a parallel first conduit 44 and a second conduit 46, the first conduit 44 comprising a first portion (not visible) and a second portion 44b.

[0035] The first conduit 38, 44 and the second conduit 40, 42 of the first loop 37 and the second loop 42 are very similar to the previous reference image 3What has been described, and differs only in that the first and second conduits are fluidly connected to each other at the circumferential ends of the heat exchanger. Also, wha...

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PUM

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Abstract

The invention relates to an annular heat exchanger (12a) having a longitudinal axis (L) for a turbomachine, intended, for example, to be supported by an annular ferrule of a housing of the turbomachine, comprising an annular one-piece part (18) having a first fluid circuit (37) comprising at least one first conduit (38) and at least one second conduit (40) extending in an annular manner, said heat exchanger being characterised in that the first conduit (38) and the second conduit (40) lead into a first cavity (48) formed on a first circumferential end (13) of said annular part (18), and in that it comprises detachable sealing means which are applied to said first end (13) and designed so as to allow a flow of fluid from the second conduit (38) into the first cavity (48) then into the first conduit (40).

Description

technical field [0001] The present invention relates to a heat exchanger, and more particularly to the cooling of oil in aircraft engines. Background technique [0002] figure 1 A turbine 10 with double flow is represented, said turbine comprising moving parts rubbing against other moving parts or fixed parts, this connection being for example a bearing. To avoid fractures due to friction-induced heating, the parts are sprayed with oil, which on the one hand allows the heating of the parts to be limited (or contained), and on the other hand lubricates them to facilitate sliding of the parts on top of each other. [0003] The oil is equipped with a heat exchanger (exactly, such as figure 2 shown in the circuit of the oil / air exchanger 12) having a matrix in the form of a curved tube for heat exchange, wherein the oil from the section is introduced The oil is then cooled. figure 2 The heat exchanger 12 shown in is an annular heat exchanger 12 mounted on the radially inne...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K3/115F01D25/12F02C7/14F28F9/22F28D1/04
CPCF01D25/12F02C7/14F02K3/115F28D1/0471F28D7/005F28F9/0246F28F9/028F28F9/0282F28F9/026F28F9/0268F28F2220/00F28F1/022F28F1/26F01D25/02Y02T50/60F05D2240/81F05D2260/213F05D2260/22141
Inventor 兰塞洛特·古伊劳斯泰凡·劳伊斯·卢西恩·奥伯格
Owner SAFRAN AIRCRAFT ENGINES SAS