Heat exchanger for aircraft engine

Patent metadata

Field	Value
Publication number	US-10156404-B2
Application number	US-201515507450-A
Country	US
Kind code	B2
Filing date	Oct 14, 2015
Priority date	Oct 21, 2014
Publication date	Dec 18, 2018
Grant date	Dec 18, 2018

Abstract

A heat exchanger for an aircraft engine that allows improvement in heat exchange ratio is provided. The heat exchanger ( 1 ) includes a plurality of heat dissipating fins ( 20, 30 ). The plurality of heat dissipating fins ( 20, 30 ) are arranged on at least one of a surface ( 2 ) and a surface ( 3 ). Each of the heat dissipating fins ( 20, 30 ) has a plate-like shape and has an inlet-side upper edge disposed on the side where a swirl flow (AF 1 ) flows in and an outlet-side upper edge disposed on the side opposite the inlet-side upper edge and on the side where the swirl flow (AF 1 ) flows out, and the inlet-side upper edge intersects the axis of rotation of a fan and extends along the direction in which the swirl flow (AF 1 ) flows at the inlet-side upper edge.

First claim

The invention claimed is:

1. A heat exchanger for an aircraft engine that is allowed to be disposed on a curved surface which is part of the aircraft engine and along which a swirl flow flows, the heat exchanger comprising:
a main body that has a plate-like shape curved along the curved surface, includes an internal channel through which a fluid is allowed to flow, and has a first surface so disposed as to face the curved surface and a second surface on a side opposite the first surface; and
a plurality of heat dissipating fins that are arranged on at least one of the first and second surfaces, wherein
the heat dissipating fin has a plate-like shape and has an inlet-side upper edge disposed on a side where the swirl flow flows in and an outlet-side upper edge disposed on a side opposite the inlet-side upper edge and on a side where the swirl flow flows out,
the inlet-side upper edge intersects an axis of rotation of a fan of the aircraft engine and extends along a direction in which the swirl flow flows at the inlet-side upper edge,
the plurality of heat dissipating fins include
first heat dissipating fins each so configured that at least the inlet-side upper edge intersects the axis of rotation at a first intersection angle, and
second heat dissipating fins arranged on the surface on which the first dissipating fins are arranged and each so configured that at least the inlet-side upper edge intersects the axis of rotation at an intersection angle different from the first intersection angle.

2. The heat exchanger according to claim 1 , wherein
the outlet-side upper edge intersects the axis of rotation of the fan and extends along the direction in which the swirl flow flows at the outlet-side upper edge.

3. The heat exchanger according to claim 1 , wherein
the first heat dissipating fins intersect the axis of rotation at the first intersection angle over the entire length thereof, and
the second heat dissipating fins intersect the axis of rotation at an intersection angle different from the first intersection angle over the entire length thereof.

4. The heat exchanger according to claim 1 , wherein
a portion including the inlet-side upper edge of the heat dissipating fin is bent.

5. The heat exchanger according to claim 2 , wherein
a portion including the inlet-side upper edge of the heat dissipating fin is bent, and a portion including the outlet-side upper edge of the heat dissipating fin is bent toward a side opposite the portion including the inlet-side upper edge.

6. The heat exchanger according to claim 1 , wherein
the plurality of heat dissipating fins are arranged on the first and second surfaces.

7. The heat exchanger according to claim 2 , wherein
the first heat dissipating fins intersect the axis of rotation at the first intersection angle over the entire length thereof, and
the second heat dissipating fins intersect the axis of rotation at an intersection angle different from the first intersection angle over the entire length thereof.

Assignees

• Sumitomo Precision Prod Co

Inventors

• Ueda Tatsuya

Classifications

• F28F1/34

  and extending obliquely (F28F1/38 takes precedence) · CPC title

• F28F1/32

  the means having portions engaging further tubular elements · CPC title

• F05D2250/71

  curved · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F28D2021/0021

  for aircrafts or cosmonautics · CPC title