Heat Exchanger with Precision Manufactured Flow Passages

Patent metadata

Field	Value
Publication number	US-2017335689-A1
Application number	US-201615156367-A
Country	US
Kind code	A1
Filing date	May 17, 2016
Priority date	May 17, 2016
Publication date	Nov 23, 2017
Grant date	—

Abstract

A heat exchanger has a first plurality of passages extending in a first direction and to receive a first fluid and a second plurality of passages extending in a second direction, and to receive a second fluid, and the first plurality of passages being formed across a cross-sectional face of the heat exchanger, and there being distinct combined flow cross-sectional areas of the first plurality of passages in different locations across the cross-sectional face of the heat exchanger. A gas turbine engine and a method of forming a heat exchanger are also disclosed.

First claim

1 . A heat exchanger comprising:
a first plurality of passages extending in a first direction and to receive a first fluid and a second plurality of passages extending in a second direction, and to receive a second fluid, and said first plurality of passages being formed across a cross-sectional face of the heat exchanger, and there being distinct combined flow cross-sectional areas of said first plurality of passages in different locations across said cross-sectional face of said heat exchanger.

2 . The heat exchanger as set forth in claim 1 , wherein said first and second directions are generally perpendicular to each other.

3 . The heat exchanger as set forth in claim 1 , wherein a corner is defined at an upstream end of said first set of passages and said second set of passages, and said flow cross-sectional area of said first and second passages being less adjacent said corner than at locations spaced from said corner.

4 . The heat exchanger as set forth in claim 3 , wherein a shape of said first flow passages adjacent said corner is distinct from a shape of said passages spaced from said corner.

5 . The heat exchanger as set forth in claim 4 , wherein a cross-sectional area of said passages in said first plurality of passages adjacent to said corner is less than a cross-sectional area of said passages in said first plurality of passages spaced further from said corner.

6 . The heat exchanger as set forth in claim 5 , wherein said passages in said first plurality of passages spaced from said corner include a polygonal shape.

7 . The heat exchanger as set forth in claim 6 , wherein said passages in said first set of passages adjacent said corner having a cylindrical shape.

8 . The heat exchanger as set forth in claim 3 , wherein a cross-sectional area of said passages in said first plurality of passages adjacent to said corner is less than a cross-sectional area of said passages in said first plurality of passages spaced further from said corner.

9 . The heat exchanger as set forth in claim 1 , wherein said second plurality of passages being formed across a cross-sectional face of the heat exchanger and there also being distinct combined flow cross-sectional areas of said second plurality of passages in different locations across said cross-sectional face of said heat exchanger.

10 . A gas turbine engine comprising:
a compressor and a turbine section; and a heat exchanger to cool air being delivered to said turbine section for cooling components in said turbine section, the heat exchanger including a first plurality of passages extending in a first direction and to receive a first fluid and a second plurality of passages extending in a second direction, and to receive a second fluid, and said first plurality of passages being formed across a cross-sectional face of the heat exchanger, and there being distinct combined flow cross-sectional areas of said first cooling passages in different locations across said cross-sectional face of said heat exchanger.

11 . The gas turbine engine as set forth in claim 10 , wherein said first and second directions are generally perpendicular to each other.

12 . The gas turbine engine as set forth in claim 10 , wherein a corner is defined at an upstream end of said first set of passages and said second set of passages, and said combined flow cross-sectional area of said first and second passages being less adjacent said corner than at locations spaced from said corner.

13 . The gas turbine engine as set forth in claim 12 , wherein a shape of said first flow passages adjacent said corner is distinct from a shape of said passages spaced from said corner.

14 . The gas turbine engine as set forth in claim 12 , wherein a cross-sectional area of said passages in said first set of passages adjacent to said corner is less than a cross-sectional area of said passages and said first set of passages spaced further from said corner.

15 . The gas turbine engine as set forth in claim 14 , wherein said passages in said first plurality of passages spaced from said corner include a polygonal shape.

16 . The gas turbine engine as set forth in claim 15 , wherein said passages in said first set of passages adjacent said corner having a cylindrical shape.

17 . The gas turbine engine as set forth in claim 10 , wherein said second plurality of passages being formed across a cross-sectional face of the heat exchanger and there being distinct combined flow cross-sectional areas of said second plurality of passages in different locations across said cross-sectional face of said heat exchanger.

18 . A method of forming a heat exchanger comprising:
forming a first plurality of passages extending in a first direction and to receive a first fluid and forming a second plurality of passages extending in a second direction, and to receive a second fluid, and said first plurality of passages being formed across a cross-sectional face of the heat exchanger, and there being distinct combined flow cross-sectional areas of said first cooling passages in different locations across said cross-sectional face of said heat exchanger.

19 . The method as set forth in claim 18 , wherein said first and second plurality of passages are formed utilizing refractory metal cores.

20 . The method as set forth in claim 18 , wherein said heat exchanger is formed using an additive manufacturing process.

Assignees

• United Technologies Corp

Inventors

• Golan John W
• Schwarz Frederick M

Classifications

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F28F13/08

  by varying the cross-section of the flow channels · CPC title

• F01D5/021

  for flow machines or engines with only one axial stage (for more than one stage F01D5/06) · CPC title

• F04D19/002

  Axial flow fans · CPC title

• F28D7/1615

  the conduits being inside a casing and extending at an angle to the longitudinal axis of the casing; the conduits crossing the conduit for the other heat exchange medium · CPC title