Heat exchange module for a turbine engine

Patent metadata

Field	Value
Publication number	US-11149644-B2
Application number	US-201916360329-A
Country	US
Kind code	B2
Filing date	Mar 21, 2019
Priority date	Sep 28, 2012
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.

First claim

What is claimed is:

1. A turbine engine with an axial centerline, comprising:
a heat exchange module including a duct and a heat exchanger;
the duct including a plurality of duct walls and a duct flowpath extending radially between the plurality of duct walls, the duct flowpath extending axially along the axial centerline and through the duct between a first duct end of the duct and a second duct end of the duct;
wherein the heat exchanger is configured to pivot substantially ninety degrees within the duct flowpath between a deployed position and a stowed position.

2. The turbine engine of claim 1 , wherein the heat exchanger has an arcuate geometry.

3. The turbine engine of claim 1 , wherein the heat exchanger has a rectangular geometry.

4. The turbine engine of claim 3 , wherein at least a portion of a first duct wall of the plurality of duct walls has a polygonal cross-sectional geometry.

5. The turbine engine of claim 4 , wherein
the first duct wall of the plurality of duct walls includes a transition segment that extends axially from the first duct end to a heat exchanger segment of the first duct wall;
the heat exchanger segment is the portion of the first duct wall having the polygonal cross-sectional geometry; and
the transition segment has a cross-sectional geometry that transitions from a circular cross-sectional geometry at the first duct end to the polygonal cross-sectional geometry at the heat exchanger segment.

6. The turbine engine of claim 5 , wherein
the first duct wall of the plurality of duct walls further includes a second transition segment that extends axially from the second duct end to the heat exchanger segment; and
the second transition segment has a cross-sectional geometry that transitions from a circular cross-sectional geometry at the second duct end to the polygonal cross-sectional geometry at the heat exchanger segment.

7. The turbine engine of claim 4 , wherein at least a portion of a second duct wall of the plurality of duct walls has a polygonal cross-sectional geometry.

8. The turbine engine of claim 1 , further comprising an actuator that moves the heat exchanger between the deployed position and the stowed position.

9. The turbine engine of claim 1 , further comprising:
a baffle arranged circumferentially between the heat exchanger and a second heat exchanger;
wherein the heat exchange module further includes the second heat exchanger, and the second heat exchanger is arranged within the duct flowpath.

10. The turbine engine of claim 1 , wherein
the heat exchange module further includes a second heat exchanger arranged within the duct flowpath; and
the second heat exchanger is configured to pivot within the duct flowpath between a deployed position and a stowed position.

11. The turbine engine of claim 1 , further comprising a first case, a second case and a third case, wherein
a central core flowpath is formed within the first case;
a first bypass flowpath is formed radially between the first case and the second case; and
a secondary bypass flowpath is formed radially between the second case and the third case.

12. A turbine engine with an axial centerline, comprising:
a heat exchange module including a duct and a heat exchanger;
the duct including a plurality of duct walls and a duct flowpath extending radially between the plurality of duct walls; and
the duct flowpath extending axially along the axial centerline and through the duct between a first duct end of the duct and a second duct end of the duct;
wherein the heat exchanger is configured to pivot ninety degrees about a pivot axis within the duct flowpath between a deployed position and a stowed position; and
wherein the pivot axis extends radially relative to the axial centerline.

13. The turbine engine of claim 12 , wherein the pivot axis is perpendicular to the axial centerline.

14. The turbine engine of claim 12 , wherein the heat exchanger has a rectangular geometry.

15. The turbine engine of claim 14 , wherein at least a portion of a first duct wall of the plurality of duct walls has a polygonal cross-sectional geometry.

16. The turbine engine of claim 15 , wherein
the first duct wall of the plurality of duct walls includes a transition segment that extends axially from the first duct end to a heat exchanger segment of the first duct wall;
the heat exchanger segment is the portion of the first duct wall having the polygonal cross-sectional geometry; and
the transition segment has a cross-sectional geometry that transitions from a circular cross-sectional geometry at the first duct end to the polygonal cross-sectional geometry at the heat exchanger segment.

17. The turbine engine of claim 16 , wherein
the first duct wall of the plurality of duct walls further includes a second transition segment that extends axially from the second duct end to the heat exchanger segment; and
the second transition segment has a cross-sectional geometry that transitions from a circular cross-sectional geometry at the second duct end to the polygonal cross-sectional geometry at the heat exchanger segment.

18. A turbine engine with an axial centerline, comprising:
a heat exchange module including a duct and a heat exchanger;
the duct including a plurality of duct walls and a duct flowpath extending radially between the plurality of duct walls; and
the duct flowpath extending axially along the axial centerline and through the duct between a first duct end of the duct and a second duct end of the duct;
wherein the heat exchanger is configured to pivot ninety degrees about a pivot axis within the duct flowpath between a deployed position and a stowed position; and
wherein the heat exchanger is completely within the duct flowpath in both the deployed position and the stowed position.

Assignees

• Raytheon Tech Corp

Inventors

• Schwarz Frederick M
• Schmitz John T

Classifications

• F02C7/12 Primary

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F02K3/105

  Heating the by-pass flow · CPC title

• F02K3/077

  the plant being of the multiple flow type, i.e. having three or more flows · CPC title

• F05D2260/213

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

• F01D25/08

  Cooling (of machines or engines in general F01P); Heating; Heat-insulation (of blade-carrying members, of blades F01D5/00) · CPC title