Heat exchange module for a turbine engine

Patent metadata

Field	Value
Publication number	US-10240531-B2
Application number	US-201715412729-A
Country	US
Kind code	B2
Filing date	Jan 23, 2017
Priority date	Sep 28, 2012
Publication date	Mar 26, 2019
Grant date	Mar 26, 2019

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 that includes:
a duct including a duct flowpath defined radially between a plurality of concentric duct walls, the duct flowpath extending along the axial centerline and through the duct between a first duct end and a second duct end; and
a plurality of heat exchangers arranged circumferentially around the axial centerline,
wherein each heat exchanger of the plurality of heat exchangers is configured to pivot substantially 90 degrees between a deployed position extending radially across the duct flowpath and a stowed position;

the turbine engine including a first case, a second case, and a third case, wherein a central core flowpath is defined by the first case;
wherein a primary bypass flowpath is defined radially between the first case and the second case;
wherein a secondary bypass flowpath is defined radially between the second case and the third case; and
wherein the duct flowpath is fluidly coupled inline with the secondary bypass flowpath.

2. A turbine engine with an axial centerline, comprising:
a heat exchange module that includes:
a duct including a duct flowpath defined radially between a plurality of concentric duct walls, the duct flowpath extending along the axial centerline and through the duct between a first duct end and a second duct end; and
a plurality of heat exchangers arranged circumferentially around the axial centerline;

the turbine engine including a first case, a second case, and a third case, wherein a central core flowpath is defined by the first case;
wherein a primary bypass flowpath is defined radially between the first case and the second case;
wherein a secondary bypass flowpath is defined radially between the second case and the third case; and
wherein the duct flowpath is fluidly coupled inline with the secondary bypass flowpath, and each heat exchanger of the plurality of heat exchangers is configured to pivot substantially 90 degrees within the duct flowpath between a deployed position and a stowed position.

3. The turbine engine of claim 2 , wherein a first heat exchanger of the plurality of heat exchangers has an arcuate geometry.

4. The turbine engine of claim 2 , wherein a first heat exchanger of the plurality of heat exchangers has a rectangular geometry.

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

6. The turbine engine of claim 5 , 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.

7. The turbine engine of claim 6 , 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.

8. The turbine engine of claim 5 , wherein at least a portion of a second duct wall of the plurality of duct walls has a polygonal cross-sectional geometry.

9. The turbine engine of claim 2 , further comprising an actuator that moves a first heat exchanger of the plurality of heat exchangers between the deployed position and the stowed position.

10. The turbine engine of claim 2 , further comprising a baffle arranged circumferentially between a first heat exchanger and a second heat exchanger of the plurality of heat exchangers.

11. A turbine engine with an axial centerline, comprising:
a core comprising a compressor section, a combustor section and a turbine section;
a first case that defines a central core flowpath through the core;
a second case that extends circumferentially around the first case such that a primary bypass flowpath is defined radially between the first case and the second case;
a third case that extends circumferentially around the second case such that a secondary bypass flowpath is defined radially between the second case and the third case;
a heat exchange module comprising:
a duct including a substantially annular duct flowpath defined radially between a plurality of duct walls, the substantially annular duct flowpath extending axially through the duct and fluidly coupled inline with the secondary bypass flowpath; and
a plurality of heat exchangers arranged circumferentially around the axial centerline, wherein each heat exchanger of the plurality of heat exchangers is configured to pivot substantially 90 degrees within the substantially annular duct flowpath between a deployed position and a stowed position.

12. The turbine engine of claim 11 , wherein a first heat exchanger of the plurality of heat exchangers has a rectangular geometry; and at least a portion of a first duct wall of the plurality of duct walls has a polygonal cross-sectional geometry.

13. The turbine engine of claim 12 , wherein the first duct wall of the plurality of duct walls includes a transition segment that extends axially from a 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.

14. The turbine engine of claim 13 , wherein the first duct wall of the plurality of duct walls further includes a second transition segment that extends axially from a 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.

15. The turbine engine of claim 11 , further comprising: an actuator that moves a first heat exchanger of the plurality of heat exchangers between the deployed position and the stowed position.

Assignees

• United Technologies Corp

Inventors

• Schwarz Frederick M
• Schmitz John T

Classifications

• B64D33/10

  Radiator arrangement · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F02C7/12 Primary

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

• B64D33/08

  of power plant cooling systems · 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