Entrainment heat exchanger

Patent metadata

Field	Value
Publication number	US-11168951-B2
Application number	US-201615210434-A
Country	US
Kind code	B2
Filing date	Jul 14, 2016
Priority date	Jul 14, 2016
Publication date	Nov 9, 2021
Grant date	Nov 9, 2021

Abstract

A heat exchanger apparatus includes: a shell extending over a flow length from an inlet at a upstream end to an outlet at a downstream end, and defining a first flowpath for a first fluid; a structure disposed within the shell defining a second flowpath for a second fluid; at least one secondary inlet in the shell disposed downstream from the upstream end; and a nozzle disposed downstream of the inlet.

First claim

What is claimed is:

1. A heat exchanger apparatus, comprising:
a shell extending over a flow length from an inlet at an upstream end to an outlet at a downstream end, and defining a first flowpath for a first fluid;
a structure disposed within the shell defining a second flowpath for a second fluid, the structure including a plurality of heat exchange elements spaced along the flow length, wherein the plurality of heat exchange elements are positioned in the first flowpath and communicate with the first fluid;
at least one secondary inlet formed in a surface of the shell disposed downstream from the upstream end, downstream of at least one of the plurality of heat exchange elements and upstream of at least one of the plurality of heat exchange elements;
a baffle disposed in the shell and extending from a first heat exchange element of the plurality of heat exchange elements to a second heat exchange element of the plurality of heat exchange elements across the at least one secondary inlet; and
a nozzle disposed downstream of the at least one secondary inlet, the baffle and the shell forming an area of reduction therebetween to define the nozzle.

2. The apparatus of claim 1 wherein the heat exchange elements are tubes.

3. The apparatus of claim 2 wherein the tubes are grouped into a plurality of bundles spaced along the flow length.

4. The apparatus of claim 1 wherein the shell has a characteristic dimension at the inlet, and an aspect ratio of the flow length divided by the characteristic dimension is unity or greater.

5. The apparatus of claim 1 wherein the nozzle is defined by spaced-apart walls of the shell.

6. The apparatus of claim 5 further comprising a centerbody disposed between the walls upstream of a throat of the nozzle.

7. The apparatus of claim 1 wherein the baffle is perforated.

8. The apparatus of claim 1 further comprising an outer housing which surrounds the shell such that a bypass duct is defined between the shell and the outer housing.

9. The apparatus of claim 1 further comprising a flow control apparatus operable to selectively control flow through the nozzle.

10. A heat exchanger apparatus for a gas turbine engine, comprising:
a shell extending over a flow length from an inlet at an upstream end to an outlet at a downstream end, and defining a first flowpath for a first fluid, wherein the shell has a characteristic dimension at the inlet, and an aspect ratio of the flow length divided by the characteristic dimension is unity or greater;
a plurality of tubes disposed within the shell extending traverse to the flow direction, and defining a second flowpath for a second fluid, wherein the plurality of tubes are grouped into a plurality of bundles spaced along the flow length;
at least one secondary inlet formed in a surface of the shell disposed downstream from the upstream end, downstream of at least one of the plurality of bundles, and upstream of at least one of the plurality of bundles;
a baffle disposed in the shell and extending from a first tube of the plurality of tubes to a second tube of the plurality of tubes across the at least one secondary inlet; and
a nozzle disposed downstream of the at least one secondary inlet, wherein a coolant flows through the at least one secondary inlet and through the nozzle without flowing over the plurality of bundles, the baffle and the shell forming an area of reduction therebetween to define the nozzle.

11. The apparatus of claim 10 wherein the nozzle is defined by spaced-apart walls of the shell.

12. The apparatus of claim 10 further comprising an outer housing which surrounds the shell such that a bypass duct is defined between the shell and the outer housing.

13. The apparatus of claim 10 wherein the inlets are disposed in fluid communication with a wall that defines a flowpath.

14. The apparatus of claim 13 wherein the flowpath is a fan bypass duct of a gas turbine engine.

15. A method of operating a heat exchanger, comprising:
flowing a primary flow of a first fluid at a first temperature through a shell that extends over a flow length from an inlet at a upstream end to an outlet at a downstream end;
flowing a second fluid at a second temperature different from the first temperature through a structure disposed within the shell, such that heat is transferred from one of the fluids to the other fluid, the structure including a plurality of heat exchange elements spaced along the flow length; and
entraining a secondary flow of a fluid into the shell through at least one secondary inlet formed in a surface of the shell disposed downstream from the upstream end, downstream of at least one of the plurality of heat exchange elements, and upstream of at least one of the plurality of heat exchange elements, a baffle disposed within the shell and extending from a first heat exchange element of the plurality of heat exchange elements to a second heat exchange element of the plurality of heat exchange elements across the at least one secondary inlet, a nozzle disposed downstream of the at least one secondary inlet, the baffle and the shell forming an area of reduction therebetween to define the nozzle, wherein the secondary flow of fluid mixes with a portion of the primary flow of the first fluid prior to flowing over at least one of the plurality of heat exchange elements, such that the at least one of the plurality of heat exchange elements receives both the primary flow and mixture of primary and secondary flows.

16. The method of claim 15 further comprising flowing the primary flow through the nozzle disposed downstream of the secondary inlet so as to provide a driving force for entraining the secondary flow.

17. The method of claim 16 further comprising modulating the secondary flow by selectively blocking flow through the nozzle.

18. The method of claim 15 further comprising entraining the secondary flow into the shell at multiple locations spaced along the flow length.

19. The method of claim 15 wherein the shell has a flow area, and an aspect ratio of the flow length divided by the flow area is unity or greater.

20. The method of claim 15 wherein the secondary flow is drawn from a boundary layer region of a third fluid at a third temperature flowing in a flowpath external to the shell.

Assignees

• Gen Electric

Inventors

• Rambo Jeffrey Douglas

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F28F2009/228

  Oblique partitions · CPC title

• 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

• F28F27/02

  for controlling the distribution of heat-exchange media between different channels ({static flow control means in header boxes F28F9/026}; arrangements of guide plates or guide vanes F28F9/22, F28F25/12) · CPC title