Fluid cooler for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11530645-B2
Application number	US-202117177866-A
Country	US
Kind code	B2
Filing date	Feb 17, 2021
Priority date	Feb 17, 2021
Publication date	Dec 20, 2022
Grant date	Dec 20, 2022

Abstract

A fluid cooler for a gas turbine engine comprises an outer tube having an outer tube inlet at a first end of the fluid cooler and an outer tube outlet at a second end of the fluid cooler. A primary axis of the fluid cooler is defined within the outer tube between the first and second ends of the fluid cooler. A plurality of inner tubes extend within the outer tube between the first second ends of the fluid cooler. The inner tubes have a common inner tube inlet and a common inner tube outlet. The inner tubes extend helically about the primary axis. A first group of the inner tubes are disposed at a first radius from the primary axis and a second group of the inner tubes are disposed at a second radius from the primary axis, the second radius different from the first radius.

First claim

The invention claimed is:

1. A fluid cooler for a gas turbine engine, comprising:
an outer tube having an outer tube inlet at a first end of the fluid cooler and an outer tube outlet at a second end of the fluid cooler, a primary axis of the fluid cooler defined within the outer tube between the first end of the fluid cooler and the second end of the fluid cooler, the outer tube inlet fluidly coupled to an oil supply within the gas turbine engine; and
a plurality of inner tubes extending within the outer tube between the first end of the fluid cooler and the second end of the fluid cooler, the plurality of inner tubes having a common inner tube inlet and a common inner tube outlet, the plurality of inner tubes extending helically about the primary axis of the fluid cooler, a first group of the plurality of inner tubes disposed at a first radius from the primary axis of the fluid cooler and a second group of the plurality of inner tubes disposed at a second radius from the primary axis of the fluid cooler, the second radius different from the first radius.

2. The fluid cooler as defined in claim 1 , wherein the primary axis of the fluid cooler is a central longitudinal axis of the outer tube.

3. The fluid cooler as defined in claim 1 , wherein the outer tube helically extends about the primary axis, conforming to an outer shape of the plurality of inner tubes.

4. The fluid cooler as defined in claim 1 , wherein the common inner tube inlet is at the second end of the fluid cooler and the common inner tube outlet is at the first end of the fluid cooler.

5. The fluid cooler as defined in claim 1 , wherein a pitch of one or more of the plurality of inner tubes varies along a length of the fluid cooler between the first end and the second end.

6. The fluid cooler as defined in claim 1 , wherein a taper angle of one or more of the plurality of inner tubes varies along a length of the fluid cooler.

7. The fluid cooler as defined in claim 1 , wherein the outer tube is a cylindrical outer tube.

8. The fluid cooler as defined in claim 1 , wherein the plurality of inner tubes include circular cross-sections.

9. The fluid cooler as defined in claim 1 , wherein the common inner tube inlet is fluidly coupled to an air supply within the gas turbine engine.

10. The fluid cooler as defined in claim 1 , wherein the common inner tube outlet is fluidly coupled to a compressor section within the gas turbine engine.

11. The fluid cooler as defined in claim 1 , wherein the outer tube inlet and the outer tube outlet define respective inlet and outlet axis which are oriented in a same direction on an outer surface of the outer tube, the inlet and outlet axis intersecting the primary axis of the fluid cooler.

12. A gas turbine engine comprising:
a casing of the gas turbine engine;
a compressor section within the casing;
an air supply;
an oil supply; and
a fluid cooler mounted outside the casing, comprising;
an outer tube having an outer tube inlet fluidly coupled to the oil supply at a first end of the fluid cooler and an outer tube outlet at a second end of the fluid cooler, a primary axis of the fluid cooler defined within the outer tube between the first end of the fluid cooler and the second end of the fluid cooler; and
a plurality of inner tubes extending within the outer tube between the first end of the fluid cooler and the second end of the fluid cooler, the plurality of inner tubes having a common inner tube inlet fluidly coupled to the air supply and a common inner tube outlet fluidly coupled to the compressor section, the plurality of inner tubes extending helically about the primary axis of the fluid cooler, a first group of the plurality of inner tubes disposed at a first radius from the primary axis of the fluid cooler and a second group of the plurality of inner tubes disposed at a second radius from the primary axis of the fluid cooler.

13. The gas turbine engine as defined in claim 12 , wherein the primary axis of the fluid cooler is a central longitudinal axis of the outer tube.

14. The gas turbine engine as defined in claim 12 , wherein the outer tube helically extends about the primary axis, conforming to an outer shape of the plurality of inner tubes.

15. The gas turbine engine as defined in claim 12 , further comprising a nacelle surrounding the casing, wherein the fluid cooler is mounted between the nacelle and the casing.

16. The gas turbine engine as defined in claim 12 , wherein a pitch of one or more of the plurality of inner tubes varies along a length of the fluid cooler.

17. The gas turbine engine as defined in claim 12 , wherein a taper angle of one or more of the plurality of inner tubes varies along a length of the fluid cooler.

18. The gas turbine engine as defined in claim 12 wherein the plurality of inner tubes include circular cross-sections.

19. The gas turbine engine as defined in claim 12 , further comprising a second fluid cooler fluidly coupled to the fluid cooler in series.

Assignees

• Pratt & Whitney Canada

Inventors

• Nicolinco Constantin
• Naccache Gabriel

Classifications

• F28D7/10

  the conduits being arranged one within the other, e.g. concentrically {(multiple wall tubes for leak detection F28F1/003)} · CPC title

• F28F9/00

  Casings; Header boxes; Auxiliary supports for elements; Auxiliary members within casings · CPC title

• F28D2021/0026

  for combustion engines, e.g. for gas turbines or for Stirling engines · CPC title

• F28D7/0083

  with units having particular arrangement relative to a supplementary heat exchange medium, e.g. with interleaved units or with adjacent units arranged in common flow of supplementary heat exchange medium · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title