IP Library Granted Patent US 10,539,378
Granted Patent B2
US 10,539,378 · App. 15/730,782 · Granted Jan 21, 2020

Heat exchanger

Inventors: Jacob Diffey (London, GB); John Marsh (Wolverhampton, GB); James Green (Worcestershire, GB); Chris McNab (Staffordshire, GB)
Assignee: HS MARSTON AEROSPACE LTD.
F28F13/125F28F9/028F28F9/0265F28F9/0268F28F2250/02
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Quick Facts
Patent No.
US 10,539,378
App. No.
15/730,782
Granted
Jan 21, 2020
Kind
B2
Abstract

A heat exchanger comprises a conduit defining an inlet flow path for a fluid; a heat exchanger matrix disposed to receive a flow from the inlet flow path; and a swirler disposed within the conduit and arranged to improve dispersion of a flow from the inlet flow path over the heat exchanger matrix.

Claims (20)

1. A heat exchanger comprising:

a conduit defining an inlet flow path for a fluid;

a heat exchanger matrix disposed to receive a flow from the inlet flow path; and

a swirler disposed within the conduit and arranged to improve dispersion of a flow from the inlet flow path over the heat exchanger matrix;

wherein the heat exchanger matrix has a polygonal cross section in the direction of the flow path, and wherein the swirler is arranged to direct flow streams from the flow path towards each of the corners of the polygonal cross section;

wherein the swirler comprises a plurality of blades; and

wherein the blades wind helically around more than 90 degrees and are disposed across an entire cross-section of the flow path so that no unobstructed path exists for fluid flow directly through the swirler along the conduit.

2. A heat exchanger as claimed in claim 1 , wherein the plurality of blades define a helical flow path within the conduit.

3. A heat exchanger as claimed in claim 1 , wherein the blades are separated from each other by equal angles.

4. A heat exchanger as claimed in claim 1 , wherein the heat exchanger matrix has a quadrilateral cross section in the direction of the flow path, and wherein the swirler comprises four blades arranged to direct flow from the flow path towards each of the four corners of the cross section.

5. A heat exchanger as claimed in claim 1 , wherein the heat exchanger matrix comprises an array of channels providing multiple flow paths for the fluid in heat exchange with another fluid, and the swirler is arranged to disperse the flow from the inlet flow path across the array of channels.

6. A heat exchanger as claimed in claim 1 , wherein the swirler comprises a sleeve portion providing a friction fit within the conduit.

7. A heat exchanger as claimed in claim 1 , wherein the heat exchanger is arranged to carry a fluid flow with a speed of greater than 300 m/s via the conduit.

8. A heat exchanger as claimed in claim 1 , wherein the swirler is disposed proximate an end of the conduit.

9. A heat exchanger as claimed in claim 1 , wherein the swirler has been formed by additive manufacturing.

10. An aircraft in combination with a heat exchanger as claimed in claim 1 .

11. A method for distributing flow in a heat exchanger that includes a conduit defining an inlet flow path for a fluid, a heat exchanger matrix disposed to receive a flow from the inlet flow path, and a swirler disposed within the conduit and arranged to improve dispersion of a flow from the inlet flow path over the heat exchanger matrix, the method comprising:

using the swirler to disperse the flow from the inlet flow path over the heat exchanger matrix,

wherein the heat exchanger matrix has a polygonal cross section in the direction of the flow path, and

wherein using the swirler includes directing flow streams from the flow path towards each of the corners of the polygonal cross section and wherein the swirler comprises a plurality of blades and wherein wind helically around more than 90 degrees and are disposed across an entire cross-section of the flow path so that no unobstructed path exists for fluid flow directly through the swirler along the conduit.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Oct 13, 2017
From: DIFFEY, JACOB; MARSH, JOHN; GREEN, JAMES; MCNAB, CHRIS
To: HS MARSTON AEROSPACE LIMITED
Reel/Frame 043860/0190 →
Priority Claims (1)
EP 16193635 · Oct 13, 2016 · regional
Continuity (1)
Related Publication 20180106561A1 · Apr 19, 2018
Cited By (1)
US 12,235,024