Contamination free reverse flow fitting

Patent metadata

Field	Value
Publication number	US-9764846-B2
Application number	US-201313856162-A
Country	US
Kind code	B2
Filing date	Apr 3, 2013
Priority date	Apr 3, 2013
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

A precooler for an aircraft engine system includes a precooler core and a precooler inlet to direct a compressor bleed flow into the precooler core to cool the compressor bleed flow. The precooler further includes a precooler outlet to direct the compressor bleed flow from the precooler to a selected component of the aircraft engine system and a precooler bleed port through which a portion of the compressor bleed flow is diverted to a secondary component of the aircraft engine system. The precooler bleed port is oriented such that flow entering the precooler bleed port must substantially reverse direction from a direction of the compressor bleed flow through the precooler.

First claim

The invention claimed is:

1. A precooler for an aircraft engine system comprising:
a precooler core;
a precooler inlet to direct a compressor bleed flow into the precooler core to cool the compressor bleed flow;
a precooler outlet to direct the compressor bleed flow from the precooler to a selected component of the aircraft engine system and out of the precooler;
a heat exchanger medium inlet;
a heat exchanger medium outlet to direct a heat exchanger medium out of the precooler; and
a precooler bleed port through which a portion of the compressor bleed flow is diverted to a secondary component of the aircraft engine system through a precooler bleed port outlet that is separate from the heat exchanger medium outlet and separate from the precooler outlet, wherein all of the flow diverted through the precooler bleed port exits the precooler through the bleed port outlet;
wherein the precooler bleed port is oriented such that flow entering the precooler bleed port must substantially reverse direction from a direction of the compressor bleed flow through the precooler.

2. The precooler of claim 1 , further comprising a precooler outlet header in which the precooler bleed port and the precooler outlet are disposed, the precooler outlet header joined to the precooler core at a planar mating face.

3. The precooler of claim 2 , wherein the precooler bleed port is disposed between the precooler outlet and the mating face.

4. The precooler of claim 2 , wherein a precooler bleed port axis is orientated at a bleed port angle to the mating face such that the flow through the precooler bleed port is toward the mating face.

5. The precooler of claim 4 , wherein the bleed port angle is in the range of 10 to 50 degrees.

6. The precooler of claim 5 , wherein the bleed port angle is 22 degrees.

7. The precooler of claim 4 , wherein a compressor bleed outlet angle defined between between a projection of the precooler bleed port axis onto the mating face 52 and a projection of a precooler outlet axis onto the mating face is in the range of 90 to 180 degrees.

8. The precooler of claim 7 , wherein the compressor bleed outlet angle is 103.5 degrees.

9. An aircraft engine system comprising:
a compressor;
a compressor bleed port to allow for extraction of a compressor bleed flow from the compressor;
a precooler operably connected to the compressor including:
a precooler core;
a precooler inlet to direct the compressor bleed flow into the precooler core to cool the compressor bleed flow;
a precooler outlet to direct the compressor bleed flow from the precooler to a selected component of the aircraft engine system and out of the precooler;
a heat exchanger medium inlet;
a heat exchanger medium outlet to direct a heat exchanger medium out of the precooler; and
a precooler bleed port through which a portion of the compressor bleed flow is diverted to a secondary component of the aircraft engine system through a precooler bleed port outlet that is separate from the heat exchanger medium outlet and separate from the precooler outlet, wherein all of the flow diverted through the precooler bleed port exits the precooler through bleed port outlet;
wherein the precooler bleed port is oriented such that flow entering the oriented such that flow entering the precooler bleed port must substantially reverse direction from a direction of the compressor bleed flow through the precooler.

10. The system of claim 9 , further comprising a precooler outlet header in which the precooler bleed port and the precooler outlet are disposed, the precooler outlet header joined to the precooler core at a planar mating face.

11. The system of claim 10 , wherein the precooler bleed port is disposed between the precooler outlet and the mating face.

12. The system of claim 10 , wherein a precooler bleed port axis is orientated at a bleed port angle to the mating face such that the flow through the precooler bleed port is toward the mating face.

13. The system of claim 12 , wherein the bleed port angle is in the range of 10 to 50 degrees.

14. The system of claim 13 , wherein the bleed port angle is 22 degrees.

15. The system of claim 12 , wherein a compressor bleed outlet angle defined between a projection of the precooler bleed port axis onto the mating face 52 and a projection of a precooler outlet axis onto the mating face is in the range of 90 to 180 degrees.

16. The system of claim 15 , wherein the compressor bleed outlet angle is 103.5 degrees.

17. The system of claim 9 , wherein the selected component is an engine control system.

18. The system of claim 9 , wherein the secondary component is a fan air torque motor.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Bizzarro Peter

Classifications

• F28F9/02

  Header boxes; End plates · CPC title

• F28F19/00

  Preventing the formation of deposits or corrosion, e.g. by using filters {or scrapers} · CPC title

• F02C7/143

  before or between the compressor stages · CPC title

• F28D2021/0021

  for aircrafts or cosmonautics · CPC title

• F28F2250/06

  Derivation channels, e.g. bypass · CPC title