Duct and method for directing a flow of air from an air-cooled device onboard an aircraft

Patent metadata

Field	Value
Publication number	US-2019256213-A1
Application number	US-201716309253-A
Country	US
Kind code	A1
Filing date	Jun 8, 2017
Priority date	Jun 14, 2016
Publication date	Aug 22, 2019
Grant date	—

Abstract

Ducts and methods for directing a flow of air from air-cooled devices onboard aircraft are disclosed. An exemplary method disclosed comprises: receiving air carrying heat extracted from the device, directing the air away from the device, and, discharging the air to at least one of an exterior of the aircraft and to an interior of the aircraft. A proportion of the air discharged to the exterior of the aircraft and to the interior of the aircraft is passively changed based on an operating condition such as the airspeed of the aircraft.

First claim

1 . A duct for directing a flow of air carrying heat extracted from an air-cooled device onboard an aircraft, the duct comprising:
an inlet configured to receive the flow of air; an exhaust outlet configured to discharge some of the air received at the inlet to an exterior of the aircraft; and an orifice disposed upstream of the exhaust outlet and configured to discharge some of the air received at the inlet to an interior of the aircraft, both the exhaust outlet and the orifice being simultaneously in fluid communication with the inlet to passively change a proportion of air being discharged through the exhaust outlet and through the orifice based on an operating condition of the aircraft.

2 . The duct as defined in claim 1 , wherein the orifice is disposed closer to the exhaust outlet than to the inlet.

3 . The duct as defined in claim 1 , wherein the orifice is disposed on a substantially straight portion of the duct.

4 . The duct as defined in claim 1 , wherein the duct has a curved center line and the orifice is disposed on a concave side of the duct.

5 . The duct as defined in claim 1 , wherein the duct is configured to be installed so that a portion of the duct adjacent the exhaust outlet is non-normal to a skin of the aircraft.

6 . The duct as defined in claim 1 , comprising a plurality of orifices configured to discharge some of the air received at the inlet to the interior of the aircraft.

7 . The duct as defined in claim 1 , wherein the inlet comprises a shroud configured to adapt to an end of an electric motor.

8 . The duct as defined in claim 1 , wherein the operating condition of the aircraft comprises an airspeed of the aircraft.

9 . An aircraft comprising the duct as defined in claim 1 .

10 . An equipment bay of an aircraft, the equipment bay comprising:
an aperture formed in a fuselage of the aircraft for permitting ambient air from an exterior of the aircraft to enter the equipment bay; an air-cooled device; and a duct for directing a flow of exhaust air carrying heat extracted from the device, the duct comprising:
an inlet configured to receive the flow of exhaust air;
an exhaust outlet configured to discharge some of the exhaust air received at the inlet to the exterior of the aircraft; and
an orifice disposed upstream of the exhaust outlet and configured to discharge some of the exhaust air received at the inlet to an interior of the aircraft, both the exhaust outlet and the orifice being simultaneously in fluid communication with the inlet to passively change a proportion of exhaust air being discharged through the exhaust outlet and through the orifice based on an operating condition of the aircraft.

11 . The equipment bay as defined in claim 10 , wherein the orifice is disposed closer to the exhaust outlet than to the inlet.

12 . The equipment bay as defined in claim 10 , wherein the orifice is disposed on a substantially straight portion of the duct.

13 . The equipment bay as defined in claim 10 , wherein the duct has a curved center line and the orifice is disposed on a concave side of the duct.

14 . The equipment bay as defined in claim 10 , wherein a portion of the duct adjacent the exhaust outlet is non-normal to a skin of the aircraft.

15 . The equipment bay as defined in claim 10 , wherein the duct comprises a plurality of orifices configured to discharge some of the air received at the inlet to the interior of the aircraft.

16 . The equipment bay as defined in claim 10 , wherein the air-cooled device comprises an electric motor and the inlet comprises a shroud configured to adapt to an end of the electric motor.

17 . The equipment bay as defined in claim 10 , wherein the air-cooled device comprises an integrated fan for driving the flow of exhaust air.

18 . The equipment bay as defined in claim 10 , wherein the operating condition of the aircraft comprises an airspeed of the aircraft.

19 . An aircraft comprising the equipment bay as defined in claim 1 .

20 . A method for directing a flow of air from an air-cooled device onboard an aircraft, the method comprising:
receiving air carrying heat extracted from the device; directing the air away from the device; and discharging the air to at least one of an exterior of the aircraft and to an interior of the aircraft where a proportion of the air discharged to the exterior of the aircraft and to the interior of the aircraft is passively changed based on an operating condition of the aircraft.

21 . The method as defined in claim 20 , comprising directing the air toward the exterior of the aircraft at least partially along a linear path and discharging the air to the interior of the aircraft in a direction transverse to the linear path.

22 . The method as defined in claim 21 , comprising discharging the air to the exterior of the aircraft substantially along the linear path.

23 . The method as defined in claim 20 , comprising directing the air toward the exterior of the aircraft at least partially along a curved path and discharging the air to the interior of the aircraft at a concave location of the curved path.

24 . The method as defined in claim 20 , comprising discharging the air to the interior of the aircraft at a plurality of locations.

25 . The method as defined in claim 20 , comprising discharging more air to the interior of the aircraft as the operating condition of the aircraft causes an increase in resistance to the air being discharged to the exterior of the aircraft.

26 . The method as defined in claim 20 , comprising discharging more air to the interior of the aircraft than to the exterior of the aircraft when the aircraft is in flight.

27 . The method as defined in claim 20 , comprising discharging more air to the exterior of the aircraft than to the interior of the aircraft when the aircraft is stationary.

28 . The method as defined in claim 20 , wherein the operating condition of the aircraft comprises an airspeed of the aircraft.

Assignees

• Bombardier Inc
• C Series Aircraft Lp

Inventors

• Wang Hongzhi

Classifications

• B64D13/00 Primary

  Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space · CPC title

• B64D2013/0614

  with subsystems for cooling avionics · CPC title

• B64D13/06 Primary

  the air being conditioned (pressurising B64D13/02) · CPC title

• B64D2013/0625

  comprising means for distribution effusion of conditioned air in the cabin · CPC title

• B64D2013/064

  comprising more than one system, e.g. dual systems · CPC title