Bypass duct heat exchanger with controlled fan

Patent metadata

Field	Value
Publication number	US-2016369706-A1
Application number	US-201514745606-A
Country	US
Kind code	A1
Filing date	Jun 22, 2015
Priority date	Jun 22, 2015
Publication date	Dec 22, 2016
Grant date	—

Abstract

A gas turbine engine comprises a main fan that delivers air into a bypass duct and into a core engine. A heat exchanger is positioned within the bypass duct and receives a fluid to be cooled from a component associated with the gas turbine engine. A heat exchanger fan is positioned to draw air across the heat exchanger and a control for the heat exchanger fan. The control is programmed to stop operation of the fan during certain conditions, and to drive the heat exchanger fan under other conditions. A method of forming a heat exchanger is also disclosed.

First claim

1 . A gas turbine engine comprising:
a main fan delivering air into a bypass duct and into a core engine; a heat exchanger positioned within said bypass duct, said heat exchanger receiving a fluid to be cooled from a component associated with the gas turbine engine; and a heat exchanger fan positioned to draw air across said heat exchanger and a control for said heat exchanger fan, said control being programmed to stop operation of the fan during certain conditions, and to drive the heat exchanger fan under other conditions.

2 . The gas turbine engine as set forth in claim 1 , wherein said control commands a motor to drive the heat exchanger fan under high heat load conditions.

3 . The gas turbine engine as set forth in claim 2 , wherein said high heat load conditions at least include takeoff of an associated aircraft.

4 . The gas turbine engine as set forth in claim 3 , wherein said control commanding said motor to turn off said heat exchanger fan under low heat load conditions.

5 . The gas turbine engine as set forth in claim 4 , wherein said low heat load conditions include a cruise condition of an associated aircraft.

6 . The gas turbine engine as set forth in claim 5 , wherein said motor is positioned within a space of a fairing such that it is out of a path of air downstream of said heat exchanger fan.

7 . The gas turbine engine as set forth in claim 6 , wherein said heat exchanger is formed through an additive manufacturing process.

8 . The gas turbine engine as set forth in claim 6 , wherein air downstream of said heat exchanger fan is delivered to mix back into a bypass airflow path.

9 . The gas turbine engine as set forth in claim 6 , wherein a shaft connects a rotor of said heat exchanger fan to said motor.

10 . The gas turbine engine as set forth in claim 1 , wherein said control commanding said motor to turn off said heat exchanger fan under low heat load conditions.

11 . The gas turbine engine as set forth in claim 10 , wherein said low heat load conditions include a cruise condition of an associated aircraft.

12 . The gas turbine engine as set forth in claim 11 , wherein said motor is positioned within a space of a fairing such that it is out of a path of air downstream of said heat exchanger fan.

13 . The gas turbine engine as set forth in claim 12 , wherein a shaft connects a rotor of said heat exchanger fan to said motor.

14 . The gas turbine engine as set forth in claim 11 , wherein said heat exchanger is formed through an additive manufacturing process.

15 . The gas turbine engine as set forth in claim 11 , wherein air downstream of said heat exchanger fan is delivered to mix back into a bypass airflow path.

16 . The gas turbine engine as set forth in claim 1 , wherein said motor is positioned within a space of a fairing such that it is out of a path of air downstream of said heat exchanger fan.

17 . The gas turbine engine as set forth in claim 16 , wherein a shaft connects a rotor of said heat exchanger fan to said motor.

18 . The gas turbine engine as set forth in claim 1 , wherein said heat exchanger is formed through an additive manufacturing process.

19 . The gas turbine engine as set forth in claim 11 , wherein air downstream of said heat exchanger fan is delivered to mix back into a bypass airflow path.

20 . A method of forming a heat exchanger comprising the steps of:
(a) determining an available space within a gas turbine engine for the heat exchanger; and (b) forming the heat exchanger to conform to said available space utilizing an additive manufacturing process.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Lord Wesley K
• Chandler Jesse M

Classifications

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F05D2230/31

  Layer deposition · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F02K3/115

  by means of indirect heat exchange · CPC title