Gas turbine engine fluid cooling systems and methods of assembling the same

Patent metadata

Field	Value
Publication number	US-10323540-B2
Application number	US-201514960800-A
Country	US
Kind code	B2
Filing date	Dec 7, 2015
Priority date	Dec 7, 2015
Publication date	Jun 18, 2019
Grant date	Jun 18, 2019

Abstract

A fluid cooling system for use in a gas turbine engine including a fan casing circumscribing a core gas turbine engine includes a heat source configured to transfer heat to a heat transfer fluid and a primary heat exchanger coupled in flow communication with the heat source. The primary heat exchanger is configured to channel the heat transfer fluid therethrough and is coupled to the fan casing. The fluid cooling system also includes a secondary heat exchanger coupled in flow communication with the primary heat exchanger. The secondary heat exchanger is configured to channel the heat transfer fluid therethrough and is coupled to the core gas turbine engine. The fluid cooling system also includes a bypass mechanism coupled in flow communication with the secondary heat exchanger. The bypass mechanism is selectively moveable based on a temperature of a fluid medium to control a cooling airflow through the secondary heat exchanger.

First claim

What is claimed is:

1. A fluid cooling system for use in a gas turbine engine including a core section of the gas turbine engine having an axis of rotation and a fan casing substantially circumscribing the core section of the gas turbine engine, said fluid cooling system comprising:
a heat source configured to transfer heat to a heat transfer fluid;
a primary heat exchanger coupled in flow communication with said heat source and configured to channel the heat transfer fluid therethrough, said primary heat exchanger coupled to the fan casing;
a secondary heat exchanger coupled in flow communication with said primary heat exchanger and configured to channel the heat transfer fluid therethrough, said secondary heat exchanger located within the core section of the gas turbine engine;
a bypass mechanism coupled in flow communication with said secondary heat exchanger, said bypass mechanism being selectively moveable based on a temperature of an ambient airflow to control a cooling airflow through said secondary heat exchanger, said secondary heat exchanger being exposed to the cooling airflow in response to the temperature of the ambient airflow being above a threshold temperature of at least 105.degree. F. (40.5.degree. C.).

2. The fluid cooling system in accordance with claim 1 , wherein said primary heat exchanger comprises a surface cooler coupled within a recess located in a radially interior surface of the fan casing, and wherein said secondary heat exchanger comprises a brick cooler.

3. The fluid cooling system in accordance with claim 1 , wherein said primary heat exchanger comprises a surface cooler sized for operating conditions including standard operation and hot day operation.

4. The fluid cooling system in accordance with claim 1 , wherein said bypass mechanism comprises a flap that is selectively moveable between a first position and a second position based on the temperature of the ambient airflow.

5. The fluid cooling system in accordance with claim 4 , wherein said bypass mechanism exposes said secondary heat exchanger to the cooling airflow in the first position and isolates said secondary heat exchanger from the cooling airflow in the second position.

6. The fluid cooling system in accordance with claim 5 , wherein said bypass mechanism is in the first position when the temperature of the ambient airflow is above the threshold temperature, and wherein said bypass mechanism is in the second position when the temperature of the ambient airflow is below the threshold temperature.

7. The fluid cooling system in accordance with claim 1 , further comprising a sensor configured to determine the temperature of the ambient airflow.

8. The fluid cooling system in accordance with claim 1 , further comprising a fuel cooled heat exchanger coupled in flow communication with said heat source, said primary heat exchanger, and said secondary heat exchanger.

9. A method of operating a gas turbine engine having a core section and a fan casing substantially circumscribing the core section, said method comprising:
transferring heat from a heat source to a heat transfer fluid;
channeling the heat transfer fluid through a primary heat exchanger coupled in flow communication with said heat source, said primary heat exchanger coupled to the fan casing;
channeling the heat transfer fluid through a secondary heat exchanger coupled in flow communication with the primary heat exchanger, said secondary heat exchanger located within the core section of the gas turbine engine;
determining a temperature of an ambient airflow; and
controlling a bypass mechanism, coupled in flow communication with the secondary heat exchanger, to selectively expose the secondary heat exchanger to a cooling airflow in response to the temperature of the ambient airflow being above a threshold temperature of at least 105.degree. F. (40.5.degree. C.).

10. The method according to claim 9 , wherein controlling the bypass mechanism comprises selectively moving a flap between a first position and a second position based on the temperature of the ambient airflow.

11. The method according to claim 10 , wherein controlling the bypass mechanism comprises exposing the secondary heat exchanger to the cooling airflow when the flap is in the first position and isolating the secondary heat exchanger from the cooling airflow when the flap is in the second position.

12. The method according to claim 11 , wherein exposing the secondary heat exchanger to the cooling airflow comprises moving the flap to the first position when the determined ambient airflow temperature is greater than the threshold temperature, and wherein the isolating the secondary heat exchanger from the cooling airflow comprises moving the flap to the second position when the determined ambient airflow temperature is less than the threshold temperature.

13. The method according to claim 9 , wherein channeling the heat transfer fluid through the primary heat exchanger comprises channeling the heat transfer fluid through a surface cooler.

14. The method according to claim 9 , wherein controlling the bypass mechanism to selectively position the secondary heat exchanger in the cooling airflow comprises controlling a bypass flap to selectively channel the cooling airflow through a brick cooler.

Assignees

• Gen Electric

Inventors

• Sennoun Mohammed El Hacin

Classifications

• F02K3/06 Primary

  with front fan · CPC title

• F05D2270/07

  to improve fuel economy · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/213

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

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title