Inverse modulation of secondary bleed

Patent metadata

Field	Value
Publication number	US-11746702-B2
Application number	US-202117558907-A
Country	US
Kind code	B2
Filing date	Dec 22, 2021
Priority date	Jun 19, 2015
Publication date	Sep 5, 2023
Grant date	Sep 5, 2023

Abstract

A cooling arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, an offtake duct that has an offtake inlet coupled to a cooling source, the offtake duct defining a throat, and a valve downstream of the throat. The valve couples the offtake duct and a first cooling flow path. The valve is operable to selectively modulate flow through the offtake duct. A bleed passage includes a bleed inlet coupling the offtake duct and a second cooling flow path. The bleed inlet is defined at a location between the offtake inlet and the throat, inclusive. A method of cooling a propulsion system is also disclosed.

First claim

What is claimed is:

1. A method of cooling a propulsion system, comprising:
communicating airflow to an offtake inlet of an offtake duct, the offtake duct defining a throat;
modulating the airflow between the offtake duct and a first cooling flow path; and
diverting a portion of the airflow from the offtake duct to a bleed passage in response to the step of modulating the airflow, the bleed passage including a bleed inlet coupling the offtake duct and a second cooling flow path, the bleed inlet defined at a location between the offtake inlet and the throat, inclusive.

2. The method as recited in claim 1 , wherein the bleed inlet is defined at the throat.

3. The method as recited in claim 2 , wherein the bleed inlet is spaced from the offtake inlet.

4. The method as recited in claim 1 , wherein a valve couples the offtake duct and the first cooling flow path at a position downstream of the throat, and the step of modulating the airflow includes modulating the valve between a closed position and an open position.

5. The method as recited in claim 4 , wherein the offtake duct and the bleed inlet are configured such that flow through the first cooling flow path is greater than flow through the bleed passage when the valve is in the open position.

6. The method as recited in claim 1 , wherein the bleed inlet is spaced from the offtake inlet.

7. The method as recited in claim 1 , wherein the bleed passage defines a passage axis oriented transversely relative to a localized surface region of the offtake duct.

8. The method as recited in claim 7 , wherein the bleed passage slopes towards an upstream portion of the offtake duct with respect to an engine longitudinal axis of the propulsion system.

9. The method as recited in claim 1 , further comprising moving a valve in the bleed passage between a closed position and an open position to modulate the diverted portion of the airflow through the bleed passage.

10. The method as recited in claim 1 , wherein the first cooling flow path is coupled to a first system, and the bleed passage is coupled to a second system, and further comprising causing the second system to modulate the airflow through the first cooling flow path.

11. The method as recited in claim 1 , wherein the airflow is communicated from a bypass flow path defined by a fan nacelle.

12. A method of cooling a propulsion system, comprising:
communicating airflow to an offtake inlet of an offtake duct, the offtake duct defining a throat;
modulating the airflow between the offtake duct and a first cooling flow path; and
diverting a portion of the airflow from the offtake duct to a bleed passage, the bleed passage including a bleed inlet coupling the offtake duct and a second cooling flow path, the bleed inlet defined at a location between the offtake inlet and the throat, inclusive; and
wherein the airflow is communicated from a bypass flow path defined by a fan nacelle.

13. The method as recited in claim 12 , wherein the offtake inlet is defined at an inner diameter of the bypass flow path.

14. A method of cooling a propulsion system, comprising:
communicating airflow to an offtake inlet of an offtake duct, the offtake duct defining a throat;
modulating the airflow between the offtake duct and a first cooling flow path; and
diverting a portion of the airflow from the offtake duct to a bleed passage, the bleed passage including a bleed inlet coupling the offtake duct and a second cooling flow path, the bleed inlet defined at a location between the offtake inlet and the throat, inclusive;
wherein the bleed inlet is spaced from the offtake inlet; and
wherein the offtake duct defines a duct axis between the offtake inlet and a valve in the first cooling flow path, and the offtake duct converges along the duct axis from the offtake inlet to the throat.

15. The method as recited in claim 14 , wherein the offtake duct diverges along the duct axis from the throat towards the valve.

16. A method of cooling a propulsion system, comprising:
communicating airflow to an offtake inlet of an offtake duct, the offtake duct defining a throat;
modulating the airflow between the offtake duct and a first cooling flow path; and
diverting a portion of the airflow from the offtake duct to a bleed passage, the bleed passage including a bleed inlet coupling the offtake duct and a second cooling flow path, the bleed inlet defined at a location between the offtake inlet and the throat, inclusive;
wherein the bleed passage defines a passage axis oriented transversely relative to a localized surface region of the offtake duct, the bleed passage slopes towards an upstream portion of the offtake duct with respect to an engine longitudinal axis of the propulsion system, the bleed passage extends along the passage axis between the bleed inlet and a bleed outlet, and the bleed outlet is axially forward of the bleed inlet with respect to the engine longitudinal axis.

17. The method as recited in claim 16 , wherein the offtake duct defines a duct axis between the offtake inlet and a valve in the first cooling flow path, and the offtake duct converges along the duct axis from the offtake inlet to the throat.

18. The method as recited in claim 17 , wherein the offtake duct diverges along the duct axis from the throat towards the valve.

19. The method as recited in claim 17 , wherein the valve couples the offtake duct and the first cooling flow path at a position downstream of the throat, and the step of modulating the airflow includes modulating the valve between a closed position and an open position.

20. The method as recited in claim 17 , wherein the valve interconnects the first cooling flow path and a first system, the bleed passage interconnects the bleed inlet and a second system, and the step of diverting the portion of the airflow occurs such that the second system has full flow when the first system has a low cooling requirement associated with a first operating condition of the propulsor system and such that the second system has a reduced flow when the first system has a relatively high cooling requirement associated with a second, different operating condition of the propulsor system.

21. The method as recited in claim 16 , wherein the airflow is communicated from a bypass flow path defined by a fan nacelle.

Assignees

• Raytheon Tech Corp

Inventors

• Ronan Michael

Classifications

• F02C7/18 Primary

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

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F02K1/78

  Other construction of jet pipes · CPC title

• F02K3/06 Primary

  with front fan · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title