Granted Patent B2

US 12,234,767 · App. 18/129,609 · Granted Feb 25, 2025

Inventor: Hugues Pellerin (Montreal, CA)

Assignee: Pratt & Whitney Canada Corp.

F02C7/06F05D2260/98

Abstract

Claims (26)

1. An aircraft engine lubrication system for an aircraft engine having a first component (FC) with an FC inlet and an FC outlet, and a second component (SC) having a SC inlet and a SC outlet, wherein the first component and the second component are a gearbox or a bearing cavity, the system comprising:

a lubricant tank (LT) configured to contain a volume of lubricant, the lubricant tank having a LT first inlet, a LT second inlet, and a LT outlet;

a first pump (FP) having a FP inlet and a FP outlet;

a second pump (SP) having a SP inlet and a SP outlet;

a de-aerator (DA) having a DA inlet, a DA gas outlet, and a DA liquid outlet;

wherein the LT outlet is in fluid communication with the FP inlet, the FP outlet is in fluid communication with the SP inlet, and the SP outlet is in fluid communication with the FC inlet and the SC inlet such that lubricant exiting the second pump passes to the first component and to the second component;

wherein the SC outlet is in fluid communication with the LT first inlet such that lubricant exiting the second component passes to the lubricant tank without passing through the de-aerator;

wherein the FC outlet is in fluid communication with the de-aerator, the DA gas outlet is in fluid communication with the LT second inlet such that gas exiting the de-aerator passes to the lubricant tank, and the DA liquid outlet is in fluid communication with the SP inlet such that the lubricant exiting the de-aerator passes to the second pump, bypassing the lubricant tank,

wherein all lubricant exiting the de-aerator passes to the second pump and bypasses the lubricant tank.

2. The system of claim 1 , wherein the de-aerator is a static de-aerator.

3. The system of claim 1 , wherein the de-aerator is an active de-aerator.

4. The system of claim 1 , wherein the second pump is a positive displacement pump.

5. The system of claim 1 , further comprising a scavenge pump in fluid communication with the FC outlet and the DA inlet such that lubricant flows from the FC outlet through the scavenge pump to the DA inlet.

6. The system of claim 1 , wherein a fluid line extends between the FP outlet and the SP inlet and the DA liquid outlet is in fluid communication with the fluid line.

7. A method of selectively operating the aircraft engine lubrication system of claim 1 , the method comprising:

pumping the lubricant from the lubricant tank using the first pump, and pumping the lubricant to the second pump from the first pump;

using the second pump to pump the lubricant to the first component (FC) and to the second component (SC);

returning the lubricant from the second component to the lubricant tank without passing through the de-aerator;

directing the lubricant from the first component to the de-aerator;

using the de-aerator to separate the lubricant into a separated gas component and a separated liquid component;

directing the separated gas component to the lubricant tank; and

directing the separated liquid component to the SP inlet, bypassing the lubricant tank.

8. The method of claim 7 , wherein a quasi-closed lubricant loop for the first component is formed by the second pump pumping the lubricant to the first component, directing the lubricant from the first component to the de-aerator, and directing the separated liquid component to the SP inlet.

9. The method of claim 7 , wherein the step of returning the lubricant from the second component to the lubricant tank includes passing the lubricant from the second component through a second de-aerator.

10. The method of claim 9 , further comprising selectively operating an oil delay valve in an open configuration or a closed configuration, wherein in the open configuration lubricant from the second pump passes from the second pump to the second component, and wherein in the closed configuration lubricant from the second pump does not pass from the second pump to the second component.

11. The method of claim 10 , wherein operating the oil delay valve in a closed configuration produces a quasi-closed lubricant loop for the first component.

Assignments (1)

Continuity (1)

References Cited (9)