IP Library › Granted Patent US 12709994
Granted Patent B1
US 12709994 · App. 19/187,430 · Granted Aug 18, 2026

Failure detection of an oil transfer seal

Inventors: Guillaume Landry-Drolet (Boucherville, CA); Michel Desjardins (Saint-Hubert, CA); Thibaut Edmond J Duchene (Longueuil, CA)
Assignee: PRATT & WHITNEY CANADA CORP.
F01D25/183F01D25/20F05D2240/55F05D2260/98F05D2270/301
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Quick Facts
Patent No.
US 12709994
App. No.
19/187,430
Granted
Aug 18, 2026
Kind
B1
Abstract

A lubricant transfer arrangement of a gas turbine engine includes a first rotationally fixed component, a second component configured to rotate about an engine central axis of the gas turbine engine, and a lubricant transfer seal positioned radially between the first component and the second component. The lubricant transfer seal is configured to direct a flow of lubricant from a first location at the first component to a second location at the second component. The lubricant transfer seal is rotationally fixed and configured to seal to at least one of the first component and the second component. A lubricant pressure sensor is operatively connected to sense a lubricant pressure in a lubricant pathway fluidly upstream of the lubricant transfer seal. A controller receives a signal from the lubricant pressure sensor. The signal is indicative of the pressure in the lubricant pathway fluidly upstream of the lubricant transfer seal.

Claims (39)

1 . A lubricant transfer arrangement of a gas turbine engine, comprising:

a first rotationally fixed component;

a second component configured to rotate about an engine central axis of the gas turbine engine;

a lubricant transfer seal disposed radially between the first component and the second component configured to direct a flow of lubricant from a first location at the first component to a second location at the second component, wherein the lubricant transfer seal is rotationally fixed and configured to seal to at least one of the first component and the second component; and

a lubricant pressure sensor operatively connected to sense a lubricant pressure in a lubricant pathway fluidly upstream of the lubricant transfer seal; and

a controller receiving a signal from the lubricant pressure sensor, the signal being indicative of the pressure in the lubricant pathway fluidly upstream of the lubricant transfer seal.

2 . The lubricant transfer arrangement of claim 1 , wherein the controller is configured to identify a drop in the lubricant pressure sensed by the lubricant pressure sensor as being indicative of damage to the oil transfer seal.

3 . The lubricant transfer arrangement of claim 1 , further comprising a lubricant pressure pump configured to urge the flow of lubricant through the lubricant transfer seal.

4 . The lubricant transfer arrangement of claim 1 , further comprising one or more first seal elements to seal between the lubricant transfer seal and the second component.

5 . The lubricant transfer arrangement of claim 4 , further comprising one or more second seal elements to seal between the lubricant transfer seal and the first component.

6 . The lubricant transfer arrangement of claim 1 , further comprising one or more component pathways formed in the first component to convey the flow of lubricant along the first component.

7 . The lubricant transfer arrangement of claim 1 , further comprising one or more transfer seal pathways to direct the flow of lubricant from the first component to the second component via the lubricant transfer seal.

8 . The lubricant transfer arrangement of claim 1 , wherein the second component is a shaft of the gas turbine engine; and

further comprising a lubricant transfer sleeve disposed between the shaft and the lubricant transfer seal, the lubricant transfer sleeve having one or more sleeve passages defined therein to transfer the flow of lubricant to a sleeve cavity between the shaft and the lubricant transfer sleeve.

9 . A gas turbine engine, comprising:

a combustor;

a turbine rotationally driven about an engine central axis of the gas turbine engine by combustion products of the combustor; and

a lubricant transfer arrangement including:

a first rotationally fixed component;

a second component configured to rotate;

a lubricant transfer seal disposed radially between the first component and the second component configured to direct a flow of lubricant from a first location at the first component to a second location at the second component, wherein the lubricant transfer seal is rotationally fixed and configured to seal to at least one of the first component and the second component; and

a lubricant pressure sensor disposed along a lubricant pathway fluidly upstream of the lubricant transfer seal;

wherein a drop in a lubricant pressure measured by the lubricant pressure sensor is indicative of damage to or failure of the oil transfer seal.

10 . The gas turbine engine of claim 9 , further comprising a lubricant pressure pump configured to urge the flow of lubricant through the lubricant transfer seal.

11 . The gas turbine engine of claim 9 , further comprising one or more first seal elements to seal between the lubricant transfer seal and the second component.

12 . The gas turbine engine of claim 11 , further comprising one or more second seal elements to seal between the lubricant transfer seal and the first component.

13 . The gas turbine engine of claim 9 , further comprising one or more component pathways formed in the first component to convey the flow of lubricant along the first component.

14 . The gas turbine engine of claim 9 , further comprising one or more transfer seal pathways to direct the flow of lubricant from the first component to the second component via the lubricant transfer seal.

15 . The gas turbine engine of claim 9 , wherein the second component is an output shaft of the gas turbine engine.

16 . The gas turbine engine of claim 15 , further comprising a lubricant transfer sleeve disposed between the output shaft and the lubricant transfer seal, the lubricant transfer sleeve having one or more sleeve passages defined therein to transfer the flow of lubricant to a sleeve cavity between the shaft and the lubricant transfer sleeve.

17 . A lubrication system of a gas turbine engine, comprising:

a lubricant flow circuit, including:

a lubricant supply; and

a lubricant transfer seal disposed between a rotationally fixed component of the gas turbine engine and a rotating component of the gas turbine engine, the lubricant transfer seal having one or more transfer seal passages to direct a flow of lubricant to the rotating component; and

a lubricant pressure sensor disposed along the lubricant flow circuit configured to measure a pressure of the flow of lubricant in the lubricant flow circuit;

wherein a drop in the measured pressure is indicative of damage to or failure of the lubricant transfer seal.

18 . The lubrication system of claim 1 , further comprising a lubricant pressure pump disposed between the lubricant supply and the lubricant pressure sensor to urge the flow of lubricant along the lubricant flow circuit.

19 . The lubrication system of claim 1 , wherein the lubricant pressure sensor is operably connected to an engine control system of the gas turbine engine, the engine control system configured to compare the measured pressure of the flow of lubricant to a pressure threshold.

20 . The lubrication system of claim 3 , further comprising an alert disposed in a cockpit of an aircraft configured to activate when the measured pressure is below the pressure threshold.