Axial pump with reduced clearance feature
AssigneePratt & Whitney Canada Corp.
InventorsIan MacFarlane, Michel Abdelnour
Life of this patent
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Abstract
A rotating seal assembly of a gas turbine engine includes a rotating seal element, and a rotationally stationary seal support positioned radially outboard of the rotating seal element. The rotating seal element and the seal support are configured to define a seal interface therebetween. The seal element includes an axial pump portion defined by one or more axially and circumferentially extending grooves to urge an airflow therethrough. The airflow is configured to prevent a fluid from entering the seal interface. The axial pump portion defines a radial running clearance with a floating seal.
Claims20
A rotating seal assembly of a gas turbine engine, comprising:
- a rotating seal element;
- and
- a rotationally stationary seal support positioned radially outboard of the rotating seal element, the rotating seal element and the seal support configured to define a seal interface therebetween;
- wherein the seal element includes an axial pump portion defined by one or more axially and circumferentially extending grooves to urge an airflow therethrough, the airflow configured to prevent a fluid from entering the seal interface;
- wherein the axial pump portion defines a radial running clearance with a floating seal.
A bearing and seal arrangement of a gas turbine engine comprising:
- a bearing disposed in a bearing housing, the bearing supportive of a rotating component of the gas turbine engine;
- a seal assembly disposed at the bearing housing to seal the bearing housing, the seal assembly including:
- a seal element operably connected to the rotating component and rotatable therewith;
- a rotationally stationary seal support positioned radially outboard of the seal element, the seal element and the seal support configured to define a seal interface therebetween;
- wherein the seal element includes an axial pump portion defined by one or more axially and circumferentially extending grooves to urge an airflow therethrough, the airflow configured to prevent a fluid from entering the seal interface;
- wherein the axial pump portion defines a radial running clearance with a floating seal.
A propulsion arrangement of an aircraft, comprising:
- a propeller;
- and
- a gas turbine engine operably connected to the propeller to drive rotation of the propeller, the gas turbine engine including:
- a rotating shaft;
- and
- a bearing disposed in a bearing housing, the bearing supportive of a rotating component of the gas turbine engine;
- a seal assembly disposed at the bearing housing to seal the bearing housing, the seal assembly including:
- a seal element operably connected to the rotating component and rotatable therewith;
- a rotationally stationary seal support positioned radially outboard of the seal element, the seal element and the seal support configured to define a seal interface therebetween;
- wherein the seal element includes an axial pump portion defined by one or more axially and circumferentially extending grooves to urge an airflow therethrough, the airflow configured to prevent a fluid from entering the seal interface;
- wherein the axial pump portion defines a radial running clearance with a floating seal.
Dependencies are inferred from the claim text.