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US 10,822,983 B2Granted
Hydrostatic seal with abradable teeth for gas turbine engine
AssigneeRaytheon Technologies Corportation
InventorsMichael L. DiFrancesco, Tara L. D'Ambruoso
Life of this patent
Estimating the term…
Abstract
A hydrostatic seal assembly includes a seal support, a seal shoe integral to the seal support and radially movable relative to the seal support. A plurality of seal teeth are located at a radially inboard surface of the seal shoe. The seal shoe is formed from a first material and the radially inboard surface is formed from a second material softer than the first material such that the radially inboard surface is abradable in the event of a rub between the radially inboard surface and an adjacent rotating component.
Claims20
A hydrostatic seal assembly, comprising:
- a seal support;
- a seal shoe integral to the seal support and radially movable relative to the seal support;
- a plurality of seal teeth disposed at a radially inboard surface of the seal shoe;
- a secondary seal located upstream of the seal shoe, the secondary seal configured to prevent airflow to and/or from a seal cavity located radially outboard of the seal shoe at an upstream side of the seal assembly;
- and
- a scalloped plate disposed downstream of the seal shoe, the scalloped plate including one or more openings formed therein to admit airflow into the seal cavity radially outboard of the seal shoe;
- wherein the seal shoe is formed from a first material and the radially inboard surface is formed from a second material softer than the first material such that the radially inboard surface is abradable in the event of a rub between the radially inboard surface and an adjacent rotating component.
4 more elements
A turbine section of a gas turbine engine, comprising:
- a turbine stator;
- a turbine rotor configured to rotate about an engine central longitudinal axis relative to the turbine stator;
- and
- a hydrostatic seal assembly fixed to the turbine stator comprising:
- a seal support;
- a seal shoe integral to the seal support and radially movable relative to the seal support;
- a plurality of seal teeth disposed at a radially inboard surface of the seal shoe;
- a secondary seal located upstream of the seal shoe, the secondary seal configured to prevent airflow to and/or from a seal cavity located radially outboard of the seal shoe at an upstream side of the seal assembly;
- and
- a scalloped plate disposed downstream of the seal shoe, the scalloped plate including one or more openings formed therein to admit airflow into the seal cavity radially outboard of the seal shoe;
- wherein the seal shoe is formed from a first material and the radially inboard surface is formed from a second material softer than the first material such that the radially inboard surface is abradable in the event of a rub between the radially inboard surface and the turbine rotor during operation of the turbine section.
8 more elements
A gas turbine engine, comprising:
- a combustor;
- a turbine section in fluid communication with the combustor, the turbine section comprising:
- a turbine stator;
- a turbine rotor configured to rotate about an engine central longitudinal axis relative to the turbine stator;
- and
- a hydrostatic seal assembly fixed to the turbine stator comprising:
- a seal support;
- a seal shoe integral to the seal support and radially movable relative to the seal support;
- a plurality of seal teeth disposed at a radially inboard surface of the seal shoe;
- a secondary seal located upstream of the seal shoe, the secondary seal configured to prevent airflow to and/or from a seal cavity located radially outboard of the seal shoe at an upstream side of the seal assembly;
- and
- a scalloped plate disposed downstream of the seal shoe, the scalloped plate including one or more openings formed therein to admit airflow into the seal cavity radially outboard of the seal shoe;
- wherein the seal shoe is formed from a first material and the radially inboard surface is formed from a second material softer than the first material such that the radially inboard surface is abradable in the event of a rub between the radially inboard surface and the turbine rotor during operation of the turbine section.
10 more elements
Dependencies are inferred from the claim text.