Non-contact seal assembly for rotational equipment
AssigneeUnited Technologies Corporation
InventorsWilliam K. Ackermann, Clifton J. Crawley, Jr., Frederick M. Schwartz
Life of this patent
Estimating the term…
Abstract
Assemblies are provided for rotational equipment. One of these assemblies includes a bladed rotor assembly, a stator vane assembly, a fixed stator structure and a seal assembly. The bladed rotor assembly includes a rotor disk structure. The stator vane assembly is disposed adjacent the bladed rotor assembly. The fixed stator structure is connected to and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.
Claims18
An assembly for rotational equipment, the assembly comprising:
- a bladed rotor assembly including a rotor disk structure;
- a stator vane assembly disposed adjacent the bladed rotor assembly;
- a fixed stator structure connected to and radially within the stator vane assembly;
- and
- a seal assembly configured for sealing a gap between the fixed stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal;
- wherein the non-contact seal comprises:
- an annular base, wherein the annular base is configured with a monolithic full hoop body;
- a plurality of shoes arranged around and radially adjacent the rotor disk structure;
- and
- a plurality of spring elements, each of the spring elements radially between and connecting a respective one of the shoes to the annular base.
An aircraft propulsion system, comprising:
- a gas turbine engine including a turbine section which comprises:
- a rotor assembly;
- a fixed stator structure axially adjacent the rotor assembly;
- and
- a seal assembly configured for sealing a gap between the stator structure and the rotor assembly, wherein the seal assembly includes a non-contact seal
- wherein the non-contact seal comprises:
- an annular base configured with a monolithic full hoop body;
- a plurality of shoes arranged around and radially adjacent the rotor assembly;
- and
- a plurality of spring elements, each of the spring elements radially between and connecting a respective one of the shoes to the annular base.
An aircraft propulsion system, comprising:
- a gas turbine engine including a combustor and a turbine section which comprises:
- a bladed rotor assembly including a rotor disk structure;
- a stator vane assembly disposed axially between and adjacent the combustor and the bladed rotor assembly;
- a stator structure connected to and radially within the stator vane assembly;
- and
- a seal assembly configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal;
- wherein the non-contact seal comprises:
- an annular base configured with a monolithic full hoop body;
- a plurality of shoes arranged around and radially adjacent the rotor disk structure;
- and
- a plurality of spring elements, each of the spring elements radially between and connecting a respective one of the shoes to the annular base.
Dependencies are inferred from the claim text.