Non-contact seal assembly for rotational equipment

1. 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 comprising an annular base, a shoe and a spring element;

the shoe radially adjacent the rotor disk structure;

the spring element radially between the shoe to the base, and the spring element connecting the shoe to the base;

the rotor disk structure including a rotor disk and a side plate attached to the rotor disk;

the side plate including a seal land with a cylindrical outer surface; and

the non-contact seal forming a seal with the cylindrical outer surface.

2. The assembly of claim 1 , wherein the shoe is configured to move radially in and out based on fluid pressure forces to which the shoe is subject during rotational equipment operation.

3. The assembly of claim 1 , wherein

the shoe is one of a plurality of shoes arranged around and radially adjacent the rotor disk structure; and

the spring element is one of a plurality of spring elements, each of the plurality of spring elements radially between and connecting a respective one of the plurality of shoes to the base.

4. The assembly of claim 3 , wherein the base is configured with a monolithic full hoop body.

5. The assembly of claim 1 , further comprising:

a combustor adjacent the stator vane assembly; and

a diffuser structure forming a diffuser plenum around the combustor.

6. The assembly of claim 5 , wherein the fixed stator structure is configured with the diffuser structure.

7. The assembly of claim 1 , wherein the fixed stator structure includes a tangential onboard injection nozzle configured to direct cooling air into an aperture in the rotor disk structure.

8. The assembly of claim 1 , wherein the fixed stator structure is configured with an aperture to direct air into an axial gap between a platform of the stator vane assembly and the rotor disk structure.

9. The assembly of claim 1 , wherein the seal assembly is configured with an aperture to direct air across the seal assembly and into an axial gap between a platform of the stator vane assembly and the rotor disk structure.

10. The assembly of claim 1 , wherein

the bladed rotor assembly is a turbine rotor assembly; and

the stator vane assembly is upstream of the bladed rotor assembly.

11. The assembly of claim 1 , wherein the side plate has a full hoop monolithic annular body.

12. The assembly of claim 1 , wherein

the bladed rotor assembly further includes a plurality of rotor blades arranged around the rotor disk; and

the rotor disk structure further includes a segmented second side plate circumscribing the side plate, and axially between the side plate and roots of the rotor blades.

13. 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 fixed stator structure and the rotor assembly, wherein the seal assembly includes a hydrostatic non-contact seal comprising a plurality of shoes, and each of the plurality of shoes is configured to move radially in and out based on fluid pressure forces generated during aircraft propulsion system operation;

the rotor assembly including a rotor disk structure comprising a seal land with a cylindrical outer surface; and

the hydrostatic non-contact seal circumscribing and forming a seal with the outer surface.

14. The system of claim 13 , wherein

the gas turbine engine further includes a combustor; and

the fixed stator structure is axially between and adjacent to the combustor and the rotor assembly.

15. The system of claim 13 , wherein the fixed stator structure is configured with a tangential onboard injection nozzle configured to direct air into an aperture in the rotor assembly.

16. The system of claim 13 , wherein the hydrostatic non-contact seal further comprises:

an annular base; and

a plurality of spring elements, a first of the plurality of spring elements radially between a first of the plurality of shoes and the base, and connecting the first of the plurality of shoes to the base;

wherein the plurality of shoes are arranged around and radially adjacent the rotor disk structure.