Disrupting flow vortices to attenuate resonant tones within a gas turbine engine
An assembly is provided for a gas turbine engine. This assembly includes a rotating structure of the gas turbine engine, a stationary structure of the gas turbine engine and a volume formed by and extending between the rotating structure and the stationary structure. The rotating structure is rotatable about an axis. The rotating structure includes a seal land and a fluid nozzle. The stationary structure includes a seal element. The seal element is arranged with the seal land to form a seal assembly that seals an annular gap between the stationary structure and the rotating structure. The volume is adjacent the seal element and the seal land. The fluid nozzle is configured to direct a fluid jet out from the rotating structure and into the volume.
1. An assembly for a gas turbine engine, comprising:
a rotating structure of the gas turbine engine rotatable about an axis, the rotating structure including a seal land, an engine shaft, and a plurality of fluid nozzles, the plurality of fluid nozzles including a first nozzle and a second nozzle, the seal land connected to and rotatable with the engine shaft;
a stationary structure of the gas turbine engine comprising a seal element, the seal element arranged with the seal land to form a seal assembly that seals an annular gap between the stationary structure and the rotating structure; and
a volume formed by and extending between the rotating structure and the stationary structure, the volume adjacent the seal element and the seal land;
each of the plurality of fluid nozzles configured to direct a respective fluid jet out from the rotating structure and into the volume,
wherein each of the plurality of fluid nozzles is mounted to and/or included as part of the rotating structure, and
wherein the first nozzle is configured to direct the respective fluid jet into the volume in a radial direction towards the seal assembly, and the second nozzle is configured to direct the respective fluid jet into the volume in an axial direction away from the seal assembly.
2. The assembly of claim 1 , wherein each of the plurality of fluid nozzles is configured to direct the respective fluid jet into the volume to disrupt flow vortices within the volume.
3. The assembly of claim 1 , wherein
at least one fluid nozzle of the plurality of fluid nozzles includes a nozzle passage and a nozzle orifice fluidly coupling the nozzle passage to the volume; and
the nozzle passage tapers as the nozzle passage extends longitudinally away from the nozzle orifice.
4. The assembly of claim 1 , wherein at least one fluid nozzle of the plurality of fluid nozzles comprises a diffuser section configured to diffuse the fluid jet directed into the volume.
5. The assembly of claim 1 , wherein
at least one fluid nozzle of the plurality of fluid nozzles includes a nozzle passage and a nozzle orifice fluidly coupling the nozzle passage to the volume; and
the nozzle passage extends longitudinally along a centerline to the nozzle orifice, and at least a portion of the centerline that extends longitudinally to the nozzle orifice is curved.
6. The assembly of claim 1 , wherein
at least one fluid nozzle of the plurality of fluid nozzles includes a nozzle passage and a nozzle orifice fluidly coupling the nozzle passage to the volume; and
the nozzle orifice has an elongated cross-sectional geometry.
7. The assembly of claim 1 , wherein
at least one fluid nozzle of the plurality of fluid nozzles includes a nozzle passage and a nozzle orifice fluidly coupling the nozzle passage to the volume; and
the nozzle orifice has a polygonal cross-sectional geometry.
8. The assembly of claim 1 , wherein
at least one fluid nozzle of the plurality of fluid nozzles includes a nozzle passage and a nozzle orifice fluidly coupling the nozzle passage to the volume; and
the nozzle orifice has an irregular cross-sectional geometry.
9. The assembly of claim 1 , further comprising:
a lubricant source fluidly coupled to at least one fluid nozzle of the plurality of fluid nozzles;
the fluid jet comprising a lubricant jet.
10. The assembly of claim 1 , further comprising:
an air source fluidly coupled to at least one fluid nozzle of the plurality of fluid nozzles;
the fluid jet comprising an air jet.
11. The assembly of claim 1 , wherein the volume comprises an air passage extending to the seal assembly.
12. The assembly of claim 1 , wherein the volume comprises an air cavity.
13. The assembly of claim 1 , further comprising:
a bearing rotatably coupling the rotating structure to the stationary structure;
the volume comprising a bearing compartment in which the bearing is disposed.
14. The assembly of claim 1 , further comprising a second plurality of fluid nozzles, each of the fluid nozzles of the second plurality of fluid nozzles mounted to and/or included as part of the stationary structure, and each of the fluid nozzles of the second plurality of fluid nozzles configured to direct a respective fluid jet out from the stationary structure and into the volume,
wherein the second plurality of fluid nozzles includes a third nozzle and a fourth nozzle, the third nozzle configured to direct the respective fluid jet into the volume radially towards the seal assembly, and the fourth nozzle configured to direct the respective fluid jet into the volume axially towards from the seal assembly.
15. An assembly for a gas turbine engine, comprising:
a rotating structure of the gas turbine engine rotatable about an axis, the rotating structure comprising a seal land;
a stationary structure of the gas turbine engine comprising a seal element, the seal element arranged with the seal land to form a seal assembly that seals an annular gap between the stationary structure and the rotating structure;
a volume formed by and extending between the rotating structure and the stationary structure, the volume adjacent the seal element and the seal land, wherein the volume comprises an air passage extending to the seal assembly; and
a plurality of fluid nozzles, the plurality of fluid nozzles including a first nozzle and a second nozzle, each fluid nozzle of the plurality of fluid nozzles including a respective nozzle passage and a respective nozzle orifice, each fluid nozzle of the plurality of fluid nozzles configured to direct a fluid out of the respective nozzle passage, through the respective nozzle orifice, and into the volume as a diffuse flow of the fluid,
wherein the first nozzle and the second nozzle are mounted to and/or included as part of the rotating structure, and wherein the first nozzle is configured to direct the respective fluid into the volume in a radial direction towards the seal assembly, and the second nozzle is configured to direct the fluid into the volume in an axial direction away from the seal assembly.
16. The assembly of claim 15 , wherein a width of each respective nozzle passage expands as the nozzle passage extends longitudinally towards the respective nozzle orifice.
17. The assembly of claim 15 , wherein each respective nozzle orifice has a non-circular cross-sectional geometry.
18. An assembly for a gas turbine engine, comprising:
a rotating structure of the gas turbine engine rotatable about an axis, the rotating structure comprising a seal land;
a stationary structure of the gas turbine engine comprising a seal element, the seal element arranged with the seal land to form a seal assembly that seals an annular gap between the stationary structure and the rotating structure;
a volume formed by and extending between the rotating structure and the stationary structure, the volume adjacent the seal element and the seal land, wherein the volume comprises an air passage extending to the seal assembly; and
a plurality of fluid nozzles, the plurality of fluid nozzles including a first nozzle and a second nozzle, each of the first nozzle and the second nozzle including a respective nozzle passage and a respective nozzle orifice, each of the first nozzle and the second nozzle configured to direct a fluid out of the respective nozzle passage, through the respective nozzle orifice, and into the volume as a turbulent flow of the fluid,
wherein each of the first nozzle and the second nozzle is configured and rotatable with the rotating structure, and
wherein the first nozzle is configured to direct the fluid into the volume in a radial direction towards the seal assembly, and the second nozzle is configured to direct the fluid into the volume in an axial direction away from the seal assembly.
19. The assembly of claim 18 , wherein each respective nozzle passage follows a curved trajectory to each respective nozzle orifice.