Controlled-leak combustor grommet

Patent metadata

Field	Value
Publication number	US-9803863-B2
Application number	US-201514711628-A
Country	US
Kind code	B2
Filing date	May 13, 2015
Priority date	May 13, 2015
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

Abstract

A grommet for a combustor of a gas turbine engine is disclosed. The grommet includes a lower platform and a raised platform. The lower platform includes a plurality of top slots located in the top surface and a plurality of bottom slots located in the bottom surface. Each top slot and bottom slot may extend radially along the lower platform. The plurality of top slots may be spaced equidistantly from one another along the circumference of the lower platform. The plurality of bottom slots may be spaced equidistantly from one another along the circumference of the lower platform.

First claim

What is claimed is:

1. A grommet assembly for a combustion chamber of a gas turbine engine, the grommet assembly comprising: a retaining shroud including an upper annulus having an inner surface; a retaining nut coupled to the retaining shroud, the retaining nut including a covering portion having an inner surface; and a grommet including a lower annular platform having a top surface, a bottom surface opposite the top surface, an outer surface extending between the top surface and the bottom surface, a plurality of top grooves extending radially along the top surface of the lower annular platform, and a plurality of bottom grooves extending radially along the bottom surface of the lower annular platform, a cylindrical platform extending from the top surface of the lower annular platform, the cylindrical platform having an outer surface, at least a portion of the lower annular platform of the grommet extending between the retaining nut and the retaining shroud, the inner surface of the covering portion of the retaining nut and the outer surface of the cylindrical platform of the grommet defining an upper gap, and the outer surface of the lower annular platform of the grommet and the inner surface of the upper annulus of the retaining shroud defining a lower gap, the upper gap in fluid communication with the lower gap.

2. The grommet assembly of claim 1 , wherein the upper gap, the plurality of top grooves, the lower gap, and the plurality of bottom grooves define a passage.

3. The grommet assembly of claim 2 , wherein the combustion chamber includes an exterior outer liner, an interior outer liner, a conduit inserted through the exterior outer liner and the interior outer liner, and the grommet assembly coupled to the conduit.

4. The grommet assembly of claim 3 , wherein the passage is in fluid communication with a portion of the interior outer liner.

5. The grommet assembly of claim 3 , further comprising a second grommet assembly including an elongated grommet, an outer retaining shroud, and an outer retaining nut, wherein the second grommet assembly is coupled to the conduit.

6. The grommet assembly of claim 5 , wherein the grommet is coupled to the elongated grommet.

7. The grommet assembly of claim 1 , wherein the lower annular platform of the grommet is configured to thermally expand between the retaining nut and the retaining shroud.

8. The grommet assembly of claim 1 , wherein the width of each top groove is 0.04″, the depth of each top groove is 0.04″, the width of each bottom groove is 0.03″, and the depth of each bottom groove is 0.03″.

9. The grommet assembly of claim 1 , wherein the grommet includes 12 top grooves and 12 bottom grooves, and each top groove and each bottom groove is a cylindrical groove.

10. The grommet assembly of claim 1 , wherein each top groove is circumferentially offset from each bottom groove.

11. A combustion chamber of a gas turbine engine, the combustion chamber comprising: an outer liner and an inner liner, the outer liner and inner liner forming a combustion zone there between; a conduit inserted through the outer liner, the conduit having a channel in fluid communication with the combustion zone; a grommet assembly coupled to the conduit, the grommet assembly including a first fixture component including an upper annulus having an inner surface; a second fixture component coupled to the first fixture component, the second fixture component including a covering portion having an inner surface, a floating grommet including a lower annular platform having a top surface, a bottom surface opposite the top surface, an outer surface extending between the top surface and the bottom surface, a plurality of top grooves extending radially along the top surface of the lower annular platform, and a plurality of bottom grooves extending radially along the bottom surface of the lower annular platform, a cylindrical platform extending from the top surface of the lower annular platform, the cylindrical platform having an outer surface, at least a portion of the top grooves and at least a portion of the bottom grooves extending between the first fixture component and the second fixture component, the inner surface of the covering portion of the second fixture component and the outer surface of the cylindrical platform of the floating grommet defining an upper gap, and the outer surface of the lower annular platform of the floating grommet and the inner surface of the upper annulus of the first fixture component defining a lower gap, the upper gap in fluid communication with the lower gap.

12. The combustion chamber of claim 11 , further comprising a plurality of conduits inserted through the outer liner, each conduit spaced circumferentially apart from each other along the circumference of the outer liner, and a plurality of grommet assemblies, each grommet assembly coupled to one of the conduits.

13. The combustion chamber of claim 11 , wherein the upper gap, the plurality of top grooves, the lower gap, and the plurality of bottom grooves define a passage in fluid communication with the combustion zone.

14. The combustion chamber of claim 13 , wherein the passage is in fluid communication with a portion of the outer liner.

15. The combustion chamber of claim 11 , further comprising a resonator in fluid communication with the conduit.

16. The combustion chamber of claim 11 , wherein the floating grommet includes 12 top grooves and 12 bottom grooves.

17. A grooved cooling grommet for a conduit within a combustion chamber for a gas turbine engine, the grooved cooling grommet comprising: a lower annular platform having a top surface, a bottom surface opposite the top surface, an outer surface extending between the top surface and the bottom surface at an outer circumferential end of the lower annular platform, and an inner circumferential end, a collar extending from the top surface of the lower annular platform adjacent the inner circumferential end of the lower annular platform, the collar having an outer surface located at an outer circumferential end of the collar, the outer surface of the collar circumferentially offset from the outer surface of the lower annular platform, a plurality of top grooves located in the top surface of the lower platform and a plurality of bottom grooves located in the bottom surface of the lower platform, each top groove and bottom groove extending radially from the outer surface of the collar to the outer surface of the lower platform; and wherein the plurality of top grooves are spaced equidistantly from one another along the circumference of the lower platform, the plurality of bottom grooves are spaced equidistantly from one another along the circumference of the lower platform, and each top groove is circumferentially offset from an adjacent bottom groove.

18. The grooved cooling grommet of claim 17 , wherein the width of each top groove is 0.04″, and the width of each bottom groove is 0.03″.

19. The grooved cooling grommet of claim 17 , wherein the depth of each top groove is 0.04″, and the depth of each bottom groove is 0.03″.

20. The grooved cooling grommet of claim 17 , wherein the grooved cooling grommet includes 12 top grooves and 12 bottom grooves.

Assignees

• Solar Turbines Inc

Inventors

• Johnson Crosby Hayhurst
• Kim Yong Weon
• Groocock Ted Edwin

Classifications

• F23R3/045 Primary

  using pipes · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title

• F23R2900/00014

  Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title