Hybrid through holes and angled holes for combustor grommet cooling

Patent metadata

Field	Value
Publication number	US-10077903-B2
Application number	US-201514886973-A
Country	US
Kind code	B2
Filing date	Oct 19, 2015
Priority date	Oct 20, 2014
Publication date	Sep 18, 2018
Grant date	Sep 18, 2018

Abstract

Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.

First claim

What is claimed is:

1. A combustor of a gas turbine engine, comprising:
a liner including a grommet and a panel, the grommet including
a plurality of angled holes; and
at least one grommet through hole separating all combinations of any two angled holes of the plurality of angled holes around a perimeter of the grommet; and

the panel including a panel through hole,
wherein the at least one grommet through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each angled hole of the plurality of angled holes are non-parallel to the at least one grommet through hole,
wherein a first grommet through hole of the at least one grommet through hole and the panel through hole are co-axial such that cooling air passes through the first grommet through hole and the panel through hole.

2. The combustor of claim 1 , wherein the grommet includes an alternating sequence of grommet through holes and angled holes around the perimeter of the grommet.

3. The combustor of claim 1 , wherein the at least one grommet through hole includes a second grommet through hole that is directly adjacent to the first grommet through hole.

4. The combustor of claim 3 , wherein the first grommet through hole and the second grommet through hole are proximate to a rib.

5. A gas turbine engine liner, comprising:
a shell;
a panel coupled to the well, the panel including a panel through hole; and
a grommet; that includes:
a plurality of angled holes; and
at least one grommet through hole separating all combinations of any two angled holes of the plurality of angled holes around a perimeter of the grommet,

wherein the at least one grommet through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and
wherein each angled hole of the plurality of angled holes are non-parallel to the at least one grommet through hole, and
wherein a first grommet through hole of the at least one grommet through hole and the panel through hole are co-axial such that cooling air passes through the first grommet through hole and the panel through hole.

6. The gas turbine engine liner of claim 5 , wherein the shell includes a plurality of impingement holes and wherein the panel includes a plurality of effusion holes.

7. The gas turbine engine liner of claim 5 , wherein the grommet includes an alternating sequence of grommet through holes and angled holes around the perimeter of the grommet.

8. The gas turbine engine liner of claim 5 , wherein the at least one grommet through hole includes a second grommet through hole that is directly adjacent to the first grommet through hole.

9. The gas turbine engine liner of claim 8 , wherein the first grommet through hole and the second grommet through hole are proximate to a rib.

10. The gas turbine engine liner of claim 5 , further comprising:
a groove configured to provide a passage for the cooling air with respect to the first grommet through hole.

Assignees

• United Technologies Corp

Inventors

• Tu John S
• Hoke James B
• Pacheco-Tougas Monica
• Snyder Timothy S
• Moura Dennis M
• Van Anthony

Classifications

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic