Combustor panel configuration with skewed side walls

Patent metadata

Field	Value
Publication number	US-11073285-B2
Application number	US-201916448414-A
Country	US
Kind code	B2
Filing date	Jun 21, 2019
Priority date	Jun 21, 2019
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

A combustor of a gas turbine engine including a first forward liner panel. The forward liner panel including a liner panel forward edge, a liner panel aft edge opposite of the liner panel forward edge, and a first liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor.

First claim

What is claimed is:

1. A combustor of a gas turbine engine, the combustor comprising:
a first forward liner panel comprising:
a liner panel forward edge;
a liner panel aft edge opposite of the liner panel forward edge;
a first liner panel side edge between the liner panel aft edge and the liner panel forward edge; and
a second liner panel side edge between the liner panel aft edge and the liner panel forward edge, the second liner panel side edge being about parallel to the first liner panel side edge,
wherein the first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor, and
wherein the second liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to the swirl flow in the combustor; and

a second forward liner panel circumferentially adjacent to the first forward liner panel, the first forward liner panel and the second forward liner panel being in a spaced relationship forming a gap therebetween,
wherein the second forward liner panel further comprises:
a liner panel forward edge;
a liner panel aft edge opposite of the liner panel forward edge of the second forward liner panel;
a first liner panel side edge between the liner panel aft edge of the second forward liner panel and the liner panel forward edge of the second forward liner panel, wherein the first liner panel side edge of the second forward liner panel is non-perpendicular to the liner panel forward edge of the second forward liner panel and oriented at an angle about perpendicular to the swirl flow in the combustor; and
a second liner panel side edge between the liner panel aft edge of the second forward liner panel and the liner panel forward edge of the second forward liner panel, the second liner panel side edge of the second forward liner panel being about parallel to the first liner panel side edge of the second forward liner panel,
wherein the second liner panel side edge of the second forward liner panel is non-perpendicular to the liner panel forward edge of the second forward liner panel and oriented at an angle about perpendicular to the swirl flow in the combustor,
wherein the second liner panel side edge of the second forward liner panel is operably shaped to direct cooling airflow from a cavity of the first forward liner panel to a hot side of the second forward liner panel, and
wherein the second liner panel side edge of the second forward liner panel is oriented non-perpendicular to the hot side of the second forward liner panel to direct cooling airflow from the cavity of the first forward liner panel to the hot side of the second forward liner panel.

2. The combustor of claim 1 , wherein the liner panel forward edge and the liner panel aft edge are parallel.

3. The combustor of claim 1 , further comprising:
a second forward liner panel circumferentially adjacent to the first forward liner panel, the first forward liner panel and the second forward liner panel being in a spaced relationship forming a gap therebetween.

4. The combustor of claim 3 , wherein the first forward liner panel is offset from the second forward liner panel to direct cooling airflow from a cavity of the first forward liner panel to the hot side of the second forward liner panel.

5. The combustor of claim 1 , wherein the first liner panel side edge of the first forward liner panel is offset from the second liner panel side edge of the second forward liner panel to direct cooling airflow from the cavity of the first forward liner panel to the hot side of the second forward liner panel.

6. The combustor of claim 5 , wherein the first liner panel side edge of the first forward liner panel is in a facing spaced relationship with the second liner panel side edge of the second forward liner panel defining the gap therebetween.

7. The combustor of claim 1 , wherein the first liner panel side edge of the first forward liner panel is operably shaped to direct cooling airflow from a cavity of the first forward liner panel to the hot side of the second forward liner panel.

8. The combustor of claim 7 , wherein the first liner panel side edge of the first forward liner panel is oriented non-perpendicular to a cold side of the first forward liner panel to direct cooling airflow from the cavity of the first forward liner panel to the hot side of the second forward liner panel.

9. The combustor of claim 1 , wherein the first forward liner panel further comprises a side wall at the first liner panel side edge of the first forward liner panel, wherein the side wall further comprises cooling film orifices.

10. The combustor of claim 1 , wherein the second forward liner panel further comprises a side wall at the first liner panel side edge of the second forward liner panel, wherein the side wall does not include cooling film orifices.

11. The combustor of claim 1 , further comprising:
an aft liner panel located aft of the first forward liner panel, wherein the aft liner panel is in a spaced relationship with the first forward liner panel forming a circumferential gap therebetween.

12. The combustor of claim 1 , further comprising:
an aft liner panel located aft of the first forward liner panel, wherein the aft liner panel is integrally attached to the first forward liner panel to form a combined liner panel.

13. The combustor of claim 2 , wherein the first liner panel side edge and the second liner panel side edge are linear in shape.

14. The combustor of claim 2 , wherein the first liner panel side edge and the second liner panel side edge are curvilinear in shape.

15. A gas turbine engine, comprising:
a combustor comprising;
a forward liner panel comprising:
a liner panel forward edge;
a liner panel aft edge opposite of the liner panel forward edge;
a first liner panel side edge between the liner panel aft edge and the liner panel forward edge; and
a second liner panel side edge between the liner panel aft edge and the liner panel forward edge, the second liner panel side edge being about parallel to the first liner panel side edge,
wherein the first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor, and
wherein the second liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to the swirl flow in the combustor; and

a second forward liner panel circumferentially adjacent to the first forward liner panel, the first forward liner panel and the second forward liner panel being in a spaced relationship forming a gap therebetween,
wherein the second forward liner panel further comprises:
a liner panel forward edge;
a liner panel aft edge opposite of the liner panel forward edge of the second forward liner panel;
a first liner panel side edge between the liner panel aft edge of the second forward liner panel and the liner panel forward edge of the second forward liner panel, wherein the first liner panel side edge of the second forward liner panel is non-perpendicular to the liner panel forward edge of the second forward liner panel and oriented at an angle about perpendicular to the swirl flow in the combustor, and
a second liner panel side edge between the liner panel aft edge of the second forward liner panel and the liner panel forward edge of the second forward liner panel the second liner panel side edge of the second forward liner panel being about parallel to the first liner panel side edge of the second forward l

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Quach San
• Styborski Jeremy
• Karanian Caroline

Classifications

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R3/50

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

• F23R3/002 Primary

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

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title