Combustor panels having angled rail

Patent metadata

Field	Value
Publication number	US-10260750-B2
Application number	US-201514982642-A
Country	US
Kind code	B2
Filing date	Dec 29, 2015
Priority date	Dec 29, 2015
Publication date	Apr 16, 2019
Grant date	Apr 16, 2019

Abstract

A combustor of a gas turbine engine including a combustor shell having an interior surface defining a combustion chamber, a first panel mounted to the interior surface at a first position, the first panel having a first surface and a first rail extending from the first surface toward the combustor shell, the first rail configured at a first angle relative to the first surface, and a second panel mounted to the interior surface at a second position axially adjacent to the first panel, the second panel having a second surface and a second rail extending from the second surface toward the combustor shell, the second rail configured at a second angle relative to the second surface. The first and second rails are proximal to each other and define a circumferential gap there between and at least one of the first or second angles is an acute angle.

First claim

What is claimed is:

1. A combustor of a gas turbine engine comprising:
a combustor shell having an interior surface and defining a combustion chamber having an axial length;
at least one first panel mounted to the interior surface at a first position, the at least one first panel having a first combustion chamber surface and a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, the first rail joins the first combustion chamber surface at a first angle α; and
at least one second panel mounted to the interior surface at a second position and axially adjacent to the at least one first panel, the at least one second panel having a second combustion chamber surface and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell, the second rail joins the second combustion chamber surface at a second angle β,
wherein the first rail and the second rail are proximal to each other and define a circumferentially extending gap therebetween, and
wherein at least one of the first angle α or the second angle β is an acute angle; and
wherein
the at least one first panel comprises a plurality of first panels, wherein the plurality of first panels define a first axially extending gap between two circumferentially adjacent first panels, and each first panel of the two circumferentially adjacent first panels have respective axially extending rails that extend from their respective first combustion chamber surfaces toward the interior surface, wherein one rail of the respective axially extending rails of the two circumferentially adjacent first panels is configured at an acute angle relative to the first combustion chamber surface of the respective first panel the one rail extends from; and/or
the at least one second panel comprises a plurality of second panels, wherein the plurality of second panels define a second axially extending gap between two circumferentially adjacent second panels, and each second panel of the two circumferentially adjacent second panels have respective axially extending rails that extend from their respective second combustion chamber surfaces toward the interior surface, wherein one rail of the respective axially extending rails of the two circumferentially adjacent second panels is configured at an acute angle relative to the second combustion chamber surface of the respective second panel the one rail extends from.

2. The combustor of claim 1 , wherein both of the first angle α and the second angle β are acute angles.

3. The combustor of claim 1 , wherein the first rail and the second rail are parallel to each other.

4. The combustor of claim 1 , wherein the other of the at least one of the first angle α and the second angle β is configured at a 90° angle.

5. A gas turbine engine comprising:
a combustor including a combustor shell having an interior surface and defining a combustion chamber having an axial length;
at least one first panel mounted to the interior surface at a first position, the at least one first panel having a first combustion chamber surface and a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, the first rail joins the first combustion chamber surface at a first angle α; and
at least one second panel mounted to the interior surface at a second position and axially adjacent to the at least one first panel, the at least one second panel having a second combustion chamber surface and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell, the second rail joins the second combustion chamber surface at a second angle β,
wherein the first rail and the second rail are proximal to each other and define a circumferentially extending gap therebetween, and
wherein at least one of the first angle α or the second angle β is an acute angle,

wherein:
the at least one first panel comprises a plurality of first panels, wherein the plurality of first panels define a first axially extending gap between two circumferentially adjacent first panels, and each first panel of the two circumferentially adjacent first panels have respective axially extending rails that extend from their respective first combustion chamber surfaces toward the interior surface, wherein one rail of the respective axially extending rails of the two circumferentially adjacent first panels is configured at an acute angle relative to the first combustion chamber surface of the respective first panel the one rail extends from; and/or
the at least one second panel comprises a plurality of second panels, wherein the plurality of second panels define a second axially extending gap between two circumferentially adjacent second panels, and each second panel of the two circumferentially adjacent second panels have respective axially extending rails that extend from their respective second combustion chamber surfaces toward the interior surface, wherein one rail of the respective axially extending rails of the two circumferentially adjacent second panels is configured at an acute angle relative to the second combustion chamber surface of the respective second panel the one rail extends from.

6. The gas turbine engine of claim 5 , wherein both of the first angle α and the second angle β are acute angles.

7. The gas turbine engine of claim 5 , wherein the first rail and the second rail are parallel to each other.

8. The gas turbine engine of claim 5 , wherein the other of the at least one of the first angle α and the second angle β is configured at a 90° angle.

9. A method of manufacturing a combustor of a gas turbine engine comprising:
mounting at least one first panel to an interior surface of a combustion chamber shell at a first position, the at least one first panel having a first combustion chamber surface and a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, the first rail joins the first combustion chamber surface at a first angle α; and
mounting at least one second panel to the interior surface at a second position axially adjacent to the at least one first panel, the at least one second panel having a second combustion chamber surface and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell, the second rail joins the second combustion chamber surface at a second angle β,
wherein the first rail and the second rail are proximal to each other and define a circumferentially extending gap therebetween, and wherein at least one of the first angle α or the second angle β is an acute angle,
wherein:
the at least one first panel comprises a plurality of first panels, wherein the plurality of first panels define a first axially extending gap between two circumferentially adjacent first panels, and each first panel of the two circumferentially adjacent first panels have respective axially extending rails that extend from their respective first combustion chamber surfaces toward the interior surface, wherein one rail of the respective axially extending rails of the two circumferentially adjacent first panels is configured at an acute angle relative to the first combustion chamber surface of the respective first panel the one rail extends from; and/or
the at least one second panel comprises a plurality of second panels, wherein the plurality of second panels define a second axially extending gap between two circumferentially adjacent second panels, and each second panel of the two circumferentially adjacent second panels have respective axially extending rails that extend from th

Assignees

• United Technologies Corp

Inventors

• Tu John S
• Hoke James B
• Eastwood Jonathan Jeffery
• Low Kevin Joseph
• Bradshaw Sean D

Classifications

• F23R2900/00012

  Details of sealing devices · CPC title

• F23R3/26

  Controlling the air flow · CPC title

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title