Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-10830434-B2
Application number	US-201715440677-A
Country	US
Kind code	B2
Filing date	Feb 23, 2017
Priority date	Feb 23, 2017
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

Abstract

A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel such that the rail is non-perpendicular to the cold side and includes a concave surface to at least partially form a curved interface passage; and a second liner panel mounted to the support shell via a multiple of studs, the first liner panel including a second rail that extends from a cold side of the second liner panel and includes a convex surface to at least partially form the curved interface passage.

First claim

What is claimed is:

1. A combustor for a gas turbine engine comprising:
a support shell that defines a support shell axis;
a forward liner panel that defines a forward liner panel axis parallel to the support shell axis, the forward liner panel mounted to the support shell via a multiple of studs, the forward liner panel comprising an aft circumferential rail that extends from a cold side of the forward liner panel toward the support shell to a distal end of the aft circumferential rail that is spaced from the support shell by a forward gap, the aft circumferential rail comprises a concave surface to at least partially form a curved interface passage; and
an aft liner panel that defines an aft liner panel axis parallel to the support shell axis, the aft liner panel mounted to the support shell via a multiple of studs, the aft liner panel comprising a forward circumferential rail that extends from a cold side of the aft liner panel toward the support shell to a distal end of the forward circumferential rail that is spaced from the support shell by an aft gap, the forward circumferential rail comprises a convex surface to at least partially form the curved interface passage, wherein the curved interface passage is formed about a single radius from adjacent to the support shell toward a combustion chamber defined at a hot side of the forward liner panel and the aft liner panel.

2. The combustor as recited in claim 1 , wherein the curved interface passage has at least a segment wherein spacing between the aft rail and the forward rail is constant.

3. A combustor for a gas turbine engine comprising:
a linear support shell that defines a support shell axis;
a forward liner panel that defines a forward liner panel axis parallel to the support shell axis, the forward liner panel mounted to the support shell via a multiple of studs, the forward liner panel comprising an aft circumferential rail that extends from a cold side of the forward liner panel such that a distal end is adjacent to and spaced from the linear support shell by a forward gap, the aft circumferential rail defining a concave surface; and
an aft liner panel that defines an aft liner panel axis parallel to the support shell axis, the aft liner panel mounted to the support shell via a multiple of studs, the aft liner panel comprising a forward circumferential rail adjacent to the aft circumferential rail, the forward circumferential rail extends from a cold side of the aft liner panel such that a distal end is adjacent to and spaced from the linear support shell by an aft gap, the forward circumferential rail having a convexsurface, the concave and convex surfaces facing each other to define a curved interface passage, the curved interface passage formed about a single radius from adjacent to the linear support shell toward a combustion chamber defined at a hot side of the forward liner panel and the aft liner panel.

4. The combustor as recited in claim 3 , wherein the curved interface passage has a segment wherein spacing between the aft rail and the forward rail is constant.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Quach San
• Morton Jeffrey T
• Parekh Matthew D

Classifications

• F23R3/002 Primary

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

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• Y02T50/60

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

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title