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

Patent metadata

Field	Value
Publication number	US-2018363902-A1
Application number	US-201715623808-A
Country	US
Kind code	A1
Filing date	Jun 15, 2017
Priority date	Jun 15, 2017
Publication date	Dec 20, 2018
Grant date	—

Abstract

A liner panel for use in a combustor of a gas turbine engine, the liner panel including a cold side; and a rail that extends from the cold side, the rail includes a first diffusion interface passage surface and a second diffusion interface passage surface, the first diffusion interface passage surface angled with respect to the second diffusion interface passage surface.

First claim

What is claimed is:

1 . A liner panel for use in a combustor of a gas turbine engine, the liner panel comprising:
a cold side; and a rail that extends from the cold side, the rail includes a first diffusion interface passage surface and a second diffusion interface passage surface, the first diffusion interface passage surface angled with respect to the second diffusion interface passage surface.

2 . The liner panel as recited in claim 1 , wherein the first diffusion interface passage surface at least partially defines a pre-diffuser section and the second diffusion interface passage surface at least partially defines a diffuser section along one side of a diffusion interface passage axis.

3 . The liner panel as recited in claim 2 , wherein the diffuser section of the rail defines a height with respect to the cold side between 0.05 H-0.6 H, where H is the height of the rail.

4 . The liner panel as recited in claim 3 , wherein the diffuser section at least partially defines an expanding passage that extends at an angle between 1-15 degrees with respect to a surface that forms the pre-diffuser section.

5 . The liner panel as recited in claim 1 , wherein the liner panel is at least one of a forward liner panel, and an aft liner panel.

6 . The liner panel as recited in claim 1 , wherein the rail is a periphery rail that defines an edge of the liner panel.

7 . The liner panel as recited in claim 1 , wherein the rail includes a ramped end section.

8 . The liner panel as recited in claim 1 , wherein the rail is trapezoidal shaped.

9 . The liner panel as recited in claim 1 , wherein the rail is ramp shaped.

10 . A combustor for a gas turbine engine comprising:
a support shell; a first liner panel mounted to the support shell, the first liner panel including a first rail that extends from a cold side of the first liner panel, the first rail includes a diffusion interface passage surface that is non-perpendicular to the hot side; and a second liner panel mounted to the support shell, the second liner panel including a second rail that extends from a cold side of the second liner panel, the second rail adjacent to the first rail to at least partially form a diffusion interface passage.

11 . The combustor as recited in claim 10 , further comprising a multiple of studs that extend from the first liner panel, the first liner panel mounted to the support shell via the multiple of studs, and a multiple of studs that extend from the second liner panel, the second liner panel mounted to the support shell via the multiple of studs.

12 . The combustor as recited in claim 10 , wherein the first liner panel is a forward liner panel.

13 . The combustor as recited in claim 10 , wherein the second liner panel is an aft liner panel.

14 . The combustor as recited in claim 10 , wherein the diffusion interface passage defines a diffusion interface passage axis oriented at 30 - 90 degrees with respect to a hot side of the second liner panel.

15 . The combustor as recited in claim 14 , wherein the diffusion interface passage defines a pre-diffuser section and a diffuser section along the diffusion interface passage axis.

16 . The combustor as recited in claim 15 , wherein the diffuser section of the first rail defines a height with respect to a cold side of the first liner panel between 0.05 H-0.6 H, where H is the height of the first rail.

17 . The combustor as recited in claim 16 , wherein the diffuser section of the first rail defines an expanding passage oriented at an angle between 1-15 degrees from an aft diffusion interface passage surface of the first rail.

18 . The combustor as recited in claim 15 , wherein the diffuser section of the second rail defines a height with respect to a cold side of the second liner panel between 0.05 H-0.6 H, where H is the height of the second rail.

19 . The combustor as recited in claim 18 , wherein the diffuser section of the second rail defines an expanding passage oriented at an angle between 1-15 degrees from a forward diffusion interface passage surface of the second rail.

20 . The combustor as recited in claim 15 , wherein the first rail is trapezoidal shaped.

Assignees

• United Technologies Corp

Inventors

• Peters Donald W
• Quach San
• Morton Jeffrey T
• Parekh Matthew D

Classifications

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• F02C7/18

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

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2220/32

  in gas turbines · CPC title