Swept combustor liner panels for gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-2016265771-A1
Application number	US-201415031070-A
Country	US
Kind code	A1
Filing date	Nov 18, 2014
Priority date	Nov 18, 2013
Publication date	Sep 15, 2016
Grant date	—

Abstract

A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge. The liner panel also includes a second liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first and the second liner panel side edges are non-perpendicular to the liner panel forward and aft edge edges.

First claim

What is claimed:

1 . A liner panel for use in a combustor of a gas turbine engine, the liner panel comprising:
a first liner panel side edge between a liner panel aft edge and a liner panel forward edge; and a second liner panel side edge between the liner panel aft edge and the liner panel forward edge, the first and second liner panel side edges non-perpendicular to the liner panel forward and aft edge edges.

2 . The liner panel as recited in claim 1 , wherein the first liner panel side edge, the second liner panel side edge, the liner panel forward edge and the liner panel aft edge generally define a parallelogram.

3 . The liner panel as recited in claim 1 , further comprising a multiple of studs which extend from the liner panel.

4 . The liner panel as recited in claim 1 , wherein the first liner panel side edge and the second liner panel side edge are parallel.

5 . The liner panel as recited in claim 1 , wherein the liner panel forward edge and the liner panel aft edge are parallel.

6 . A wall assembly for use in a combustor of a gas turbine engine, the wall assembly comprising:
a support shell arranged around an engine central longitudinal axis; and a multiple of liner panels mounted to the support shell, the multiple of liner panels defining a multiple of liner panel gaps around the engine central longitudinal axis with at least one of the multiple of liner panel gaps swept with respect to the axis.

7 . The wall assembly as recited in claim 6 , wherein each of the multiple of liner panel gaps are swept with respect to the engine central longitudinal axis.

8 . The wall assembly as recited in claim 6 , wherein each of the multiple of liner panel gaps are swept about 10-45 degrees with respect to the engine central longitudinal axis.

9 . The wall assembly as recited in claim 6 , wherein each of the multiple of liner panel gaps are swept about 20 degrees with respect to the engine central longitudinal axis.

10 . The wall assembly as recited in claim 6 , wherein each the multiple of liner panels defines a parallelogram.

11 . The wall assembly as recited in claim 6 , wherein the multiple of liner panels are outboard of the support shell with respect to the engine central longitudinal axis.

12 . The wall assembly as recited in claim 6 , wherein the multiple of liner panels are inboard of the support shell with respect to the engine central longitudinal axis.

13 . A combustor of a gas turbine engine, the combustor comprising:
a multiple of first liner panels mounted to a first support shell around an engine central longitudinal axis, the multiple of first liner panels defining a multiple of first liner panel gaps around the engine central longitudinal axis, and the multiple of first liner panel gaps swept with respect to the axis.

14 . The combustor as recited in claim 13 , wherein the multiple of first liner panel gaps include a multiple of outer liner panel gaps and a multiple of inner liner panel gaps, the outer liner panel gaps swept in a direction opposite that of the multiple of inner liner panel gaps.

15 . The combustor as recited in claim 14 , wherein the multiple of outer liner panel gaps and the multiple of inner liner panel gaps are swept with to a swirler flow direction.

16 . The combustor as recited in claim 14 , wherein the multiple of outer liner panel gaps and the multiple of inner liner panel gaps are swept transverse to a swirler flow direction.

17 . The combustor as recited in claim 13 , wherein the swirler flow direction is generally transverse to the multiple of first liner panel gaps.

18 . The combustor as recited in claim 13 , wherein each of the multiple of first liner panels defines a parallelogram.

19 . The combustor as recited in claim 13 , wherein the multiple of first liner panel gaps include a multiple of outer liner panel gaps and a multiple of inner liner panel gaps, and the outer liner panel gaps are swept in a direction of the multiple of inner liner panel gaps.

20 . A combustor of a gas turbine engine, the combustor comprising:
a multiple of first liner panels mounted to a first support shell around an engine central longitudinal axis, the multiple of first liner panels defining a multiple of first liner panel gaps around the engine central longitudinal axis, and the multiple of first liner panel gaps swept with respect to a swirler flow direction.

21 . The combustor as recited in claim 20 , wherein the multiple of first liner panel gaps include a multiple of outer liner panel gaps and a multiple of inner liner panel gaps, the outer liner panel gaps are swept in a direction opposite that of the multiple of inner liner panel gaps, and the multiple of outer liner panel gaps and the multiple of inner liner panel gaps are swept with to a swirler flow direction.

Assignees

• United Technologies Corp

Inventors

• Max Seth A
• Low Kevin J

Classifications

• F23R3/002 Primary

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

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/58

  Cyclone or vortex type combustion chambers · CPC title