Combustor panel configuration with skewed side walls
AssigneeUnited Technologies Corporation
InventorsSan Quach, Jeremy Styborski, Caroline Karanian
Life of this patent
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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.
Claims20
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;
- and
- a first liner panel side edge between the liner panel aft edge and the liner panel forward 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.
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;
- and
- a first liner panel side edge between the liner panel aft edge and the liner panel forward 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.
A forward liner panel for use in a combustor of a gas turbine engine, the forward liner panel comprising:
- 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,
- 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.
Dependencies are inferred from the claim text.