Combustor for a gas turbine engine including a liner having a looped feature
AssigneeGeneral Electric Company
InventorsRavindra Shankar Ganiger, Hiranya Kumar Nath, Daniel J. Kirtley, Shai Birmaher, Pradeep Naik
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Abstract
A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.
Claims20
A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising:
- a liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a dilution slot extending through the liner and a looped feature extending outward from an outer surface of the liner, the looped feature having:
- a first portion extending generally in the longitudinal direction;
- a second portion positioned radially outward and substantially parallel to the first portion;
- a radially extending portion coupling the liner to the second portion, the radially extending portion extending through the dilution slot from a location radially outward of the liner to a location radially inward of the liner;
- and
- a radially outer window extending through the second portion, the radially outer window configured to pass cooling medium to the combustion chamber.
A liner for a combustor of a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the liner comprising:
- an annular body configured to at least partially define a combustion chamber of the combustor, wherein the annular body comprises:
- a dilution slot extending to the combustion chamber;
- and
- a looped feature extending outward from an outer surface of the liner, the looped feature configured to absorb deflection during thermal expansion of the liner, the looped feature having:
- a first portion extending generally in the longitudinal direction;
- a second portion positioned radially outward and substantially parallel to the first portion;
- a radially extending portion coupling the liner to the second portion, the radially extending portion extending through the dilution slot from a location radially outward of the liner to a location radially inward of the liner;
- and
- a radially outer window extending through the second portion, the radially outer window configured to pass cooling medium to the combustion chamber.
Dependencies are inferred from the claim text.