Back to results
US 9,429,323 B2Granted
Combustion liner with bias effusion cooling
AssigneeGeneral Electric Technology GmbH
InventorsBrian Richardson, Khalid Oumejjoud, John Cutright, Nikki McMullen, Peter John Stuttaford, Richard Parker, Sumit Soni
Life of this patent
Estimating the term…
Abstract
A system and method for improving the cooling to a portion of a combustion liner of a gas turbine combustor is disclosed. The combustion liner is cooled by supplying air through a plurality of cooling holes arranged in axially spaced rows in an upper and lower portion of the liner. The cooling holes are spaced accordingly so as to direct additional cooling flow to an area of the combustion liner not receiving sufficient flow due to maldistributions of air from the compressor discharge.
Claims20
A combustion liner for a gas turbine combustor comprising:
- a generally annular body having an inner wall, an outer wall spaced a distance from the inner wall, an inlet end, and an opposing outlet end, the generally annular body also having a plane extending through
- a centerline to bisect the generally annular body and define an upper portion and a lower portion of the generally annular body;
- a seal positioned along the outer wall proximate the outlet end;
- the upper portion having a plurality of cooling holes, the upper portion having a lower boundary defined by the plane extending through the centerline, a left boundary defined by a column of one or more cooling holes most near to the inlet end, and a right boundary defined by a column of one or more cooling holes most near to the outlet end;
- the lower portion having a plurality of cooling holes, the lower portion having an upper boundary defined by the plane extending through the centerline, a left boundary defined by a column of one or more cooling holes most near to the inlet end, and a right boundary defined by a column of one or more cooling holes most near to the outlet end, wherein the lower portion comprises a section of the generally annular body that is positioned closer to an engine axis upon installation of the combustion liner in the gas turbine engine;
- and
- wherein the entire lower portion of the generally annular body has a higher concentration of cooling holes than the entire upper portion of the generally annular body.
4 more elements
A cooling pattern for a combustion liner having a generally annular body, the cooling pattern comprising:
- a first set of axially spaced rows, the first set of axially spaced rows spaced a first distance apart;
- a second set of axially spaced rows, the second set of axially spaced rows spaced a second distance apart;
- a third set of axially spaced rows, the third set of axially spaced rows spaced a third distance apart;
- an upper half having a lower boundary defined by a plane extending through a centerline, a left boundary defined by a left-most row in the first set of axially spaced rows, and a right boundary defined by a right-most row in the first set of axially spaced rows;
- a lower half having an upper boundary defined by the plane extending through the centerline, a left boundary defined by a left-most row in the second set of axially spaced rows, and a right boundary defined by a right-most row in the second set of axially spaced rows;
- and
- wherein the second set of axially spaced rows and the third set of axially spaced rows are arranged such that of the entire lower half of the combustion liner has a higher concentration of cooling holes than the entire upper half of the combustion liner.
4 more elements
A method of providing increased cooling to a portion of a combustion liner comprising:
- providing a generally annular body having a plane extending through a centerline, wherein the plane extending through the centerline bisects the generally annular body and defines an upper portion and a lower portion, where the lower portion is a section of the combustion liner positioned closest to the centerline of a gas turbine engine when the combustion liner is installed in the gas turbine engine;
- providing a plurality of cooling holes in the upper portion of the combustion liner, the upper portion having a lower boundary defined by the plane extending through the centerline, a left boundary defined by a column of one or more cooling holes most near to the inlet end, and a right boundary defined by a column of one or more cooling holes most near to the outlet end:
- providing a plurality of cooling holes in the lower portion of the combustion liner, the lower portion having an upper boundary defined by the plane extending through the centerline:
- a left boundary defined by a left-most row in the second set of axially spaced rows, and a right boundary defined by a right-most row in the second set of axially spaced rows;
- and
- wherein the plurality of cooling holes are arranged such that the entire lower portion of the generally annular body has a higher concentration of cooling holes than the entire upper portion of the generally annular body.
3 more elements
Dependencies are inferred from the claim text.