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US 11,306,918 B2Granted
Turbulator geometry for a combustion liner
AssigneeChromalloy Gas Turbine Corporation
InventorsDaniel L. Folkers, Vincent C. Martling, Zhenhua Xiao, John Bacile
Life of this patent
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Abstract
A heat transfer mechanism is provided comprising a plurality of turbulators located along a surface of a body, such as a combustion liner. The turbulators have a first side with a first ramp angle, a second side with a second ramp angle, a height, and a base width, where the base width is a function of the height and where the turbulators are spaced an axial distance apart that is a function of the turbulator height.
Claims19
A combustion liner comprising:
- a generally annular body having a first cylindrical portion, a conical portion, and a second cylindrical portion;
- a cooling passage formed around the first cylindrical portion;
- an inlet proximate the first cylindrical portion and an outlet proximate the second cylindrical portion;
- a first plurality of discrete turbulators located along an outer surface of the first cylindrical portion;
- and
- a second plurality of discrete turbulators located along an outer surface of the conical portion;
- wherein:
- each of the first plurality of turbulators are a band with a uniform profile that extends entirely about a circumference of the first cylindrical portion;
- each of the second plurality of turbulators are a band with a uniform profile that extends entirely about a circumference of the conical portion;
- each of the first plurality of turbulators have a first side extending at a first ramp angle from the outer surface of the first cylindrical portion, a second side extending at a second ramp angle from the outer surface of the first cylindrical portion, a height, and a base width, each of the first plurality of turbulators first and second ramp angles being an acute angle measured from the first cylindrical portion outer surface, wherein a height of one turbulator of the first plurality of turbulators is based on a height of the cooling passage, and an axial spacing of the first plurality of turbulators is based on both the height and a streamwise length of the cooling passage;
- each of the second plurality of turbulators have a first side extending from the outer surface of the conical portion at a first ramp angle, a second side extending from the outer surface of the conical portion at a second ramp angle, a height, and a base width, each of the second plurality of turbulators first and second ramp angles being an acute angle measured from the conical portion outer surface.
8 more elements
A heat transfer mechanism for a gas turbine component, the heat transfer mechanism comprising:
- a body having a first cylindrical portion, a conical portion, and a second cylindrical portion;
- an inlet proximate the first cylindrical portion and an outlet proximate the second cylindrical portion;
- a cooling passage formed around each of the first cylindrical portion, and the second cylindrical portion;
- a first plurality of discrete turbulators located along an outer surface of the first cylindrical portion, each of the first plurality of turbulators having a uniform profile and being a band which extends entirely about a circumference of the first cylindrical portion;
- a second plurality of discrete turbulators located along an outer surface of the conical portion, each of the second plurality of turbulators having a uniform profile and being a band which extends entirely about a circumference of the conical portion;
- wherein a height of one turbulator of the second plurality of turbulators is based on a height of the cooling passage, and an axial spacing of the first plurality of turbulators is based on both the height and a streamwise length of the cooling passage.
3 more elements
A method of providing a heat transfer mechanism comprising:
- providing a body having a surface for the heat transfer mechanism, the body comprising a first cylindrical portion, a conical portion, a second cylindrical portion, and a cooling passage formed around the first cylindrical portion;
- and
- forming the heat transfer mechanism in the surface of the first cylindrical portion and the conical portion, where the heat transfer mechanism comprises a plurality of discrete turbulators, the plurality of turbulators each comprising:
- a band having a uniform profile extending entirely about a circumference of the body;
- a first side with a first ramp angle measured from the surface;
- a second side with a second ramp angle measured from the surface;
- the first side connected to the second side at a peak, the peak having a height and a full round tip radius;
- and
- a base having a base width;
- wherein a height of one of the plurality of turbulators is based on a height of the cooling passage, and an axial spacing of the plurality of turbulators is based on both the height and a streamwise length of the cooling passage.
7 more elements
Dependencies are inferred from the claim text.