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US 2023/0399951 A1Published application
Gas turbine engine with an airfoil
AssigneeGeneral Electric Company
InventorsRathakrishnan Bhaskaran, Thomas W. Vandeputte
Life of this patent
Estimating the term…
Abstract
A turbine engine includes a compressor section, a combustion section, and a turbine section. Fuel combusted in the combustion section drive stages of airfoils in the turbine section to drive the compressor section. The airfoils can include a geometry near or at the trailing edge with a linear portion provided between the pressure side and a first curved portion, to reduce shock generated in the wake of the airfoils.
Claims23
A gas turbine engine comprising:
- a compressor section, a combustion section, and a turbine section in serial flow arrangement;
- and
- an airfoil including an outer wall bounding an interior, the outer wall comprising:
- a leading edge structure defining a leading edge line;
- a trailing edge structure spaced from the leading edge structure and defining a trailing edge line, with a camber line defined between the leading edge line and the trailing edge line;
- a pressure side extending between the leading edge structure and the trailing edge structure;
- a suction side extending between the leading edge structure and the trailing edge structure;
- wherein the trailing edge structure comprises:
- a linear portion extending from the pressure side toward the trailing edge line;
- a first curved portion extending between the linear portion and the trailing edge line;
- a second curved portion extending between the suction side and the trailing edge line;
- and
- a virtual diameter defined between the second curved portion and a junction where the pressure side meet the linear portion;
- wherein the virtual diameter defines a first virtual circle with a first centerpoint;
- wherein a radius of curvature, defined where the first curved portion and the second curved portion meet at the trailing edge line, defines a second virtual circle with a second centerpoint;
- wherein a virtual line is defined by the first centerpoint and the second centerpoint;
- wherein a tangent line is defined tangent to the camber line and extending from the first centerpoint, with the tangent line arranged at an angle relative to the virtual line;
- and
- wherein the linear portion includes a length and a ratio of the length to the virtual diameter is between 0.1 and 1.3.
16 more elements
(canceled)
14-17. (canceled)
An airfoil for a turbine engine, the airfoil comprising:
- an outer wall bounding an interior, the outer wall defining a pressure side and a suction side and extending between a leading edge structure and a trailing edge structure with a trailing edge line, and the outer wall defining a camber line, the trailing edge structure comprising:
- a linear portion extending from the pressure side toward the trailing edge line;
- a first curved portion extending between the linear portion and the trailing edge line;
- and
- a second curved portion extending between the suction side and the trailing edge line;
- wherein a virtual diameter can be defined extending between a junction of the linear portion and the first curved portion, and the second curved portion, and wherein the virtual diameter defines a first virtual circle having a first virtual centerpoint;
- wherein a radius of curvature for the first curved portion and the second curved portion at the trailing edge line defines a second virtual circle having a second virtual centerpoint and a second virtual diameter, and wherein a virtual line can be defined by the first virtual centerpoint and the second virtual centerpoint;
- wherein a tangent line is defined tangent to the camber line where the virtual line meets the camber line, and wherein an angle can be defined between the tangent line and the virtual line;
- and
- wherein a ratio of a length of the linear portion to a length of the virtual diameter is between 0.1 and 1.3.
7 more elements
(canceled)
An airfoil for a turbine engine, the airfoil comprising:
- an outer wall bounding an interior, the outer wall defining a pressure side and a suction side and extending between a leading edge structure and a trailing edge structure with a trailing edge line, and the outer wall defining a camber line, the trailing edge structure comprising:
- a linear portion extending from the pressure side toward the trailing edge line;
- a first curved portion extending between the linear portion and the trailing edge line;
- and
- a second curved portion extending between the suction side and the trailing edge line;
- wherein a first virtual diameter can be defined extending between a junction of the linear portion and the first curved portion, and the second curved portion, and wherein the first virtual diameter defines a first virtual circle having a first virtual centerpoint;
- wherein a radius of curvature for the first curved portion and the second curved portion at the trailing edge line defines a second virtual circle having a second virtual centerpoint and a second virtual diameter, and wherein a virtual line can be defined by the first virtual centerpoint and the second virtual centerpoint;
- wherein a tangent line is defined tangent to the camber line where the virtual line meets the camber line, and wherein an angle can be defined between the tangent line and the virtual line;
- and
- wherein, at least one of:
- a ratio of a length of the linear portion to a length of the first virtual diameter is between 0.1 and 1.3,
- a ratio of the first virtual diameter to the second virtual diameter is between 0.2 and 1.0,
- the angle between the tangent line and the virtual line is between 5-degrees and 25-degrees, or
- a ratio of a length of the virtual line to a length of the virtual diameter is between 0.5 and 1.25.
11 more elements
Dependencies are inferred from the claim text.