Turbine cooling apparatus
AssigneeSolar Turbines Incorporated
InventorsLuzeng Zhang, Xubin Gu, Juan Yin, Hee Koo Moon
Life of this patent
Estimating the term…
Abstract
A turbine blade for a gas turbine engine is disclosed. The turbine blade can include at least one internal cooling path, and an internal vane disposed in the at least one internal cooling path. The internal vane can include a central portion, a first leg extending in a first direction from the central portion, and a second leg extending in a second direction from the central portion. The central portion can have a thickness greater than a thickness of the first leg or a thickness of the second leg.
Claims15
A turbine blade for a gas turbine engine, comprising:
- at least one internal cooling path;
- and
- a first vane disposed at a first location in the at least one internal cooling path;
- and
- a second vane disposed at a second location in the at least one internal cooling path downstream from the first location;
- wherein each of the first vane and the second vane includes:
- a central portion;
- a first leg extending in a first direction from the central portion;
- and
- a second leg extending in a second direction from the central portion, wherein the central portion has a thickness greater than a thickness of the first leg or a thickness of the second leg, wherein the first vane is disposed adjacent a first corner of a wall forming the at least one internal cooling path, and the second vane is disposed adjacent a second corner of the wall forming the at least one internal cooling path, wherein a cross-sectional area of the first vane is greatest at a portion of the first vane closest to the first corner of the wall, and wherein a cross-sectional area of the second vane is greatest at a portion of the second vane closest to the second corner of the wall.
A turbine blade for a gas turbine engine, comprising:
- at least one internal cooling path;
- and
- a first vane disposed at a first location in the at least one internal cooling path;
- and
- a second vane disposed at a second location in the at least one internal cooling path downstream from the first location;
- wherein each of the first vane and the second vane includes:
- a central portion;
- and
- a leg extending from the central portion, wherein the central portion has a thickness greater than a thickness of the leg, wherein the first vane is disposed adjacent a first corner of a wall forming the at least one internal cooling path, and the second vane is disposed adjacent a second corner of the wall forming the at least one internal cooling path, wherein a cross-sectional area of the first vane is greatest at a portion of the first vane closest to the first corner of the wall, and wherein a cross-sectional area of the second vane is greatest at a portion of the second vane closest to the second corner of the wall.
A turbine blade for a gas turbine engine, comprising:
- an internal cooling path;
- a first vane disposed at a first location in the cooling path;
- and
- a second vane disposed at a second location in the cooling path downstream from the first location, wherein the first and second vane each taper from a central thickness to a first thickness, and from the central thickness to a second thickness, wherein the first thickness is disposed upstream from the central thickness in the cooling path, and wherein the central thickness is disposed upstream from the second thickness in the cooling path, wherein the first vane is disposed adjacent a first corner of a wall forming the cooling path, and the second vane is disposed adjacent a second corner of the wall forming the cooling path, wherein a cross-sectional area of the first vane is greatest at a portion of the first vane closest to the first corner of the wall, and wherein a cross-sectional area of the second vane is greatest at a portion of the second vane closest to the second corner of the wall.
Dependencies are inferred from the claim text.