Turbine engine with a blade assembly having cooling conduits
AssigneeGeneral Electric Company
InventorsThomas P. Warburg, Zachary R. Noeth, Kelli Marie Fishback, Marie Myers, Zachary Daniel Webster, Kurt Thomas Whittington
Life of this patent
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Abstract
A gas turbine engine having a blade assembly with a platform, an airfoil, and a shank. The airfoil has a plurality of cooling conduits, and the shank has a plurality of inlet passages to provide cooling fluid to the cooling conduits in the airfoil. The cooling fluid is vented through a plurality of cooling holes along the trailing edge of the airfoil. The blade assembly has specific geometries that improve durability.
Claims16
A gas turbine engine, comprising:
- an engine core configured to generate a redline exhaust gas temperature (EGT) in a range of 988 degrees Celsius (° C.) to 1120° C. and having a redline core speed (CS) in a range of 306 Hertz to 353 Hertz, the engine core extending along an engine centerline and including:
- a compressor section;
- a combustor;
- and
- a turbine section, the turbine section including a blade assembly rotatable about the engine centerline, the blade assembly comprising:
- a platform having an upper surface and a lower surface;
- an airfoil coupled to the upper surface of the platform, the airfoil having an outer wall defining an exterior surface, the exterior surface defining a pressure side and a suction side, the outer wall extending between a leading-edge and a trailing-edge;
- a shank coupled to the lower surface, the shank having a base defining a base plane;
- a leading-edge inlet passage located within the shank, the leading-edge inlet passage defining a leading-edge cross-sectional area (LEA), wherein the leading-edge cross-sectional area (LEA) is from 0.000014 meters squared (m2) to 0.000018 m2;
- and
- a plurality of cooling conduits located within the airfoil, the plurality of cooling conduits including a group of suction side cooling conduits proximate the suction side, the group of suction side cooling conduits collectively defining a suction side cross-sectional area (SSA), wherein the suction side cross-sectional area (SSA) is from 0.000005 m2 to 0.00000945 m2, and wherein,
- 0.145
- ≤
- (
- 100
- *
- (
- 0.005
- m
- 2
- SSA
-
- (
- m
- 2
- )
- )
- 2
-
- (
- LEA
-
- (
- m
- 2
- )
- 20
-
- m
- 2
- )
- -
- 19.5
- )
- *
- (
- 1.7
- *
- (
- Redline
-
- EGT
-
- (
- °
-
- C
- .
- )
- 1054
-
- °
-
- C
- .
- )
- *
- (
- Redline
-
- CS
-
- (
- Hz
- )
- 323.183
- Hz
- )
- )
- ≤
- 139.105
- .
A blade assembly for a gas turbine engine having an engine core configured to generate a redline exhaust gas temperature (EGT) in a range of 988 degrees Celsius (° C.) to 1120° C. and having a redline core speed (CS) in a range of 306 Hertz to 353 Hertz, the blade assembly to be connected to the engine core and rotatable about an engine centerline of the engine core, the blade assembly comprising:
- a platform having an upper surface and a lower surface;
- an airfoil coupled to the upper surface of the platform, the airfoil having an outer wall defining an exterior surface, the exterior surface defining a pressure side and a suction side, the outer wall extending between a leading-edge and a trailing-edge;
- a shank coupled to the lower surface, the shank having a base defining a base plane;
- a leading-edge inlet passage located within the shank, the leading-edge inlet passage defining a leading-edge cross-sectional area (LEA), wherein the leading-edge cross-sectional area (LEA) is from 0.000014 meters squared (m2) to 0.000018 m2;
- and
- a plurality of cooling conduits located within the airfoil, the plurality of cooling conduits including a group of suction side cooling conduits proximate the suction side, the group of suction side cooling conduits collectively defining a suction side cross-sectional area (SSA), wherein the suction side cross-sectional area (SSA) is from 0.000005 m2 to 0.00000945 m2, and wherein,
- 0.145
- ≤
- (
- 100
- *
- (
- 0.005
- m
- 2
- SSA
-
- (
- m
- 2
- )
- )
- 2
-
- (
- LEA
-
- (
- m
- 2
- )
- 20
-
- m
- 2
- )
- -
- 19.5
- )
- *
- (
- 1.7
- *
- (
- Redline
-
- EGT
-
- (
- °
-
- C
- .
- )
- 1054
-
- °
-
- C
- .
- )
- *
- (
- Redline
-
- CS
-
- (
- Hz
- )
- 323.183
- Hz
- )
- )
- ≤
- 139.105
- .
Dependencies are inferred from the claim text.