US 2025/0154873 A1Published application

Turbine engine with a blade assembly having cooling conduits

AssigneeGeneral Electric Company

InventorsZachary R. Noeth, Thomas P. Warburg, Zachary Daniel Webster, Kelli Marie Fishback, Marie Myers, Kurt Thomas Whittington

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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

Claims20

Dependent claims

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., 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 including:
a platform having an upper surface and a lower surface, the platform having a stator rotor seal with an upper edge having a radius of curvature defined as a stator rotor seal radius (SRSR), wherein the stator rotor seal radius (SRSR) is 0.224 to 0.239 meters;
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;
and
a plurality of cooling conduits located within the airfoil, the plurality of cooling conduits including:
a first cooling conduit located closest to the trailing-edge and defining a trailing-edge area (TEA), wherein the trailing-edge area (TEA) is from 0.0000056 square-meters (m2) to 0.00001 m2;
and
a second cooling conduit next to the first cooling conduit and defining a secondary area (SA), wherein the secondary area (SA) is from 0.000002 m2 to 0.0000048 m2, and
wherein,
43.951
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[
100
*
(
T
⁢
E
⁢
A
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(
m
2
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0.005
m
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2
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(
S
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m
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0.005
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2
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[
0.17
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Redline
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500
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1
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≤
9
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7
⁢
6
.
3
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8
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8
.

105 more elements

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., 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, the platform having a stator rotor seal with an upper edge having a radius of curvature defined as a stator rotor seal radius (SRSR), wherein the stator rotor seal radius (SRSR) is 0.224 to 0.239 meters;
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;
and
a plurality of cooling conduits located within the airfoil, the plurality of cooling conduits including:
a first cooling conduit located closest to the trailing-edge and defining a trailing-edge area (TEA), wherein the trailing-edge area (TEA) is from 0.0000056 square-meters (m2) to 0.00001 m2;
and
a second cooling conduit next to the first cooling conduit and defining a secondary area (SA), wherein the secondary area (SA) is from 0.000002 m2 to 0.0000048 m2, and wherein,
43.951
≤
[
100
*
(
T
⁢
E
⁢
A
⁢
1
⁢
(
m
2
)
0.005
m
2
)
-
2
⁢
(
S
⁢
A
⁢
(
m
2
)
0.005
m
2
)
2
]
[
0.17
*
(
Redline
⁢
E
⁢
G
⁢
T
⁢
(
°
⁢
C
.
)
500
⁢
°
⁢
C
.
)
⁢
(
S
⁢
R
⁢
S
⁢
R
⁢
(
m
)
1
⁢
m
)
]
≤
9
⁢
7
⁢
6
.
3
⁢
8
⁢
8
.

101 more elements

Dependencies are inferred from the claim text.

Facts

Application: 18/941,684Filed 8 Nov 2024
Priority: 10 Nov 2023
Published: 15 May 2025
Term ends: Not estimatedThe source records don’t support an estimate.

Classification15 codes

F01D 5/186
Hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades: film cooling
F01D 5/187
Hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades: convection cooling
F01D 5/147
Form or construction: construction, i.e. structural features, e.g. of weight-saving hollow blades
F01D 5/18
Form or construction: hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades

Family

Application63/597,828Us provisional application · filed 10 Nov 2023
Application63/686,037Us provisional application · filed 22 Aug 2024
US 12,378,889 B2Related patent
US 2025/0154873 A1This patent

From the US filing history. Foreign family members aren’t listed.

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