US 12,747,666 B2Granted

Turbine engine with a blade assembly having cooling holes

AssigneeGeneral Electric Company

InventorsEmily K. Langlois, Brian Patrick Peterson, Haidong Liu, Lauren Rose Watson, Daniel Endecott Osgood

Life of this patent

Estimating the term…

Abstract

A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A set of blades are circumferentially arranged in the turbine section and the compressor section. Each blade including cooling holes arranged in an overlapping region of the blade.

Claims12

Dependent claims

A turbine engine, comprising:

an engine core configured to generate an exhaust gas temperature (EGT) in a range of 980.1 and 1059.4 degrees Celsius (° C.) and a rotational speed (N2) in a range of 12511 to 13980.5 RPM, 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 configured to rotate about the engine centerline at the rotational speed (N2), wherein a radial axis is perpendicular to the engine centerline and aligned with a height dimension of the blade assembly, the blade assembly comprising:
a platform defining a platform plane;
an airfoil extending from the platform, the airfoil including:
a pressure side and a suction side and an exterior surface;
a leading edge and a trailing edge;
a root;
a tip defining a tip plane;
a cooling conduit;
a plurality of cooling holes in an overlapping region of the pressure side of the blade;
wherein an airfoil height (Hairfoil) is defined as a radial distance measured from the platform plane to the tip plane, wherein the airfoil height is in a range of 73.7 to 86.4 millimeters;
wherein the overlapping region of the pressure side of the blade is defined by:
a mid-region, wherein the mid-region is a region of the pressure side of the airfoil between a first radial plane and a second radial plane, wherein the first radial plane is arranged parallel to the tip plane and located at a first radial distance from the engine centerline, wherein the second radial plane is arranged parallel to the tip plane and located at a second radial distance from the engine centerline, and wherein the first radial distance is 0.369 meters and the second radial distance is 0.353 meters;
and
an aft region, wherein the a blade curve is defined as a line of intersection between the exterior surface of the pressure side and the second radial plane, wherein the blade curve extends between the leading edge and the trailing edge, wherein a curve point is defined at a distance of 68% of a length of the blade curve from the leading edge along the blade curve;
wherein an aft plane includes the curve point, is perpendicular to the second radial plane, and is perpendicular to the pressure side of the blade curve at the curve point, wherein the aft region is a region of the pressure side of the blade that is located between the aft plane and the trailing edge;
wherein each cooling hole in the plurality of cooling holes includes a cooling passage, each cooling passage extending between an inlet fluidly coupled to the cooling conduit and an outlet open to the exterior surface, the cooling passage defining a passage centerline;
wherein each cooling hole in the plurality of cooling holes includes a radial hole angle (RHA) defined between the second radial plane and the respective passage centerline;
wherein a radial hole angle average (RHAavg) is defined as an average of the radial hole angles (RHAs) for all cooling holes in the overlapping region, wherein the radial hole angle average (RHAavg) is in the range of 21.4 to 63.7 degrees;
and
wherein a minimum radial hole angle (RHAmin) is defined as a smallest radial hole angle of all the radial hole angles in the plurality of cooling holes, wherein the minimum radial hole angle (RHAmin) is in the range of 20.1 to 44.9 degrees;
wherein the exhaust gas temperature (EGT), the rotational speed (N2), the airfoil height (Hairfoil), and the radial hole angle average (RHAavg), define a first value (EQ1) by the following expression:
EQ
⁢
1
=
(
(
RHA
avg
15
⁢
°
)
+
3
.
7
⁢
5
⁢
(
H
airfoil
⁢
(
mm
)
73.7
mm
)
3
)
⁢
(
1
.
7
×
EGT
⁡
(
°
⁢
C
.
)
1000
⁢
°
⁢
C
.
)
⁢
(
1.2
×
13
,
000
⁢
RPM
N
⁢
2
⁢
(
RPM
)
)
,
wherein the exhaust gas temperature (EGT), the rotational speed (N2), and the minimum radial hole angle (RHAmin), define a second value (EQ2) by the following expression:
EQ
⁢
2
=
(
RHA
min
30
⁢
°
)
⁢
(
EGT
⁡
(
°
⁢
C
.
)
1000
⁢
°
⁢
C
.
)
⁢
(
13
,
000
⁢
RPM
N
⁢
2
⁢
(
RPM
)
)
,
and
wherein the first value (EQ1) is in the range of 9.87 to 22.7, and the second value (EQ2) is in the range of 0.61 to 1.64.

139 more elements

Dependencies are inferred from the claim text.

Facts

Application: 18/665,668Filed 16 May 2024 · us provisional application
Priority: 16 May 2023
Published: US 2026/0022640 A122 Jan 2026
Granted: 29 Sep 2026
Term ends: Not estimatedThe source records don’t support an estimate.

Classification7 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 5/141
Form or construction: shape, i.e. outer, aerodynamic form
F05D 2260/202
Heat transfer, e.g. cooling: by film cooling
Y02T 50/60
Aeronautics or air transport: efficient propulsion technologies, e.g. for aircraft

Family

Application63/502,556Us provisional application · filed 16 May 2023
US 2026/0022640 A1Pre-grant publication · published 22 Jan 2026
US 12,747,666 B2This patent

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

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Abstract

A turbine engine, comprising:

an engine core configured to generate an exhaust gas temperature (EGT) in a range of 980.1 and 1059.4 degrees Celsius (° C.) and a rotational speed (N2) in a range of 12511 to 13980.5 RPM, 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 configured to rotate about the engine centerline at the rotational speed (N2), wherein a radial axis is perpendicular to the engine centerline and aligned with a height dimension of the blade assembly, the blade assembly comprising:
a platform defining a platform plane;
an airfoil extending from the platform, the airfoil including:
a pressure side and a suction side and an exterior surface;
a leading edge and a trailing edge;
a root;
a tip defining a tip plane;
a cooling conduit;
a plurality of cooling holes in an overlapping region of the pressure side of the blade;
wherein an airfoil height (Hairfoil) is defined as a radial distance measured from the platform plane to the tip plane, wherein the airfoil height is in a range of 73.7 to 86.4 millimeters;
wherein the overlapping region of the pressure side of the blade is defined by:
a mid-region, wherein the mid-region is a region of the pressure side of the airfoil between a first radial plane and a second radial plane, wherein the first radial plane is arranged parallel to the tip plane and located at a first radial distance from the engine centerline, wherein the second radial plane is arranged parallel to the tip plane and located at a second radial distance from the engine centerline, and wherein the first radial distance is 0.369 meters and the second radial distance is 0.353 meters;
and
an aft region, wherein the a blade curve is defined as a line of intersection between the exterior surface of the pressure side and the second radial plane, wherein the blade curve extends between the leading edge and the trailing edge, wherein a curve point is defined at a distance of 68% of a length of the blade curve from the leading edge along the blade curve;
wherein an aft plane includes the curve point, is perpendicular to the second radial plane, and is perpendicular to the pressure side of the blade curve at the curve point, wherein the aft region is a region of the pressure side of the blade that is located between the aft plane and the trailing edge;
wherein each cooling hole in the plurality of cooling holes includes a cooling passage, each cooling passage extending between an inlet fluidly coupled to the cooling conduit and an outlet open to the exterior surface, the cooling passage defining a passage centerline;
wherein each cooling hole in the plurality of cooling holes includes a radial hole angle (RHA) defined between the second radial plane and the respective passage centerline;
wherein a radial hole angle average (RHAavg) is defined as an average of the radial hole angles (RHAs) for all cooling holes in the overlapping region, wherein the radial hole angle average (RHAavg) is in the range of 21.4 to 63.7 degrees;
and
wherein a minimum radial hole angle (RHAmin) is defined as a smallest radial hole angle of all the radial hole angles in the plurality of cooling holes, wherein the minimum radial hole angle (RHAmin) is in the range of 20.1 to 44.9 degrees;
wherein the exhaust gas temperature (EGT), the rotational speed (N2), the airfoil height (Hairfoil), and the radial hole angle average (RHAavg), define a first value (EQ1) by the following expression:
EQ
⁢
1
=
(
(
RHA
avg
15
⁢
°
)
+
3
.
7
⁢
5
⁢
(
H
airfoil
⁢
(
mm
)
73.7
mm
)
3
)
⁢
(
1
.
7
×
EGT
⁡
(
°
⁢
C
.
)
1000
⁢
°
⁢
C
.
)
⁢
(
1.2
×
13
,
000
⁢
RPM
N
⁢
2
⁢
(
RPM
)
)
,
wherein the exhaust gas temperature (EGT), the rotational speed (N2), and the minimum radial hole angle (RHAmin), define a second value (EQ2) by the following expression:
EQ
⁢
2
=
(
RHA
min
30
⁢
°
)
⁢
(
EGT
⁡
(
°
⁢
C
.
)
1000
⁢
°
⁢
C
.
)
⁢
(
13
,
000
⁢
RPM
N
⁢
2
⁢
(
RPM
)
)
,
and
wherein the first value (EQ1) is in the range of 9.87 to 22.7, and the second value (EQ2) is in the range of 0.61 to 1.64.

139 more elements

Facts

Application

18/665,668Filed 16 May 2024 · us provisional application

Priority

16 May 2023

Published

US 2026/0022640 A122 Jan 2026

Granted

29 Sep 2026

Term ends

Not estimatedThe source records don’t support an estimate.

Classification7 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 5/141
Form or construction: shape, i.e. outer, aerodynamic form
F05D 2260/202
Heat transfer, e.g. cooling: by film cooling
Y02T 50/60
Aeronautics or air transport: efficient propulsion technologies, e.g. for aircraft