US 2026/0103987 A1Published application

Turbine engine with a blade assembly having a dovetail

AssigneeGeneral Electric Company

InventorsClive Andrew Morgan, Zachary A. Hase, Brian L. DeVilbiss, 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. A set of dovetails mounts the set of blades to a disk, rotated about the engine centerline. Each dovetail can include a first upper lobe and a first lower lobe defining a first intervening recess, and a second upper lobe and a second lower lobe defining a second intervening recess, collectively defining a neck for mounting to the disk.

Claims14

Dependent claims

A turbine engine, comprising:

an engine core extending along an engine centerline and including a compressor section, a combustor generating hot combustion gases at a redline exhaust gas temperature (EGT), and a turbine section in serial flow arrangement, wherein the redline exhaust gas temperature (EGT) is between 920° C. and 980° C.;
a disk provided within the engine core and rotatable about the engine centerline;
and
a blade comprising a dovetail mounted to the disk and rotatable by the disk at a redline rotational speed (N2), wherein the redline rotational speed (N2) is between 14000 rpm and 16000 rpm, and wherein the dovetail comprises:
an aft face;
an inlet passage extending through the dovetail and defining a passage axis;
a first portion including a first upper lobe, a first lower lobe, and a first intervening recess between the first upper lobe and the first lower lobe;
a first curved surface partially defining the first lower lobe and the first intervening recess;
a first planar surface partially defining the first lower lobe and the first intervening recess;
and
a second portion including a second upper lobe, a second lower lobe, and a second intervening recess between the second upper lobe and second lower lobe;
wherein a spaced plane is defined parallel to the aft face and intersecting the passage axis, wherein the spaced plane is spaced from the aft face by a spacing distance of 0.275 in;
wherein an offset plane is defined rotated from the spaced plane by 10-degrees being rotated about the passage axis;
wherein a first radius length (L) is defined as a radius of curvature of the first curved surface measured along the offset plane, wherein the first radius length (L) is between 0.04 in and 0.105 in;
wherein a first length (LPF) is defined as a length defined by the first planar surface measured along the offset plane, wherein the first length (LPF) is between 0.071 in and 0.080 in;
wherein a second width (CVX) is defined as a minimum length between the passage axis and a furthest extent of a gage pin from the inlet passage when the gage pin is provided within the second intervening recess, wherein the gage pin is a 0.165 in gage pin, wherein the second width (CVX) measured along the offset plane, and wherein the second width (CVX) is between 0.315 in and 0.335 in;
and
wherein a recess width (CVMN) is defined as a minimum length between the inlet passage and the second intervening recess measured along the offset plane, wherein the recess width (CVMN) is between 0.050 in and 0.140 in;
wherein the redline exhaust gas temperature (EGT), the redline rotational speed (N2), the first length (LPF), and the second width (CVX), define a first value (EQ1) by the following expression:
EQ
⁢
1
=
(
L
⁢
P
⁢
F
0.075
in
)
4
*
(
CVX
0.31
in
)
1
4
*
(
(
N
⁢
2
15000
⁢
RPM
)
1
2
(
E
⁢
G
⁢
T
9
⁢
5
⁢
0
∘
⁢
C
.
)
1
2
)
;
wherein the redline exhaust gas temperature (EGT), the redline rotational speed (N2), the first radius length (L), and the recess width (CVMN), define a second value (EQ2) by the following expression:
EQ
⁢
2
=
(
L
0.08
in
)
6
*
(
CVMN
0.08
in
)
1
6
*
(
(
N
⁢
2
15000
⁢
RPM
)
(
E
⁢
G
⁢
T
9
⁢
5
⁢
0
∘
⁢
C
.
)
)
;
and
wherein the first value (EQ1) is between 0.760 and 1.370, and the second value (EQ2) is between 0.010 and 5.300.

119 more elements

A turbine engine to generate hot combustion gases at a redline exhaust gas temperature (EGT) between 920° C. and 980° C., the turbine engine including a disk provided within an engine core and rotatable about an engine centerline, and including a dovetail for mounting a blade to the disk and rotatable by the disk at a rotation speed (N2) between 14000 rpm and 16000 rpm, the dovetail having an inlet passage defining a passage axis, the dovetail comprising:

an aft face;
a first portion including a first upper lobe, a first lower lobe, and a first intervening recess between the first upper lobe and the first lower lobe;
a first curved surface partially defining the first lower lobe and the first intervening recess;
a first planar surface partially defining the first lower lobe and the first intervening recess;
and
a second portion including a second upper lobe, a second lower lobe, and a second intervening recess between the second upper lobe and second aft lower lobe;
wherein the dovetail defines a spaced plane defined parallel to and spaced from the aft face by 0.275 in, with the spaced plane intersecting and arranged parallel to the passage axis;
wherein the dovetail further defines an offset plane being rotated from the spaced plane about the passage axis by an offset angle, and wherein the offset angle is 10-degrees;
wherein a first radius length (L) defined as a radius of curvature of the first curved surface measured along the offset plane, wherein the first radius length (L) is between 0.04 in and 0.105 in;
wherein a first length (LPF) defined as a length defined by the first planar surface measured along the offset plane, wherein the first length (LPF) is between 0.071 in and 0.080 in;
wherein a second width (CVX) is defined as a minimum length between the passage axis and a furthest extent of a gage pin from the inlet passage when the gage pin is provided within the second intervening recess, wherein the gage pin is a 0.165 in gage pin, wherein the second width (CVX) measured along the offset plane, and wherein the second width (CVX) is between 0.315 in and 0.335 in;
and
wherein a recess width (CVMN) defined as a minimum length between the inlet passage and the second intervening recess measured along the offset plane, wherein the recess width (CVMN) is between 0.050 in and 0.140 in;
wherein the exhaust gas temperature (EGT), the rotational speed (N2), the first length (LPF), and the second width (CVX), define a first value (EQ1) by the following expression:
EQ
⁢
1
=
(
L
⁢
P
⁢
F
0.075
in
)
4
*
(
CVX
0.31
in
)
1
4
*
(
(
N
⁢
2
15000
⁢
RPM
)
1
2
(
E
⁢
G
⁢
T
9
⁢
5
⁢
0
∘
⁢
C
.
)
1
2
)
;
wherein the exhaust gas temperature (EGT), the rotation speed (N2), the first radius length (L), and the recess width (CVMN), define a second value (EQ2) by the following expression:
EQ
⁢
2
=
(
L
0.08
in
)
6
*
(
CVMN
0.08
in
)
1
6
*
(
(
N
⁢
2
15000
⁢
RPM
)
(
E
⁢
G
⁢
T
9
⁢
5
⁢
0
∘
⁢
C
.
)
)
;
and
wherein the first value (EQ1) is between 0.760 and 1.370, and the second value (EQ2) is between 0.010 and 5.300.

114 more elements

Dependencies are inferred from the claim text.

Facts

Application: 19/355,500Filed 10 Oct 2025
Priority: 11 Oct 2024
Published: 16 Apr 2026
Term ends: Not estimatedThe source records don’t support an estimate.

Classification10 codes

F01D 5/3007
Fixing blades to rotors; Blade roots ; Blade spacers: of axial insertion type
F01D 5/141
Form or construction: shape, i.e. outer, aerodynamic form
F01D 5/143
Of the blades of successive rotor or stator blade-rows: contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
F02C 3/00
Gas-turbine plants characterised by the use of combustion products as the working

Family

Application63/706,301Us provisional application · filed 11 Oct 2024
US 2026/0103987 A1This patent

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

Timeline

Citations

Open elsewhere

patentgrep

Loading patent…

Abstract

A turbine engine, comprising:

an engine core extending along an engine centerline and including a compressor section, a combustor generating hot combustion gases at a redline exhaust gas temperature (EGT), and a turbine section in serial flow arrangement, wherein the redline exhaust gas temperature (EGT) is between 920° C. and 980° C.;
a disk provided within the engine core and rotatable about the engine centerline;
and
a blade comprising a dovetail mounted to the disk and rotatable by the disk at a redline rotational speed (N2), wherein the redline rotational speed (N2) is between 14000 rpm and 16000 rpm, and wherein the dovetail comprises:
an aft face;
an inlet passage extending through the dovetail and defining a passage axis;
a first portion including a first upper lobe, a first lower lobe, and a first intervening recess between the first upper lobe and the first lower lobe;
a first curved surface partially defining the first lower lobe and the first intervening recess;
a first planar surface partially defining the first lower lobe and the first intervening recess;
and
a second portion including a second upper lobe, a second lower lobe, and a second intervening recess between the second upper lobe and second lower lobe;
wherein a spaced plane is defined parallel to the aft face and intersecting the passage axis, wherein the spaced plane is spaced from the aft face by a spacing distance of 0.275 in;
wherein an offset plane is defined rotated from the spaced plane by 10-degrees being rotated about the passage axis;
wherein a first radius length (L) is defined as a radius of curvature of the first curved surface measured along the offset plane, wherein the first radius length (L) is between 0.04 in and 0.105 in;
wherein a first length (LPF) is defined as a length defined by the first planar surface measured along the offset plane, wherein the first length (LPF) is between 0.071 in and 0.080 in;
wherein a second width (CVX) is defined as a minimum length between the passage axis and a furthest extent of a gage pin from the inlet passage when the gage pin is provided within the second intervening recess, wherein the gage pin is a 0.165 in gage pin, wherein the second width (CVX) measured along the offset plane, and wherein the second width (CVX) is between 0.315 in and 0.335 in;
and
wherein a recess width (CVMN) is defined as a minimum length between the inlet passage and the second intervening recess measured along the offset plane, wherein the recess width (CVMN) is between 0.050 in and 0.140 in;
wherein the redline exhaust gas temperature (EGT), the redline rotational speed (N2), the first length (LPF), and the second width (CVX), define a first value (EQ1) by the following expression:
EQ
⁢
1
=
(
L
⁢
P
⁢
F
0.075
in
)
4
*
(
CVX
0.31
in
)
1
4
*
(
(
N
⁢
2
15000
⁢
RPM
)
1
2
(
E
⁢
G
⁢
T
9
⁢
5
⁢
0
∘
⁢
C
.
)
1
2
)
;
wherein the redline exhaust gas temperature (EGT), the redline rotational speed (N2), the first radius length (L), and the recess width (CVMN), define a second value (EQ2) by the following expression:
EQ
⁢
2
=
(
L
0.08
in
)
6
*
(
CVMN
0.08
in
)
1
6
*
(
(
N
⁢
2
15000
⁢
RPM
)
(
E
⁢
G
⁢
T
9
⁢
5
⁢
0
∘
⁢
C
.
)
)
;
and
wherein the first value (EQ1) is between 0.760 and 1.370, and the second value (EQ2) is between 0.010 and 5.300.

119 more elements

Facts

Application

19/355,500Filed 10 Oct 2025

Priority

11 Oct 2024

Published

16 Apr 2026

Term ends

Not estimatedThe source records don’t support an estimate.

Classification10 codes

F01D 5/3007
Fixing blades to rotors; Blade roots ; Blade spacers: of axial insertion type
F01D 5/141
Form or construction: shape, i.e. outer, aerodynamic form
F01D 5/143
Of the blades of successive rotor or stator blade-rows: contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
F02C 3/00
Gas-turbine plants characterised by the use of combustion products as the working