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US 2026/0103990 A1Published application
Turbine engine with a blade assembly having a dovetail
AssigneeGeneral Electric Company
InventorsJordan Paige Reddington, Clive Andrew Morgan, Daniel Endecott Osgood
Life of this patent
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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 set of lobes defining complementary recesses, collectively defining a neck for mounting to the disk.
Claims14
A blade assembly for a turbine engine, the blade assembly comprising:
- an airfoil;
- a platform coupled to the airfoil, the platform including a stator rotor seal having a seal upper surface and a seal end surface, with a seal junction defined where the seal upper surface and meets the seal end surface;
- a dovetail extending from the platform opposite the airfoil, 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 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, with the second upper lobe having a second lobe upper surface;
- 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 pressure face surface defining a planar portion of the second lobe upper surface;
- wherein a spaced plane is defined parallel to the aft face and parallel to and intersecting the passage axis, and wherein the spaced plane is spaced from the aft face by 0.6985 cm;
- wherein an offset plane is defined offset from the spaced plane by 10-degrees 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 0.001016 m and 0.001994 m;
- 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 0.0.001016 m and 0.001778 m;
- wherein a pressure face area (UPF) is defined as an area of the pressure face surface, wherein the pressure face area (UPF) is between 0.000129 m2 and 0.000148 m2;
- and
- wherein a seal radius (R) is defined as a radius of curvature of the seal junction, wherein the seal radius (R) is between 0.315214 m and 0.316484 m;
- wherein the first radius length (L), the first length (LPF), the pressure face area (UPF), and the seal radius (R) define a first value (EQ1) by the following expression:
- EQ
-
- 1
- =
- (
- UPF
- 0.004303
- m
- 2
- )
- +
- (
- LPF
- 0.0015
- m
- )
- (
- L
- 0.0015
- m
- )
- -
- (
- R
- 0.22555
- m
- )
- ;
- and
- wherein the first value (EQ1) is between −17.886 and −0.988.
46 more elements
A dovetail assembly for a turbine engine, the dovetail assembly comprising:
- a platform including a stator rotor seal having a seal upper surface and a seal end surface, with a seal junction defined between the seal upper surface and the seal end surface;
- and
- a dovetail coupled to the platform, wherein the dovetail comprising:
- 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 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, with the second upper lobe having a second lobe upper surface;
- 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 pressure face surface defining a planar portion of the second lobe upper surface;
- wherein a spaced plane is defined parallel to the aft face and parallel to and intersecting the passage axis, wherein the spaced plane is spaced from the aft face by 0.6985 cm;
- wherein an offset plane is defined offset from the spaced plane by 10-degrees 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 0.001016 m and 0.001994 m;
- wherein a first length (LPF) is defined as a length of the first planar surface measured along the offset plane, wherein the first length (LPF) is between 0.0.001016 m and 0.001778 m;
- wherein a pressure face area (UPF) is defined as an area of the pressure face surface measured along the offset plane, wherein the pressure face area (UPF) is between 0.000129 m2 and 0.000148 m2;
- and
- wherein a seal radius (R) defined as a radius of curvature of the seal junction, wherein the seal radius (R) is between 0.315214 m and 0.316484 m;
- wherein the first radius length (L), the first length (LPF), the pressure face area (UPF), and the seal radius (R) define a first value (EQ1) by the following expression:
- EQ
-
- 1
- =
- (
- UPF
- 0.004303
- m
- 2
- )
- +
- (
- LPF
- 0.0015
- m
- )
- (
- L
- 0.0015
- m
- )
- -
- (
- R
- 0.22555
- m
- )
- ;
- and
- wherein the first value (EQ1) is between −17.886 and −0.988.
46 more elements
Dependencies are inferred from the claim text.