Turbine blade, and turbine and gas turbine including the same

Patent metadata

Field	Value
Publication number	US-2023167744-A1
Application number	US-202217932214-A
Country	US
Kind code	A1
Filing date	Sep 14, 2022
Priority date	Nov 30, 2021
Publication date	Jun 1, 2023
Grant date	—

Abstract

Disclosed herein are a grooved turbine blade, and a turbine and a gas turbine including the same. According to the disclosure, since a groove part is formed on a root member to disperse torsional stress, it is possible to improve durability of a rotor disk to which the turbine blade is assembled.

First claim

What is claimed is:

1 . A turbine blade comprising:
an airfoil having an airfoil cross-section and extending radially; a platform disposed radially inward from the airfoil; a root member disposed radially inward from the platform and having a decreased width as it is directed radially inward; a plurality of dovetails formed on both circumferential sides of the root member and each having a contact surface formed on a radially outer surface thereof, the plurality of dovetails being arranged radially in sequence; and a groove part formed on at least one axial side of the root member, the groove part being recessed inwardly of the root member and extending circumferentially therein, wherein the groove part is formed at a height corresponding to a radially outermost dovetail in the root member, and comprises a planar portion having a flat surface formed in at least a portion thereof.

2 . The turbine blade according to claim 1 , wherein the groove part is recessed from a bottom of the platform.

3 . The turbine blade according to claim 1 , wherein the groove part has a deepest recessed portion into the root member located at a height corresponding to the contact surface.

4 . The turbine blade according to claim 1 , wherein the groove part is formed such that an area occupied by the planar portion in the root member at least partially overlaps an area corresponding to the contact surface.

5 . The turbine blade according to claim 1 , wherein the groove parts are formed asymmetrically on both axial sides of the root member.

6 . The turbine blade according to claim 1 , wherein the planar portion is formed perpendicular to an axial direction of the turbine.

7 . The turbine blade according to claim 1 , wherein:
the groove part further comprises a first section, a second section, and a third section arranged radially inwardly in sequence; the first section is recessed inwardly of the root member while being downwardly inclined with respect to an axial direction of the turbine; the second section is the planar portion; and the third section is recessed inwardly of the root member while being upwardly inclined with respect to the axial direction of the turbine.

8 . The turbine blade according to claim 7 , wherein the first section, the second section, and the third section are formed continuously.

9 . The turbine blade according to claim 7 , wherein the first section or the third section has a curved cross-section.

10 . The turbine blade according to claim 7 , wherein the third section extends further radially inward than the radially outermost dovetail.

11 . A turbine comprising:
a rotatable turbine rotor disk; a plurality of turbine blades arranged on the turbine rotor disk; and a plurality of fixed turbine vanes, wherein each of the turbine blades comprises: an airfoil having an airfoil cross-section and extending radially; a platform disposed radially inward from the airfoil; a root member disposed radially inward from the platform and having a decreased width as it is directed radially inward; a plurality of dovetails formed on both circumferential sides of the root member and each having a contact surface formed on a radially outer surface thereof, the plurality of dovetails being arranged radially in sequence; and a groove part formed on at least one axial side of the root member, the groove part being recessed inwardly of the root member and extending circumferentially therein, and wherein the groove part is formed at a height corresponding to a radially outermost dovetail in the root member, and comprises a planar portion having a flat surface formed in at least a portion thereof.

12 . The turbine according to claim 11 , wherein the groove part is formed such that an area occupied by the planar portion in the root member at least partially overlaps an area corresponding to the contact surface.

13 . The turbine according to claim 11 , wherein:
the groove part further comprises a first section, a second section, and a third section arranged radially inwardly in sequence; the first section is recessed inwardly of the root member while being downwardly inclined with respect to an axial direction of the turbine; the second section is the planar portion; and the third section is recessed inwardly of the root member while being upwardly inclined with respect to the axial direction of the turbine.

14 . The turbine according to claim 13 , wherein the first section or the third section has a curved cross-section.

15 . The turbine according to claim 13 , wherein the third section extends further radially inward than the radially outermost dovetail.

16 . A gas turbine comprising:
a compressor configured to compress air; a combustor configured to mix fuel with the air compressed by the compressor to burn a mixture thereof; and a turbine comprising a turbine vane fixed to guide combustion gas produced by the combustor and a turbine blade rotated by the combustion gas, wherein the turbine blade comprises:
an airfoil having an airfoil cross-section and extending radially;
a platform disposed radially inward from the airfoil;
a root member disposed radially inward from the platform and having a decreased width as it is directed radially inward; a plurality of dovetails formed on both circumferential sides of the root member and each having a contact surface formed on a radially outer surface thereof, the plurality of dovetails being arranged radially in sequence; and a groove part formed on at least one axial side of the root member, the groove part being recessed inwardly of the root member and extending circumferentially therein, and wherein the groove part is formed at a height corresponding to a radially outermost dovetail in the root member, and comprises a planar portion having a flat surface formed in at least a portion thereof.

17 . The gas turbine according to claim 16 , wherein the groove part is formed such that an area occupied by the planar portion in the root member at least partially overlaps an area corresponding to the contact surface.

18 . The gas turbine according to claim 16 , wherein:
the groove part further comprises a first section, a second section, and a third section arranged radially inwardly in sequence; the first section is recessed inwardly of the root member while being downwardly inclined with respect to an axial direction of the turbine; the second section is the planar portion; and the third section is recessed inwardly of the root member while being upwardly inclined with respect to the axial direction of the turbine.

19 . The gas turbine according to claim 18 , wherein the first section or the third section has a curved cross-section.

20 . The gas turbine according to claim 18 , wherein the third section extends further radially inward than the radially outermost dovetail.

Assignees

• Doosan Enerbility Co Ltd

Inventors

• Song Jin Woo
• Bae Jin Ho
• Kim Ki Baek
• Jung Sung Chul
• Choi Jae Yeon

Classifications

• F01D5/10

  Anti- vibration means {(specially adapted for radial flow machines or engines F01D5/04)} · CPC title

• F01D5/3023

  of radial insertion type, e.g. in individual recesses · CPC title

• F01D5/027 Primary

  Arrangements for balancing (for balancing rotating bodies in general F16F15/32; for compensating imbalance G01M1/36) · CPC title

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F05D2250/294

  grooved · CPC title