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US 2026/0146540 A1Published application
Gas turbine
AssigneeDoosan Enerbility Co., Ltd.
InventorsIurii GOROSHCHAK, Seol BAEK
Life of this patent
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Abstract
Provided is a blade-disk assembly for a gas turbine. The blade-disk assembly includes a blade having a root part, a disk having a disk slot, into which the root part is inserted, and a fixing block inserted into a block assembly groove of the blade and a block insertion groove of the disk in a circumferential direction to retain an axial position of the blade with respect to the disk.
Claims13
A blade-disk assembly for a gas turbine comprising:
- a blade having a root part;
- a disk having a disk slot, into which the root part is inserted;
- and
- a fixing block inserted into a block assembly groove of the blade and a block insertion groove of the disk in a circumferential direction to retain an axial position of the blade with respect to the disk.
1 more element
A gas turbine comprising:
- a compressor configured to draw in and compress external air;
- a combustor configured to mix fuel with the external air compressed in the compressor and to combust a mixture of fuel and the compressed air;
- and
- a turbine which comprises a blade-disk assembly in which a blade and a disk are assembled and rotated by a combustion gas discharged from the combustor,
- wherein the blade-disk assembly comprises:
- the blade having a root part;
- the disk having a disk slot, into which the root part is inserted;
- and
- a fixing block inserted into a block assembly groove of the blade and a block insertion groove of the disk in a circumferential direction to retain an axial position of the blade with respect to the disk.
6 more elements
Dependencies are inferred from the claim text.