Turbine blade having gas film cooling structure with a composite irregular groove and a method of manufacturing the same
US11352888B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 28, 2018 |
| Grant date | Jun 7, 2022 |
| Priority date | — |
| Expiry date | Dec 28, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade having a gas film cooling structure with a composite irregular groove. The turbine blade has a hollow structure, and a plurality of first grooves which are recessed grooves are provided on an outer surface thereof. A plurality of discrete holes A extending to an inner surface of the turbine blade are provided at the groove bottom of each first groove. The first groove is an irregular groove, and includes at least two portions in a depth direction. A portion having a depth H1 from the groove bottom of the first groove is a first portion, and the rest thereof is a second portion. At least one side surface of the second portion is formed by expanding in lateral direction from a corresponding side surface of the first portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.