Method of manufacturing gas turbine engine element having at least one elongated opening
US11035249B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 23, 2014 |
| Grant date | Jun 15, 2021 |
| Priority date | — |
| Expiry date | Jul 22, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A method of manufacturing a gas turbine engine element, for example a shroud segment. An insert has at least one elongated feature received in a mold cavity. A powder injection molding feedstock is injected. When the green part is disengaged from the mold, each elongated feature is slid out of the green part to define a respective elongated passage. The cross-sectional dimension of the elongated feature may be 0.020 inches or less, and/or a ratio between the length and cross-sectional dimension of the elongated feature may be at least 25. The method may include, after debinding and sintering, projecting a coating material while defining an obstruction between source of coating material and the open end of each elongated feature with a shoulder of the element to prevent the coating material from reaching the open end, followed by machining to remove at least a part of the shoulder.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.