Gas turbine engine component with increased cooling capacity
US10247011B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 27, 2015 |
| Grant date | Apr 2, 2019 |
| Priority date | — |
| Expiry date | Aug 19, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.