Gas turbine engine with bypass TOBI cooling/purge flow and method
US12320270B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 4, 2023 |
| Grant date | Jun 3, 2025 |
| Priority date | — |
| Expiry date | May 14, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/606
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine is provided that includes a high pressure compressor (HPC), a combustor section, a high pressure turbine (HPT), and a bypass tangential on board injector (TOBI) system. The combustor section has a combustor. A core gas path extends through the HPC, the combustor section, and the HPT. The bypass TOBI system extends circumferentially around the engine axial centerline, and has a plurality of nozzles, inner and outer radial sides, a plurality of first type and second type radial passages configured to allow the gas from the HPC to pass from the inner radial side of the bypass TOBI system to the outer radial side of the bypass TOBI system, wherein the first type radial passages are differently configured from the second type radial passages.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.