Gas turbine engine with idle thrust ratio
US12123310B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 4, 2023 |
| Grant date | Oct 22, 2024 |
| Priority date | — |
| Expiry date | Oct 4, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/40311
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine according to an example of the present disclosure may include, among other things, a propulsor section including a propulsor having a plurality of propulsor blades, a geared architecture, a first spool including a first shaft that interconnects a first compressor and a first turbine, the first driving the propulsor through the geared architecture. The gas turbine engine is rated to provide an amount of thrust at ground idle, and the gas turbine engine is rated to provide an amount of thrust at maximum takeoff. A thrust ratio is defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff. The thrust ratio can be less than or equal to 0.050.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.