Suspension of a triple-flow aircraft turbine engine
US12404821B2 · kind B2 · utility
Assignees
Inventors
Key dates
| Filing date | Apr 15, 2022 |
| Grant date | Sep 2, 2025 |
| Priority date | — |
| Expiry date | Apr 15, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.