Counter rotating turbine with reversing reduction gear assembly
US10801442B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 8, 2017 |
| Grant date | Oct 13, 2020 |
| Priority date | — |
| Expiry date | Sep 12, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section and a gear assembly within or downstream of the turbine section. The turbine section includes a first rotating component and a second rotating component along the longitudinal direction. The first rotating component includes one or more connecting airfoils coupled to a radially extended rotor, and the second rotating component includes an inner shroud defining a plurality of inner shroud airfoils extended outward of the inner shroud along the radial direction. The second rotating component is coupled to a second shaft connected to an input accessory of the gear assembly, and the first rotating component is coupled to an output accessory of the gear assembly. The output accessory rotates the first rotating component about the axial centerline at a first speed and wherein the second rotating component rotates about the axial centerline at a second speed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.