Three spool gas turbine engine with interdigitated turbine section
US10544734B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 23, 2017 |
| Grant date | Jan 28, 2020 |
| Priority date | — |
| Expiry date | Apr 6, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/54
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end long the longitudinal direction. The gas turbine engine includes a turbine section including a low speed turbine rotor, a high speed turbine rotor, and an intermediate speed turbine rotor. The low speed turbine rotor includes an inner shroud and an outer shroud outward of the inner shroud in the radial direction. The outer shroud defines a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction. The low speed turbine rotor further includes at least one connecting airfoil coupling the inner shroud to the outer shroud. The high speed turbine rotor is disposed upstream of the one or more connecting airfoils of the low speed turbine rotor along the longitudinal direction. The high speed turbine rotor includes a plurality of high speed turbine airfoils extended outward in the radial direction. The intermediate speed turbine rotor is disposed upstream of the one or more connecting airfoils of the low s…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.