Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines
US6684626B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 30, 2002 |
| Grant date | Feb 3, 2004 |
| Priority date | — |
| Expiry date | Sep 25, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C3/067
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An aircraft gas turbine engine includes a low pressure turbine having a low pressure turbine flowpath and counter rotatable low pressure inner and outer shaft rotors having inner and outer shafts, respectively. The low pressure inner and outer shaft rotors include low pressure first and second turbine blade rows disposed across the turbine flowpath and drivingly connected to first and second fan blade rows by low pressure inner and outer shafts, respectively. At least one of the low pressure first and second turbine blade rows is interdigitated with an adjacent pair of one of the turbine blade rows. At least one row of non-rotatable low pressure vanes is disposed across the low pressure turbine flowpath between a non interdigitated adjacent pair of one of the turbine blade rows.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.