Integrated fan / low pressure compressor rotor for gas turbine engine
US6145300A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jul 9, 1998 |
| Grant date | Nov 14, 2000 |
| Priority date | — |
| Expiry date | Jul 9, 2018 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An integrated fan and low pressure compressor rotor having a hub with a circumferential array of primary blades. Each primary blade has a forward fan blade portion housed in the engine inlet radially extending from the hub to the fan case and a rearward compressor blade portion housed in the core duct radially extending from the hub to the intermediate case. The fan blade portion and compressor blade portion have aerodynamically aligned lateral airfoil surfaces and platforms such that the fan blade portion and compressor blade portion have continuously merged lateral airfoil surfaces and platforms. The integrated rotor replaces two conventional rotors resulting in cost savings.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.