Gas turbine engine compressor arrangement
US8449247B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 21, 2012 |
| Grant date | May 28, 2013 |
| Priority date | — |
| Expiry date | Oct 7, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/4031
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas a pressure ratio across the fan section being less than or equal to about 1.45.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.