Gas turbine engine compressor with a biased inner ring
US9341194B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Nov 1, 2012 |
| Grant date | May 17, 2016 |
| Priority date | — |
| Expiry date | Feb 20, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/501
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An inner bushing assembly (280) to provide a biasing force between a guide vane (260) and an inner ring half (261) of a gas turbine engine compressor (200) is disclosed. The inner bushing assembly (280) includes a first bushing (281), a second bushing (282), and a biasing element (283). The first bushing (281) is configured to be installed about an inner vane shaft (267) of the guide vane (260) adjacent to an airfoil (265) of the guide vane (260). The second bushing (282) is configured to be installed about the inner vane shaft (267) distal to the airfoil (265). The biasing element (283) is configured to be installed about the inner vane shaft (267) between the first bushing (281) and the second bushing (282).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.