System and method for flow control in gas turbine engine
US8919127B2 · kind B2 · utility
15Cited by
28References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 24, 2011 |
| Grant date | Dec 30, 2014 |
| Priority date | — |
| Expiry date | Aug 15, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/286
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure between the combustion liner and the flow sleeve. The structure obstructs an airflow through the air passage. The gas turbine combustor also includes a wake reducer disposed adjacent the structure. The wake reducer directs a flow into a wake region downstream of the structure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.