Supports for connecting a flow sleeve and a liner in a gas turbine combustor
US6216442A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Oct 5, 1999 |
| Grant date | Apr 17, 2001 |
| Priority date | — |
| Expiry date | Oct 5, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/642
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a combustor having an axis, a flow sleeve and a liner, a plurality of circumferentially spaced supports interconnect the upstream ends of the liner and flow sleeve to limit wear on the supports and accommodate relative thermal expansion of the liner and flow sleeve. Each support includes a flow sleeve stop having an angled surface, a groove and a female threaded aperture and a liner stop having a complementary angled surface, a rib and an enlarged opening. By inserting the liner axially through the open upstream end of the flow sleeve, the rib of the liner stop engages the slot of the flow sleeve stop. By passing a bolt having a spring through the enlarged opening of the liner stop and threading the bolt to the flow sleeve stop, the liner is biased for axial downstream movement to maintain the complementary inclined surfaces of the stops in contact with one another, thereby limiting wear and accommodating relative thermal expansion of the flow sleeve and liner.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.