Hot gas path duct for a combustor of a gas turbine
US9316396B2 · kind B2 · utility
14Cited by
24References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 18, 2013 |
| Grant date | Apr 19, 2016 |
| Priority date | — |
| Expiry date | Sep 4, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/346
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A hot gas path duct or unibody liner for a gas turbine includes a main body having a forward end and an aft end. The main body defines a cross-sectional flow area and an axial flow length that extends between the forward end and the aft end. The main body further defines a fuel injection portion disposed downstream from the forward end and upstream from the aft end. The cross-sectional flow area decreases along the axial flow length between the forward end and the fuel injection portion and increases along at least a portion of the axial flow length downstream from the fuel injection portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.