Gas turbine engine combustor can with trapped vortex cavity
Abstract
A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.
- Inventors:
- Issue Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1175512
- Patent Number(s):
- 6951108
- Application Number:
- 10/762,993
- Assignee:
- General Electric Company (Schenectady, NY)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23C - METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN {A CARRIER GAS OR} AIR
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23D - BURNERS
- DOE Contract Number:
- FC26-01NT41020
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS
Citation Formats
Burrus, David Louis, Joshi, Narendra Digamber, Haynes, Joel Meier, and Feitelberg, Alan S. Gas turbine engine combustor can with trapped vortex cavity. United States: N. p., 2005.
Web.
Burrus, David Louis, Joshi, Narendra Digamber, Haynes, Joel Meier, & Feitelberg, Alan S. Gas turbine engine combustor can with trapped vortex cavity. United States.
Burrus, David Louis, Joshi, Narendra Digamber, Haynes, Joel Meier, and Feitelberg, Alan S. Tue .
"Gas turbine engine combustor can with trapped vortex cavity". United States. https://www.osti.gov/servlets/purl/1175512.
@article{osti_1175512,
title = {Gas turbine engine combustor can with trapped vortex cavity},
author = {Burrus, David Louis and Joshi, Narendra Digamber and Haynes, Joel Meier and Feitelberg, Alan S.},
abstractNote = {A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Oct 04 00:00:00 EDT 2005},
month = {Tue Oct 04 00:00:00 EDT 2005}
}