skip to main content
OSTI.GOV title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: 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:
; ; ;
Publication Date:
Research Org.:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1175512
Patent Number(s):
6,951,108
Application Number:
10/762,993
Assignee:
General Electric Company (Schenectady, NY)
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 = {2005},
month = {10}
}

Patent:

Save / Share: