Title:
FUEL NOZZLE FOR A GAS TURBINE ENGINE
Document Type and Number:
WIPO Patent Application WO/2014/113105
Kind Code:
A3
Abstract:
A fuel nozzle for a combustor of a gas turbine engine, includes a swirler tip along an axis; and a helical adapter along the axis and within the swirler tip. A method of directing a fuel gas and a liquid through a fuel nozzle and into a combustor of a gas turbine engine includes directing a primary fuel flow through a helical insert; and directing a secondary fuel flow around the helical insert.
Inventors:
COFFEY ROGER O (US)
Application Number:
PCT/US2013/065453
Publication Date:
October 16, 2014
Filing Date:
October 17, 2013
Export Citation:
Assignee:
UNITED TECHNOLOGIES CORP (US)
International Classes:
F23R3/28; B05B1/02; F02C9/26; F02M63/00
Foreign References:
| US6715292B1 | 2004-04-06 | |||
| US7926282B2 | 2011-04-19 | |||
| US6021635A | 2000-02-08 | |||
| US20120186259A1 | 2012-07-26 | |||
| US20070074517A1 | 2007-04-05 |
Attorney, Agent or Firm:
O'SHEA, Patrick, J. (c/o CPA GlobalP.O. Box 5205, Minneapolis MN, US)
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