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Title: Combustor arrangement including flow control vanes

Abstract

A combustor assembly (17) including guide vanes (44) located between an inner cylinder (24) and a flow sleeve (25). Each guide vane (44) includes a circumferentially angled flow directing portion (60) adjacent to a leading edge (46). The leading edge (46) of at least one guide vane (44) can be located radially inward along the longitudinal axis (54) relative to the leading edge (46) of at least one other of the guide vanes (44). The length of the guide vanes (44) may vary, and the circumferential spacing between a first pair of the guide vanes (44) can be different from a spacing between a second pair of the guide vanes (44).

Inventors:
Issue Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1453794
Patent Number(s):
9982893
Application Number:
15/506,055
Assignee:
Siemens Energy, Inc. (Orlando, FL)
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2014 Sep 05
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Rodriguez, Jose L. Combustor arrangement including flow control vanes. United States: N. p., 2018. Web.
Rodriguez, Jose L. Combustor arrangement including flow control vanes. United States.
Rodriguez, Jose L. Tue . "Combustor arrangement including flow control vanes". United States. https://www.osti.gov/servlets/purl/1453794.
@article{osti_1453794,
title = {Combustor arrangement including flow control vanes},
author = {Rodriguez, Jose L.},
abstractNote = {A combustor assembly (17) including guide vanes (44) located between an inner cylinder (24) and a flow sleeve (25). Each guide vane (44) includes a circumferentially angled flow directing portion (60) adjacent to a leading edge (46). The leading edge (46) of at least one guide vane (44) can be located radially inward along the longitudinal axis (54) relative to the leading edge (46) of at least one other of the guide vanes (44). The length of the guide vanes (44) may vary, and the circumferential spacing between a first pair of the guide vanes (44) can be different from a spacing between a second pair of the guide vanes (44).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2018},
month = {5}
}

Works referenced in this record:

Combustor device of gas turbine engine
patent, December 1978


Airflow distribution to a low emissions combustor
patent, March 2010


Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010


Transition with a linear flow path for use in a gas turbine engine
patent, February 2012


Assembly for directing combustion gas
patent, October 2012


Angled vanes in combustor flow sleeve
patent, August 2013


Modular Transvane Assembly
patent-application, April 2010


Combustor Assembly for Use in a Turbine Engine and Methods of a Assembling Same
patent-application, February 2012


System and Method for Flow Control in Gas Turbine Engine
patent-application, November 2012


Combustor and Method for Suppling Flow to a Combustor
patent-application, April 2013


Annular Flow Conditioning Member for Gas Turbomachine Combustor Assembly
patent-application, April 2013


Systems and Methods For Suppressing Combustion Driven Pressure Fluctuations With a Premix Combustor Having Multiple Premix Times
patent-application, March 2014


System and Method for Swirl Flow Generation
patent-application, April 2014


Cooling Structure for Gas Turbine Combustor Liner
patent-application, April 2015


Combustion Chamber with Cooling Sleeve
patent-application, September 2015


Heat-Transfer Device and Gas Turbine Combustor with Same
patent-application, December 2015