1-D, UV-Raman imaging from a high-pressure, Jet-A fueled gas turbine combustor

2000 ◽  
Author(s):  
Yongwei Gu ◽  
Erhard Rothe ◽  
Gene Reck ◽  
Robert Anderson ◽  
Yolanda Hicks ◽  
...  
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Raman Imaging ◽  
Gas Turbine Combustor ◽  
Uv Raman

Preliminary Results from a High Pressure Optical gas Turbine Combustor Model with 3D Viewing Capability

2015 ◽  
Author(s):  
Nicholas Syred ◽  
Stephen M. Morris ◽  
P. J. Bowen ◽  
Agustin Valera-Medina ◽  
Richard Marsh
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbine Combustor ◽  
Preliminary Results

scholarly journals Wall Temperature Measurements in a Full-Scale Gas Turbine Combustor Test Rig With Fiber Coupled Phosphor Thermometry

2020 ◽  
Vol 143 (1) ◽  
Author(s):  
Patrick Nau ◽  
Simon Görs ◽  
Christoph Arndt ◽  
Benjamin Witzel ◽  
Torsten Endres
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Wall Temperature ◽  
Clean Energy ◽  
Full Scale ◽  
Temperature Measurements ◽  
Test Facility ◽  
Fiber Optic Probe ◽  
Gas Turbine Combustor ◽  
Phosphor Thermometry

Abstract Wall temperature measurements with fiber coupled online phosphor thermometry were, for the first time, successfully performed in a full-scale H-class Siemens gas turbine combustor. Online wall temperatures were obtained during high-pressure combustion tests up to 8 bar at the Siemens Clean Energy Center (CEC) test facility. Since optical access to the combustion chamber with fibers being able to provide high laser energies is extremely challenging, we developed a custom-built measurement system consisting of a water-cooled fiber optic probe and a mobile measurement container. A suitable combination of chemical binder and thermographic phosphor was identified for temperatures up to 1800 K on combustor walls coated with a thermal barrier coating (TBC). To our knowledge, these are the first measurements reported with fiber coupled online phosphor thermometry in a full-scale high-pressure gas turbine combustor. Details of the setup and the measurement procedures will be presented. The measured signals were influenced by strong background emissions probably from CO*2 chemiluminescence. Strategies for correcting background emissions and data evaluation procedures are discussed. The presented measurement technique enables the detailed study of combustor wall temperatures and using this information an optimization of the gas turbine cooling design.

Self-Excited Transverse Instabilities in a High-Pressure Multi-Element Gas Turbine Combustor

2018 ◽  
Author(s):  
John J. Philo ◽  
Rohan Gejji ◽  
Aaron Lemcherfi ◽  
Michael Arendt ◽  
Chris Journell ◽  
...  
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbine Combustor

High Momentum Jet Flames at Elevated Pressure: A — Experimental and Numerical Investigation for Different Fuels

2017 ◽  
Author(s):  
Oliver Lammel ◽  
Michael Severin ◽  
Holger Ax ◽  
Rainer Lückerath ◽  
Andrea Tomasello ◽  
...  
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Elevated Pressure ◽  
Operating Conditions ◽  
Diagnostic Methods ◽  
Liquid Fuels ◽  
Main Stage ◽  
High Momentum ◽  
Gas Turbine Combustor ◽  
Jet Flames

In this work, results of comprehensive high-pressure tests and numerical simulations of high momentum jet flames in an optically accessible combustion chamber are presented. A generic single nozzle burner was designed as a full-scale representation of one duct of a high temperature FLOX® gas turbine combustor with a model pilot burner supporting the main nozzle. As an advanced step of the FLOX® gas turbine combustor development process, tests and simulations of the entire burner system (consisting of a multi nozzle main stage plus a pilot stage) are complemented with this work on an unscaled single nozzle combustor, thus supporting the development and testing of sub concepts and components like the mixing section and dual-fuel injectors. These injectors incorporate a gaseous fuel stage and a spray atomizer for liquid fuels, both separately exchangeable for testing of different fuel placement concepts. The combustor was successfully operated at gas turbine relevant conditions with natural gas including a variation of the Wobbe index, and with light heating oil with and without water admixture. The presented work is the first of two contributions and covers the description of the experimental setup, an overview of the numerical methods, high-pressure test results for different fuels and variations of the operating conditions including exhaust gas measurements and basic optical diagnostic methods, together with CFD results for several cases. The other part will present detailed and focused investigations of few conditions by complex and extensive optical and laser combustion diagnostics.

Sign in / Sign up

Export Citation Format

Share Document