A test rig for investigations of gas turbine combustor cooling concepts under realistic operating conditions

2008 ◽  
Vol 222 (2) ◽  
pp. 169-177 ◽  
Author(s):  
T Behrendt ◽  
Ch Hassa
Keyword(s):  
Gas Turbine ◽  
Gas Flow ◽  
Leading Edge ◽  
Test Sample ◽  
Operating Conditions ◽  
Test Rig ◽  
Hot Gas ◽  
Elevated Pressures ◽  
Low Emission

In the current paper, a new test rig for the characterization of advanced combustor cooling concepts for gas turbine combustors is presented. The test rig is designed to allow investigations at elevated pressures and temperatures representing realistic operating conditions of future lean low emission combustors. The features and capabilities of the test rig in comparison to existing rigs are described. The properties of the hot gas flow are measured in order to provide the necessary data for a detailed analysis of the measured cooling effectivity of combustor wall test samples. Results of the characterization of the velocity and temperature distribution in the hot gas flow at the leading edge of the test sample at pressures up to p = 10 bar and global flame temperatures up to TF = 2000 K are presented.

Emission, LBO and Combustion Dynamic Characterization of Several Alternative Fuels

2005 ◽  
Author(s):  
Khalid Oumejjoud ◽  
Peter Stuttaford ◽  
Steve Jennings ◽  
John Henriquez ◽  
Hany Rizkalla ◽  
...  
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Alternative Fuels ◽  
Operating Conditions ◽  
Low Emission ◽  
Reduction Measure ◽  
Main Components ◽  
Fuel Costs ◽  
Base Load

Regulations are becoming increasingly stringent regarding gas turbine emissions. In addition fuel costs are at record highs. Power plant operators are exploring all alternatives for reducing operational cost. Refinery offgas represents an attractive cost reduction measure if one could burn it in the gas turbine. Hydrogen and methane are often the main components of such offgas. In an attempt to define the potential for an LEC-III® (Power Systems Mfg., LLC. Low Emission Combustor) performance with such an offgas, rig testing has been successfully carried out with several alternative fuels. Small quantities of hydrogen blended with natural gas and burned in specific zones of the combustor allowed emissions levels of sub 2ppm NOx and sub 9ppm CO to be demonstrated at full base load engine operating conditions on the test rig. Based upon rig to engine benchmarking these same emissions levels should be realized upon the full engine.

Experimental Investigation of a SOFC/MGT Hybrid Power Plant Test Rig: Impact and Characterization of Coupling Elements

2014 ◽  
Author(s):  
Martina Hohloch ◽  
Andreas Huber ◽  
Manfred Aigner
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Operating Conditions ◽  
System Stability ◽  
Test Rig ◽  
Micro Gas Turbine ◽  
Hybrid Power ◽  
Hybrid Power Plant ◽  
Plant Test

The main topic of the paper is the discussion of the operational behavior of the solid oxide fuel cell (SOFC)/micro gas turbine (MGT) hybrid power plant test rig with the pressure vessels of the SOFC emulator. In the first part a brief introduction to the test rig and its components is given. In the arrangement of the test rig the MGT is connected via an interface to the tubing system. Here, the preheated air after the recuperator can be led either to the emulator or via a bypass tube directly to the MGT. Furthermore, there is a direct connection between the compressor outlet and emulator for the startup and shutdown procedure. The facility is equipped with detailed instrumentation, including mass flow meters, thermocouples and pressure probes. In the second part of the paper the characterization of the hybrid power plant test rig is shown. To analyze the thermodynamic and fluid dynamic impact of the coupling elements various studies were carried out. Hereby, the influence of the coupling elements on the operational behavior, system stability and system performance of the micro gas turbine is shown for stationary load points, as well as during transient maneuvers like startup, load-change and shutdown. To avoid critical operating conditions limitations were defined and emergency maneuvers were developed and tested. Out of these investigations an operating concept for the hybrid power plant test rig can be derived.

Computational Study of Kelvin-Helmholtz Instability Created by Interaction of the Mainstream Flow and the Seal Flow in Gas Turbines

2011 ◽  
Author(s):  
M. Rabs ◽  
F.-K. Benra ◽  
C. Domnick ◽  
O. Schneider
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Gas Flow ◽  
Computational Study ◽  
Theoretical Background ◽  
Splitter Plate ◽  
Parameter Study ◽  
Test Rig ◽  
Hot Gas ◽  
Mainstream Flow

The present paper gives a contribution to a better understanding of the emergence of Kelvin-Helmholtz instabilities (KHI) in gas turbines. In an earlier paper of the authors, the occurrence of the KHI’s near the rim cavity of a 1.5 stage gas turbine has been examined by use of CFD methods. It is shown that the KHI’s occur, when the swirl component of the hot gas flow is very strong. Due to the fact, that a high swirl is produced by the guide vanes of the first stage, this matter concerns all common gas turbines. In order to get a basic theoretical background of the emergence of the KHI’s, 2D CFD investigations of the flow behind a splitter plate have been performed showing the development of KHI’s downstream of the splitter plate. To validate the numerical results a comparison to test rig data is used. This shows that the numerical method can simulate the characteristics of the KHI’s. Furthermore, a parameter study is conducted to extract parameters describing the appearance of KHI’s, the vortex periodicity and stability criteria. The main intention of this paper is to deliver “KHI parameters”, which are able to describe the development of the KHI in gas turbine rim cavities.

Introducing a New Test Rig for Film Cooling Measurements With Realistic Hole Inflow Conditions

2017 ◽  
Author(s):  
Marc Fraas ◽  
Tobias Glasenapp ◽  
Achmed Schulz ◽  
Hans-Jörg Bauer
Keyword(s):  
Film Cooling ◽  
Gas Flow ◽  
Test Rig ◽  
Hot Gas ◽  
Cooling Hole ◽  
Measurement Principle ◽  
Density Ratios ◽  
Operational Range ◽  
Film Cooling Holes

Further improvements in film cooling require an in-depth understanding of the influencing parameters. Therefore, a new test rig has been designed and commissioned for the assessment of novel film cooling holes under realistic conditions. The test rig is designed for generic film cooling studies. External hot gas flow as well as internal coolant passage flow are simulated by two individual flow channels connected to each other by the cooling holes. Based on a similarity analysis, the geometry of the test rig is scaled up by a factor of about 20. It furthermore offers the possibility to conduct experiments at high density ratios and realistic approach flow conditions at both cooling hole exit and inlet. The operational range of the new test rig is presented and compared to real engine conditions. It is shown that the important parameters are met and the transfer-ability of the results is ensured. Special effort is put onto the uniformity of the approaching hot gas flow, which will be demonstrated by temperature and velocity profiles. A first measurement of the heat transfer coefficient without film cooling is used to demonstrate the quality of the measurement principle.

Fuel Influence on Targeted Gas Turbine Combustion Properties: Part I — Detailed Diagnostics

2014 ◽  
Author(s):  
Thomas Mosbach ◽  
Victor Burger ◽  
Barani Gunasekaran
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Leading Edge ◽  
Operating Conditions ◽  
Optical Measurements ◽  
Test Facility ◽  
Research Centre ◽  
High Speed Imaging ◽  
Combustion Properties ◽  
First Results

The threshold combustion performance of different fuel formulations under simulated altitude relight conditions were investigated in the altitude relight test facility located at the Rolls-Royce plc. Strategic Research Centre in Derby, UK. The combustor employed was a twin-sector representation of an RQL gas turbine combustor. Eight fuels including conventional crude-derived Jet A-1 kerosene, synthetic paraffinic kerosenes (SPKs), linear paraffinic solvents, aromatic solvents and pure compounds were tested. The combustor was operated at sub-atmospheric air pressure of 41 kPa and air temperature of 265 K. The temperature of all fuels was regulated to 288 K. The combustor operating conditions corresponded to a low stratospheric flight altitude near 9 kilometres. The experimental work at the Rolls-Royce (RR) test-rig consisted of classical relight envelope ignition and extinction tests, and ancillary optical measurements: Simultaneous high-speed imaging of the OH* chemiluminescence and of the soot luminosity was used to visualize both the transient combustion phenomena and the combustion behaviour of the steady burning flames. Flame luminosity spectra were also simultaneously recorded with a spectrometer to obtain information about the different combustion intermediates and about the thermal soot radiation curve. This paper presents first results from the analysis of the weak extinction measurements. Further detailed test fuel results are the subject of a separate complementary paper [1]. It was found in general that the determined weak extinction parameters were not strongly dependent on the fuels investigated, however at the leading edge of the OH* chemiluminescence intensity development in the pre-flame region fuel-related differences were observed.

Characterization of solid deposits from urea water solution injected into a hot gas test rig

2019 ◽  
Vol 377 ◽  
pp. 119855 ◽  
Author(s):  
M. Börnhorst ◽  
S. Langheck ◽  
H. Weickenmeier ◽  
C. Dem ◽  
R. Suntz ◽  
...  
Keyword(s):  
Water Solution ◽  
Test Rig ◽  
Hot Gas

Wheel Box Test Aeromechanical Verification of New First Stage Bucket With Integrated Cover Plates for MS5002 GT

2019 ◽  
Author(s):  
Marco Mariottini ◽  
Nicola Pieroni ◽  
Pietro Bertini ◽  
Beniamino Pacifici ◽  
Alessandro Giorgetti
Keyword(s):  
Gas Turbine ◽  
Oil And Gas ◽  
Oil And Gas Industry ◽  
Response Assessment ◽  
Operating Conditions ◽  
Analytical Models ◽  
Gas Industry ◽  
Improved Performance ◽  
Cover Plates

Abstract In the oil and gas industry, manufacturers are continuously engaged in providing machines with improved performance, reliability and availability. First Stage Bucket is one of the most critical gas turbine components, bearing the brunt of very severe operating conditions in terms of high temperature and stresses; aeromechanic behavior is a key characteristic to be checked, to assure the absence of resonances that can lead to damage. Aim of this paper is to introduce a method for aeromechanical verification applied to the new First Stage Bucket for heavy duty MS5002 gas turbine with integrated cover plates. This target is achieved through a significantly cheaper and streamlined test (a rotating test bench facility, formally Wheel Box Test) in place of a full engine test. Scope of Wheel Box Test is the aeromechanical characterization for both Baseline and New bucket, in addition to the validation of the analytical models developed. Wheel Box Test is focused on the acquisition and visualization of dynamic data, simulating different forcing frequencies, and the measurement of natural frequencies, compared with the expected results. Moreover, a Finite Elements Model (FEM) tuning for frequency prediction is performed. Finally, the characterization of different types of dampers in terms of impact on frequencies and damping effect is carried out. Therefore, in line with response assessment and damping levels estimation, the most suitable damper is selected. The proposed approach could be extended for other machine models and for mechanical audits.

Degradation Assessment of Gas Turbine Hot Gas Path Components

2016 ◽  
Vol 1133 ◽  
pp. 376-380
Author(s):  
Ahmad Afiq Pauzi
Keyword(s):  
Gas Turbine ◽  
Fuel Mixture ◽  
Operating Conditions ◽  
Research Project ◽  
Damage Mechanisms ◽  
Damage And Failure ◽  
Hot Gas ◽  
Failure Risk ◽  
Path Component ◽  
Damage Processes

Hot gas path component consists of components designed to burn air-fuel mixture in combustion section and provide hot gasses to the turbine section where mechanical power is produced. The aim of this research project is expected to improve the current practices of managing degradation of hot gas path components. Understanding the damage mechanisms is of great interest in reducing the damage and failure risk. In this research, a study was conducted on F-Class type gas turbine hot gas path components assembly. It involved extensive examination and testing of the components which had been in operations for 24,000 hours since the last shutdown. Various factors such as installation, operating conditions, hardness and material of constructions were also investigated. This paper reports the initial findings of the study of hot gas path components degradation. It describes the damage observed on the affected areas of the components and proposes the factors that contribute to the damage processes. Potential solutions for mitigating the damages are also discussed.

Simulation Film Cooling in the Leading Edge Region of a Turbine Blade (Trench Effect on Film Effectiveness from Cylinder in Crossflow)

2014 ◽  
Vol 554 ◽  
pp. 317-321
Author(s):  
Mohamad Rasidi Bin Pairan ◽  
Norzelawati Binti Asmuin ◽  
Hamidon bin Salleh
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Leading Edge ◽  
Edge Region ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Blowing Ratio ◽  
Hot Gas ◽  
Cooling Technique

Film cooling is one of the cooling techniques applied to the turbine blade. Gas turbine used film cooling technique to protect turbine blade from directly expose to the hot gas to avoid the blade from defect. The focus of this investigation is to investigate the effect of embedded three difference depth of trench at coolant holes geometry. Comparisons are made at four difference blowing ratios which are 1.0, 1.25 and 1.5. Three configuration leading edge with depth Case A (0.0125D), Case B (0.0350D) and Case C (0.713D) were compared to leading edge without trench. Result shows that as blowing ratio increased from 1.0 to 1.25, the film cooling effectiveness is increase for leading edge without trench and also for all cases. However when the blowing ratio is increase to 1.5, film cooling effectiveness is decrease for all cases. Overall the Case B with blowing ratio 1.25 has the best film cooling effectiveness with significant improvement compared to leading edge without trench and with trench Case A and Case C.

Sign in / Sign up

Export Citation Format

Share Document