Experimental Investigation of the Flow Inside a Water Model of a Gas Turbine Combustor: Part 1—Mean and Turbulent Flowfield

1995 ◽  
Vol 117 (3) ◽  
pp. 450-458 ◽  
Author(s):  
J. J. McGuirk ◽  
J. M. L. M. Palma
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Laser Doppler Velocimetry ◽  
Recirculation Zone ◽  
Water Model ◽  
Doppler Velocimetry ◽  
Flow Conditions ◽  
Gas Turbine Combustor ◽  
High Turbulence ◽  
The Mean

The present study examines the flow inside the water model of a gas turbine combustor, with the two main objectives of increasing the understanding of this type of flow and providing experimental data to assist the development of mathematical models. The main features of the geometry are the interaction between two rows of radially opposed jets penetrating a cross-flowing axial stream with and without swirl, providing a set of data of relevance to all flows containing these features. The results, obtained by laser Doppler velocimetry, showed that under the present flow conditions, the first row of jets penetrate almost radially into the combustor and split after impingement, giving rise to a region of high turbulence intensity and a toroidal recirculation zone in the head of the combustor. Part 1 discusses the mean and turbulent flowfield, and the detailed study of the region near the impingement of the first row of jets is presented in Part 2 of this paper.

Study of the Cold Flow Field of a Multi-Injection Combustor

2009 ◽  
Author(s):  
F. Wang ◽  
Y. Huang ◽  
T. Deng
Keyword(s):  
Experimental Data ◽  
Flow Field ◽  
Gas Turbine ◽  
Recirculation Zone ◽  
Turbulent Model ◽  
Gas Turbine Combustor ◽  
Cold Flow ◽  
Basic Work ◽  
Lining Structure ◽  
Recirculation Zones

Multi-injection combustor (MIC) could extend the steady working range of the whole combustor and reduce emissions therefore, so it is one of the Gas Turbine Combustor (GTC) design direction of future. The cold flow character of MIC is the basic work for MIC designers. Because of the low cost nowadays, the CFD method is a very suitable tool for it. Thus, firstly realizable k-epsilon turbulent model (RKE) and Reynolds stress turbulent model (RSM) were used to simulate the downstream flow field of a double radial swirl-cup amongst a simple tube, and the prediction results are compared with the experimental data which are gained by another researcher in Beihang University. The comparison between the experimental data and the CFD prediction results are shown that in most regions, the prediction results quite agree with the experimental data, and the max error of RKE model and RSM model is about 5% and 3% respectively. So the RKE model can be used for swirl-cup combustor simulation for its low computing cost. Then the RKE model is applied in a single swirl-cup gas turbine combustor and two kinds of multi-injection GTC flow field simulation. In the comparison between one single swirl-cup and nine arranged swirl-cups which all are in the same lining structure, each swirl-cup in MIC has a recirculation zone after its exit. Gradually, the recirculation zones mixed and united together in the downstream region. Finally, the recirculation zones structure turns to be similar to the structure in the single swirl-cup GTC after the primary combustion holes. In the other comparison between two kinds of lining structures which all are fixed with the same multi-injection head, the primary combustion holes affect flow field obviously. All the recirculation zones finished before the former primary combustion holes of the MIC without the primary combustion holes, and the separated recirculation zones form a new recirculation zone close to the primary holes for the MIC with primary holes. So the MIC design should combine with the real combustor lining structure to make a high performance for the whole combustor.

A Numerical Study of Spray Injected in a Gas Turbine Lean Pre-Mixed Pre-Vaporized Combustor

2015 ◽  
Vol 32 (1) ◽  
Author(s):  
Amedeo Amoresano ◽  
Maria Cristina Cameretti ◽  
Raffaele Tuccillo
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Numerical Study ◽  
Fluid Dynamic ◽  
Spray Parameters ◽  
Flow Conditions ◽  
Gas Turbine Combustor ◽  
Flow Solver ◽  
Combustion Simulation ◽  
Fuel Vapour

AbstractThe authors have performed a numerical study to investigate the spray evolution in a modern gas turbine combustor of the Lean Pre-Mixed Pre-vaporized type. The CFD tool is able to simulate the injection conditions, by isolating and studying some specific phenomena. The calculations have been performed by using a 3-D fluid dynamic code, the FLUENT flow solver, by choosing the injection models on the basis of a comparative analysis with some experimental data, in terms of droplet diameters, obtained by PDA technique.In a first phase of the investigation, the numerical simulation refers to non-evaporating flow conditions, in order to validate the estimation of the fundamental spray parameters. Next, the calculations employ boundary conditions close to those occurring in the actual combustor operation, in order to predict the fuel vapour distribution throughout the premixing chamber. The results obtained allow the authors to perform combustion simulation in the whole domain.

scholarly journals Numerical Prediction of Non-Reacting and Reacting Flow in a Model Gas Turbine Combustor

2004 ◽  
Author(s):  
Farhad Davoudzadeh ◽  
Nan-Suey Liu
Keyword(s):  
Experimental Data ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Recirculation Zone ◽  
Three Dimensional ◽  
Flow Characteristics ◽  
Reacting Flow ◽  
Complex Flow ◽  
Gas Turbine Combustor ◽  
Model Gas Turbine Combustor

The three-dimensional, viscous, turbulent, reacting and non-reacting flow characteristics of a model gas turbine combustor operating on air/methane are simulated via an unstructured and massively parallel Reynolds-Averaged Navier-Stokes (RANS) code. This serves to demonstrate the capabilities of the code for design and analysis of real combustor engines. The effects of some design features of combustors are examined. In addition, the computed results are validated against experimental data. The numerical model encompasses the whole experimental flow passage, including the flow development sections for the air annulus and the fuel pipe, twelve channel air and fuel swirlers, the combustion chamber, and the tail pipe. A cubic non-linear low-Reynolds number K-e turbulence model is used to model turbulence, whereas the eddy-breakup model of Magnussen and Hjertager is used to account for the turbulence combustion interaction. Several RANS calculations are performed to determine the effects of the geometrical features of the combustor, and of the grid resolution on the flow field. The final grid is an all-hexahedron grid containing approximately two and one half million elements. To provide an inlet condition to the main combustion chamber, consistent with the experimental data, flow swirlers are adjusted along the flow delivery inlet passage. Fine details of the complex flow structure such as helicalring vortices, recirculation zones and vortex cores are well captured by the simulation. Consistent with the experimental results, the computational model predicts a major recirculation zone in the central region immediately downstream of the fuel nozzle, a second recirculation zone in the upstream corner of the combustion chamber, and a lifted flame. Further, the computed results predict the experimental data with reasonable accuracy for both the cold flow and for the reacting flow. It is also shown that small changes to the geometry can have noticeable effects on the combustor flowfield.

scholarly journals Development of Micro Gas Turbine Combustor with a Recirculation Zone Induced by an Upward Swirl

2008 ◽  
Vol 3 (1) ◽  
pp. 204-215
Author(s):  
Kousaku YOTORIYAMA ◽  
Shunsuke AMANO ◽  
Hidetomo FUJIWARA ◽  
Tomohiko FURUHATA ◽  
Masataka ARAI
Keyword(s):  
Gas Turbine ◽  
Recirculation Zone ◽  
Gas Turbine Combustor ◽  
Micro Gas Turbine

Wall Shear Stress Determination in a Small-Scale Parallel Plate Flow Chamber Using Laser Doppler Velocimetry Under Laminar, Pulsatile and Low-Reynolds Number Turbulent Flows

2018 ◽  
Vol 140 (6) ◽  
Author(s):  
Hamed Avari ◽  
Kem A. Rogers ◽  
Eric Savory
Keyword(s):  
Shear Stress ◽  
Wall Shear Stress ◽  
Laser Doppler Velocimetry ◽  
Parallel Plate ◽  
Flow Chamber ◽  
Laser Doppler ◽  
Small Scale ◽  
Doppler Velocimetry ◽  
Flow Conditions ◽  
Parallel Plate Flow Chamber

The parallel plate flow chamber (PPFC) has gained popularity due to its applications in fields such as biological tissue engineering. However, most of the studies using PPFC refer to theoretical relations for estimating the wall shear stress (WSS) and, hence, the accuracy of such quantifications remains elusive for anything other than steady laminar flow. In the current study, a laser Doppler velocimetry (LDV) method was used to quantify the flow in a PPFC (H = 1.8 mm × W = 17.5 mm, Dh = 3.26 mm, aspect ratio = 9.72) under steady Re = 990, laminar pulsatile (carotid Re0-mean = 282 as well as a non-zero-mean sinusoidal Re0-mean = 45 pulse) and low-Re turbulent Re = 2750 flow conditions. A mini-LDV probe was applied, and the absolute location of the LDV measuring volume with the respect to the wall was determined using a signal monitoring technique with uncertainties being around ±27 μm. The uniformity of the flow across the span of the channel, as well as the WSS assessment for all the flow conditions, was measured with the uncertainties all being less than 16%. At least two points within the viscous sublayer of the low-Re turbulent flow were measured (with the y+ for the first point < 3) and the WSS was determined using two methods with the differences between the two methods being within 5%. This paper for the first time presents the experimental determination of WSS using LDV in a small-scale PPFC under various flow conditions, the challenges associated with each condition, and a comparison between the cases. The present data will be useful for those conducting biological or numerical modeling studies using such devices.

803 Study of a Micro-Gas turbine Combustor with a Recirculation Zone Induced by an Upward Swirl

2005 ◽  
Vol 2005.3 (0) ◽  
pp. 5-6
Author(s):  
Kousaku YOTORIYAMA ◽  
Shunsuke AMANO ◽  
Hidetomo FUJIWARA ◽  
Tomohiko FURUHATA ◽  
Masataka ARAI
Keyword(s):  
Gas Turbine ◽  
Recirculation Zone ◽  
Gas Turbine Combustor ◽  
Micro Gas Turbine

Study of Flame Stability in a Step Swirl Combustor

1996 ◽  
Vol 118 (2) ◽  
pp. 308-315 ◽  
Author(s):  
M. D. Durbin ◽  
M. D. Vangsness ◽  
D. R. Ballal ◽  
V. R. Katta
Keyword(s):  
Gas Turbine ◽  
Recirculation Zone ◽  
Swirling Flow ◽  
Tangential Velocity ◽  
Combustion Stability ◽  
Combustion Model ◽  
Fuel Injector ◽  
Gas Turbine Combustor ◽  
Swirl Combustor ◽  
Radial Profiles

A prime requirement in the design of a modern gas turbine combustor is good combustion stability, especially near lean blowout (LBO), to ensure an adequate stability margin. For an aeroengine, combustor blow-off limits are encountered during low engine speeds at high altitudes over a range of flight Mach numbers. For an industrial combustor, requirements of ultralow NOx emissions coupled with high combustion efficiency demand operation at or close to LBO. In this investigation, a step swirl combustor (SSC) was designed to reproduce the swirling flow pattern present in the vicinity of the fuel injector located in the primary zone of a gas turbine combustor. Different flame shapes, structure, and location were observed and detailed experimental measurements and numerical computations were performed. It was found that certain combinations of outer and inner swirling air flows produce multiple attached flames, aflame with a single attached structure just above the fuel injection tube, and finally for higher inner swirl velocity, the flame lifts from the fuel tube and is stabilized by the inner recirculation zone. The observed difference in LBO between co- and counterswirl configurations is primarily a function of how the flame stabilizes, i.e., attached versus lifted. A turbulent combustion model correctly predicts the attached flame location(s), development of inner recirculation zone, a dimple-shaped flame structure, the flame lift-off height, and radial profiles of mean temperature, axial velocity, and tangential velocity at different axial locations. Finally, the significance and applications of anchored and lifted flames to combustor stability and LBO in practical gas turbine combustors are discussed.

scholarly journals Detailed Flow Measurements at the Exit of a Mixed Flow Turbine Under Steady Flow Conditions

1999 ◽  
Author(s):  
N. Karamanis ◽  
R. F. Martinez-Botas ◽  
C. C. Su
Keyword(s):  
Laser Doppler Velocimetry ◽  
Incidence Angle ◽  
Performance Tests ◽  
Doppler Velocimetry ◽  
Flow Conditions ◽  
Blade Angle ◽  
Mixed Flow ◽  
Flow Measurements ◽  
Flow Investigation ◽  
Improved Performance

A detailed flow investigation downstream of two mixed-flow turbocharger turbines has been carried out at 50% and 70% design speeds, equivalent to 29,400 and 41,300 rpm respectively. The measurement technique used was laser Doppler velocimetry (LDV). The measurements were performed at a plane 9.5 mm behind the rotor trailing edge, they were resolved in a blade-to-blade sense to fully examine the nature of the flow. The results confirmed the performance tests and indicated the improved performance of the rotor with a constant inlet blade angle relative to the rotor with a nominally constant incidence angle.

Sign in / Sign up

Export Citation Format

Share Document