LDV measurements in an annular combustor model

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Purdue University, School of Aeronautics and Astronautics, For sale by the National Technical Information Service , West Lafayette, Ind, [Springfield, Va
Lasers., Turbul
Statementby Dean A. Barron.
SeriesNASA-CR -- 182207., NASA contractor report -- NASA CR-182207.
ContributionsUnited States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v .
ID Numbers
Open LibraryOL15289378M

This thesis covers the design and setup of a laser doppler velocimeter (LDV) system used to take velocity measurements in an annular combustor model. The annular combustor model is of contemporary design using 60 degree flat vane swirlers, producing a strong recirculation zone.

Detailed measurements are taken of the swirler inlet air flow and of the downstream enclosed swirling flow. The laser system Author: Dean A. Barron. LDV Measurements in an Annular Combustor Model. Professor: John P. Sullivan. x Major This thesis covers the design and setup of a LDV system used to take velocity measurements in an annular combustor model.

The annular combustor model is of contemporary design using 60 degree flat vane swirlers, producing a strong recirculation zone. Detailed. Get this from a library. LDV measurements in an annular combustor model.

[Dean A Barron; United States. National Aeronautics and Space Administration.]. This thesis covers the design and setup of a laser doppler velocimeter (LDV) system used to take velocity measurements in an annular combustor model. The annular combustor model is of contemporary design using 60 degree flat vane swirlers, producing a strong recirculation zone.

Detailed measurements are taken of the swirler inlet air flow and of the downstream enclosed swirling flow. The laser system Author: Dean A. Barron.

Details LDV measurements in an annular combustor model EPUB

The design and setup of a Laser Doppler Velocimeter (LDV) system used to take velocity measurements in an annular combustor model are covered. The annular combustor model is of contemporary design using 60 degree flat vane swirlers, producing a strong recirculation zone.

Detailed LDV measurements in an annular combustor model book are taken of the swirler inlet air flow and of the downstream enclosed swirling flow.

The laser system. Results of three-component Laser Doppler Velocimeter (LDV) measurements in an annular combustor-diffuser system are presented in this paper.

The LDV measurements were made at several locations in the prediffuser and dump regions of the combustor-diffuser test rig for three different inlet velocity profiles. LDV Measurements of Flowfield NOMENCLATURE H combustor height, 30 mm k turbulent kinetic energy, m2/s2 La dome height, 15 mm mass flow rate, kg/s rhi, total inlet mass flow rate, kg/s Rec combustor Reynolds number (-= PUREFH/t~t), di- mensionless U axial mean velocity, m/s UREF combustor bulk mean velocity, m/s u' axial turbulence intensity, m/s - u--v turbulent shear stress, Cited by: 4.

Results of three-component Laser Doppler Velocimeter (LDV) measurements in an annular combustor-diffuser system are presented in this paper. The LDV measurements were made at several locations in the prediffuser and dump regions of the combustor.

LDV Measurements of Confined Vortex Breakdown Generated by a Rotating Cone Experimental Investigation of the Flow Inside a Water Model of a Gas Turbine Combustor: Part 1—Mean and Turbulent FlowfieldCited by: Detailed Measurements on a Modern Combustor Dump Diffuser System of the Aerodynamic Performance of an Annular Combustor-Diffuser System,” Paper No.

AIAA, 5. Hestermann, R., Kim, S., and Wittig, S., “Geometrical Dependence of the Fluid Dynamic Performance Parameters of Plane Combustor Model Diffusers,” AIAA ISABE Cited by: A gas turbine model combustor (GTMC) as seen in Fig.

2[5] is used to study acoustic behavior and performance. The injector consists of a central air nozzle, an annular fuel nozzle, and a co-annular air nozzle.

Both air nozzles supply swirling dry air at atmospheric pressure and temperature from a common plenum. The inner air nozzle has an outer. Abstract. The flow within the combustors of gas-turbine engines is considered in terms of measurements of velocity, temperature and major species concentrations to demonstrate the influence of geometry, combustion, preheat temperature and : S.

Chow, D. Tse, J. Whitelaw. A database for the complex turbulent flow of a confined double annular burner in cold conditions is presented here. In the region close to the exit of the annular nozzles LDV measurements at Detailed measurements of velocity statistics, temperature distribution, flame chemiluminescence, and emission characteristics in a lean direct fuel injection multiswirl gas turbine combustor are.

The gas turbine model combustor is schematically shown in Fig. burner was a modified version of a practical gas turbine combustor with an air blast nozzle for liquid -swirling dry air at room temperature was supplied to the flame through a central nozzle (diameter 15 mm) and an annular nozzle (i.d.

17 mm, o.d. 25 mm contoured to an outer diameter of 40 mm).Cited by: The design and setup of a Laser Doppler Velocimeter (LDV) system used to take velocity measurements in an annular combustor model are covered.

The annular.

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This thesis covers the design and setup of a LDV system used to take velocity measurements in an annular combustor model. The annular combustor model is of contemporary design using 60 degree flat vane swirlers, producing a strong recirculation zone.

Detailed measurements are taken of. Azimuthal instabilities in annular combustors: standing and spinning modes Bluff-Body Stabilized Flame, Part II: Flame Response Modeling and Comparison with Measurements. Combustion Science and Technology, Vol. Issue. 7, p. Entropy and Vorticity Waves in an Annular Model Combustor and Nozzle for the Prediction of the Ratio Cited by: Flow experiments were conducted in an approximately one-third geometric scale, deg annular test model simulating practical details of the prototype including the support struts, transition pieces, impingement sleeves, and can-annular combustors.

Wall static pressures and velocity profiles were measured at selected locations in the test by:   In some cases, a multinozzle combustor may exhibit flowfields in which individual nozzles hold two distinct flow or flame shapes in an alternating pattern. This study presents flowfield measurements for nonreacting and reacting flows in a rectangular combustor with two adjacent swirl-stabilizing nozzles at varying internozzle : Brian Dolan, Rodrigo Villalva Gomez, Spencer Pack, Ephraim Gutmark.

A comparison with earlier measurements in the same combustor burning gaseous propane suggests that the flow field and mixing rates are similar for both fuels. The maximum levels of CO are found to be effectively independent of AFR with maximum concentrations of about 6% arising under slightly fuel rich conditions in both : W.

Jones, A. Tober. texts All Books All Texts latest This Just In Smithsonian Libraries FEDLINK (US) Genealogy Lincoln Collection. National Emergency Full text of "An Experimental Study of Swirling Flows as Applied to Annular Combustors".

CiteSeerX - Document Details (Isaac Councill, Lee Giles, Pradeep Teregowda): A two-component fibre-optic laser Doppler velocimeter (LDV) system has been employed to measure the flowfield characteristics of a confined, isothermal strongly swirling flow in a combustor model.

The primary objectives are to understand such complex flowfields and to provide complete benchmark data for. The size of the combustor is m in the Z direction, m in the Y direction, and m in the X direction.

A quality mesh was generated for the can annular combustor (see Fig. 1(b)). (a) Geometry model (b) Meshes for combustor. Fig. Geometry and meshes of the gas turbine can annular combustor. Towards the Prediction of Combustion Noise in a Gas Turbine Combustor 5 Figure 3. Sketch of the combustion chamber setup used for the model experiments.

1 Nm /h of methane gas to a thermal capacity of 10 kW with an equivalence ratio of and a. Laser Doppler Velocimetry (LDV) was used to obtain time-averaged statistics for the three components of velocity at various axial positions across the combustor and laser Raman spectroscopy was used for species, mixture fra ction, and temperature measurements.

In addi-Cited by: 4. LDV measurements in the nozzle region of a confined double annular burner: statistical analysis and model evaluation F.

Schmitt, Ch. Hirsch, B. Hazarika VUB, Dept. of Fluid Mechanics Pleinlaan 2, B Brussels, Belgium Email: [email protected] ABSTRACT Industrial devices designed to handle fluid quite often create complex turbulent.

Gas turbine combustor design involves the calculation of “annular combustor 1” and “annular combustor 2”, as well as a reverse flow combustor. The annular combustors were selected as and c onvergence for the reverse flow combustor model was slightly slower t han for the annular Size: KB.

Wireframe CATIA model of Annular Combustor Model with Flat Swirl ⅲ) Annular Combustor Model with Curved Type Swirl Fig 3. Wireframe CATIA model of Annular Combustor Model with Curved Type Swirl Fig 4. ⅱ C) CFD FLUENT ANALYSIS The designed CATIA system was imported into the CFD fluent development framework in the ANSYS : J.

Sumendran, Kamal Raj Chandra Shekar, G.

Description LDV measurements in an annular combustor model EPUB

Jegadeeswari, B. Kirubadura. The model evaluated for different models. ABSTRACT. This work is measured to be a foremost factor in the growth of an annular combustor. For measure the values for the annular geometry, an analytical approach is used. The dissimilar dimensions of the combustor are gritty dependent on dissimilar mathematical : J.

Sumendran, Kamal Raj Chandra Shekar, G. Jegadeeswari, B. Kirubadura. @article{osti_, title = {Flow field and performance characteristics of combustor diffusers: A basic study}, author = {Hestermann, R and Kim, S and Ben Khaled, A and Wittig, S}, abstractNote = {Results of a detailed study concerning the influence of geometric as well as fluid mechanic parameters o the performance of a plane model combustor diffuser in cold flow are presented.dump combustor model.

The results obtained for free vortex swirler (S = )indicated that generalized feed forward in LDV measurements was corrected in this study by the use Three-dimensional Turbulent Swirling Flow Reconstruction Using Artificial Neural Networks.Abstract The axial and transverse mean velocity and turbulence intensity components as well as Reynolds stresses and turbulent kinetic energy were measured by using a four-beam two-color LDV system for the isothermal flowfield of a simulated combustor that consisted of a plexiglass rectangular duct with two opposing deg side inlets and one axial inlet.