Velocity and turbulence measurements in combustion systems

Goldstein, R. J.; Lau, K. Y.; Leung, Chuk-Ling

doi:10.1007/bf00266261

Cited by 32 publications

(16 citation statements)

References 4 publications

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“…For the combustors simulated, the non-reacting simulations produced maximum turbulence levels of 8.7 and 9.0%, while for the reacting case, the turbulence levels were 9.2 and 9.3%. These finding contradict those found by Goldstein et al (1983).…”

Section: Non-reacting and Reacting Studiescontrasting

confidence: 84%

“…Combustor models used by Goldstein, Lau, and Leung (1983), which include their first combustor with the entry holes for the secondary air arranged axisymmetrically, and the General Electric Company combustor with secondary holes arranged non-symmetrically................38…”

Section: Figure 225mentioning

confidence: 99%

“…Combustor models used by Goldstein, Lau, and Leung (1983). Above, the first combustor with the entry holes for the secondary air arranged axisymmetrically.…”

Section: Figure 225mentioning

confidence: 99%

See 2 more Smart Citations

Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine

Vakil

Thole

2005

Journal of Engineering for Gas Turbines and Power

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The highly competitive gas turbine industry has been motivated by consumer demands for higher power-to-weight ratios, increased thermal efficiencies, and reliability while maintaining affordability. In its continual quest, the industry must continually try to raise the turbine inlet temperature, which according to the well-known Brayton cycle is key to higher engine efficiencies. The desire for increased turbine inlet temperatures creates an extremely harsh environment for the combustor liner in addition to the components downstream of the combustor. Shear layers between the dilution jets and the mainstream, as well as combustor liner film-cooling interactions create a complex mean flow field within the combustor, which is not easy to model. A completely uniform temperature and velocity profile at the combustor exit is desirable from the standpoint of reducing the secondary flows in the turbine. However, this seldom occurs due to a lack of thorough mixing within the combustor. Poor mixing results in non-uniformities, such as hot streaks, and allow non-combusted fuel to exit the combustor.This investigation developed a database documenting the thermal and flow characteristics within a combustor simulator representative of the flowfield within a gas turbine aero-engine. Three-and two-component laser Doppler velocimeter measurements were completed to quantify the flow and turbulence fields, while a thermocouple rake was used to quantify the thermal fields.The measured results show very high turbulence levels due to the dilution flow injection. Directly downstream of the dilution jets, an increased thickness in the filmcooling was noted with a fairly non-homogeneous temperature field across the combustor width. A highly turbulent shear layer was found at the leading edge of the dilution jets. Measurements also showed that a relatively extensive recirculation region existed downstream of the dilution jets. Despite the lack of film-cooling injection at the trailing edge of the dilution hole, there existed coolant flow indicative of a horse-shoe vortex wrapping around the jet. As a result of the dilution jet interaction with the mainstream flow, kidney-shaped thermal fields and counter-rotating vortices developed. These vortices serve to enhance combustor mixing.iii

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Section: Non-reacting and Reacting Studiescontrasting

confidence: 84%

Section: Figure 225mentioning

confidence: 99%

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Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine

Vakil

Thole

2005

Journal of Engineering for Gas Turbines and Power

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“…Heat transfer augmentation was predicted well by correlations. The reported turbulence levels exiting the combustor were somewhat higher than measured by other researchers (Goldstein, et al, 1983, Kuotmos and McGuirk, 1989and Ames 1994 where levels of 20-25%…”

Section: Cylinder Experimentscontrasting

confidence: 54%

Effects of High Intensity, Large-Scale Freestream Combustor Turbulence on Heat Transfer in Transonic Turbine Blades

Nix¹,

Diller²,

Ng³

2003

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“…In determining ReaQ, the relative RMS values (u'/U) measured in the "cold flow" experiments are used, since velocity measurements could not be performed for the large heating rates produced by combustion. This procedure is justified by the experiments of Goldstein et al (1983) who performed LDA-measurements in a combustion system similar to the turbulence grid used here, and found that the values of (u'/U) did not change in comparison to the cold flow conditions. For the measurements of (u'/[7), see Oberste-Lehn (1991).…”

Section: Aqmentioning

confidence: 99%

Speckle optical measurement of a turbulent scalar field with high fluctuation amplitudes

Oberste-Lehn

Merzkirch

1993

Experiments in Fluids

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A turbulent temperature field is produced in the gas flow downstream of a turbulence grid by passing the flow through a plane combustion front at the grid that serves as a flame holder. RMS values of the temperature fluctuations of up to 33 K are generated thereby. Properties of the turbulent scalar are measured with an optical speckle technique. The experimental results are compared with theoretical models described by Rotta (1972) and Driscoll and Kennedy (1985). From this comparison it is evident that, even at these high fluctuation amplitudes, the turbulent temperature field still behaves as a passive scalar.

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Velocity and turbulence measurements in combustion systems

Cited by 32 publications

References 4 publications

Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine

Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine

Effects of High Intensity, Large-Scale Freestream Combustor Turbulence on Heat Transfer in Transonic Turbine Blades

Speckle optical measurement of a turbulent scalar field with high fluctuation amplitudes

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