Measurements of Combustor Velocity and Turbulence Profiles

Goebel, S. G.; Abuaf, N.; Lovett, J.; Lee, C.-P.

doi:10.1115/93-gt-228

Cited by 50 publications

(21 citation statements)

References 4 publications

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“…The A summary of the measured turbulence intensities and length scales for three of the isothermal tests is shown in Table 3. The measured turbulence intensities were found to be in an elevated range from 20% < Tu < 30%, which is consistent with real combustor exit flows as reported by Cameron et al [7], Goebel et al [20], and Van Fossen and Bunker [13]. The main difference between these three tests was the position (porosity) of the center shutter at the inlet of the central chamber.…”

Section: Turbulence Intensity and Length Scalesupporting

confidence: 75%

Experimental Evaluation of an Inlet Profile Generator for High-Pressure Turbine Tests

Barringer

Thole

Polanka

2006

Journal of Turbomachinery

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information © 2006 ASME. This work is copyrighted. One or more of the authors is a U.S. Government employee working within the scope of their Government job; therefore, the U.S. Government is joint owner of the work and has the right to copy, distribute, and use the work. All other rights are reserved by the copyright owner. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING/MONITORING AGENCY ACRONYM(S) AFRL-PR-WP ABSTRACTImproving the performance and durability of gas turbine aircraft engines depends highly on achieving a better understanding of the flow interactions between the combustor and turbine sections. The flow exiting the combustor is very complex, and it is characterized primarily by elevated turbulence and large variations in temperature and pressure. To better understand these effects, the goal of this work is to benchmark an adjustable turbine inlet profile generator for the Turbine Research Facility (TRF) at the Air Force Research Laboratory (AFRL). The research objective was to experimentally evaluate the performance of the non-reacting simulator that was designed to provide representative combustor exit profiles to the inlet of the TRF turbine test section. This paper discusses the verification testing that was completed to benchmark the performance of the generator. Results are presented in the form of temperature and pressure profiles as well as turbulence intensity and length scale. This study shows how one combustor geometry can produce significantly different flow and thermal field conditions entering the turbine. SUBJECT TERMS ABSTRACTImproving the performance and durability of gas turbine aircraft engines depends highly on achieving a better understanding of the flow interactions between the combustor and turbine sections. The flow exiting the combustor is very complex and it is characterized primarily by elevated turbulence and large variations in temperature and pressure. The heat transfer and aerodynamic losses that occur in the turbine passages are driven primarily by these spatial variations. To better understand these effects, the goal of this work is to benchmark an adjustable turbine inlet profile generator for the Turbine Research Facility (TRF) at the Air Force Research Laboratory (AFRL).The research objective was to experimentally evaluate the performance of the non-reacting simulator that was designed to provide representative combustor exit profiles to the inlet of the TRF turbine test section. This paper discusses the...

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Section: Turbulence Intensity and Length Scalesupporting

confidence: 75%

Experimental Evaluation of an Inlet Profile Generator for High-Pressure Turbine Tests

Barringer

Thole

Polanka

2006

Journal of Turbomachinery

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“…Taking account of the experimental finding by Goebei et al (1993) that the turbulence intensity at the exit of combustor was around 10-15 percent on the average, we can roughly estimate the turbulence intensity at nozzle exit from Eq. (A.4), which is easily converted into the value in the coordinate system fixed to the rotor blade as presented in Table A.l.…”

Section: Discussionmentioning

confidence: 99%

Effect of Periodic Wake Passing on Film Effectiveness of Discrete Cooling Holes Around the Leading Edge of a Blunt Body

Funazaki

Yokota

Yamawaki

1997

Journal of Turbomachinery

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Detailed studies are conducted on film effectiveness of discrete cooling holes around the leading edge of a blunt body that is subjected to periodically incoming wakes as well as free-stream turbulence with various levels of intensity. The cooling holes have a configuration similar to that of typical turbine blades except for the spanwise inclination angle. Secondary air is heated so that the temperature difference between the mainstream and secondary air is about 20 K. In this case, the air density ratio of the mainstream and secondary air becomes less than unity, therefore the flow condition encountered in an actual aero-engine cannot be simulated in terms of the density ratio. A spoke-wheel type wake generator is used in this study. In addition, three types of turbulence grids are used to elevate the free-stream turbulence intensity. We adopt three blowing ratios of the secondary air to the mainstream. For each of the blowing ratios, wall temperatures around the surface of the test model are measured by thermocouples situated inside the model. The temperature is visualized using liquid crystals in order to obtain qualitative information of film effectiveness distribution. / Vol. 119, APRIL 1997Transactions of the ASME Copyright © 1997 by ASME Downloaded From: http://turbomachinery.asmedigitalcollection.asme.org/ on 05/13/2015 Terms of Use: http://asme.org/terms Subscripts oo, 2 = mainstream, secondary air 15, 40 = first row, second row

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“…For a variety of gas turbine combustors, the exit turbulence can range between 8% and 30% [1][2][3]. As the now passes the downstream turbine vane passage, the turbulence level still remains high [4].…”

Section: Introductionmentioning

confidence: 98%

Effects of Inlet Turbulence and End-Wall Boundary Layer on Aerothermal Performance of a Transonic Turbine Blade Tip

Zhang

Rawlinson

2014

Journal of Engineering for Gas Turbines and Power

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Most of the previous researches of inlet turbulence effects on blade tip have been carried out for low speed situations. Recent work has indicated that for a transonic turbine tip, turbulent diffusion tends to have a distinctively different impact on tip heat transfer than for its subsonic counterpart. It is hence of interest to examine how inlet turbulence flow conditioning would affect heat transfer characteristics for a transonic tip. The present work is aimed to identify and understand the effects of both inlet freestream turbulence and end wall boundary layer on a transonic turbine blade tip aerothermal performance. Spatially-resolved heat transfer data are obtained at aerodynamic conditions representative of a high-pressure turbine, using the transient infrared thermógraphy technique with the Oxford High-Speed Linear Cascade research facility. With and without turbulence grids, the turbulence levels achieved are 7%-9% and 1%, respectively. On the blade tip surface, no apparent change in heat transfer was observed with high and low inlet turbulence intensity levels investigated. On the blade suction suiface, however, substantially different local heat transfer distributions for the suction side near tip surface have been observed, indicating a strong local dependence of the local vortical flow structure on the freestream turbulence. These experimentally observed trends have also been confirmed by CFD examinations using the Rolls-Royce HYDRA. A further CFD analysis suggests that the level of inflow turbulence alters the balance between the passage vortex associated secondaiy flow and the over tip leakage (OTL) flow. Consequently, an enhanced inertia of near wall fluid at a higher inflow turbulence weakens the cross-passage flow. As such, the weaker passage vortex leads the tip leakage vortex to move further into the mid passage, with the less spanwise coverage on the suction surface, as consistently indicated by the heat transfer signature. Different inlet end wall boundary layer profiles are employed in the computational study with HYDRA. All CFD results indicate the inlet boundary layer thickness has little impact on the heat transfer over the tip surface as well as the pressure side near-tip suiface. However, noticeable changes in heat transfer are obsei-vedfor the suction side near-tip surface. Similar to the inlet turbulence effect, such changes can be attributed to the interaction between the passage vortex and the OTL flow.

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Measurements of Combustor Velocity and Turbulence Profiles

Cited by 50 publications

References 4 publications

Experimental Evaluation of an Inlet Profile Generator for High-Pressure Turbine Tests

Experimental Evaluation of an Inlet Profile Generator for High-Pressure Turbine Tests

Effect of Periodic Wake Passing on Film Effectiveness of Discrete Cooling Holes Around the Leading Edge of a Blunt Body

Effects of Inlet Turbulence and End-Wall Boundary Layer on Aerothermal Performance of a Transonic Turbine Blade Tip

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