A Frequency Domain Analysis of Surface Heat Transfer/Free-Stream Turbulence Interactions in a Transonic Turbine Cascade PDF Download
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Author: David G. Holmberg
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Languages : en
Pages : 0
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The relationship of time resolved surface heat flux to the turbulent free stream flow over a turbine blade is investigated. Measurements are made in a transonic linear cascade with a modern high pressure turbine blade profile. Time resolved direct heat transfer measurements are made with Heat Flux Microsensor (HFM) inserts along the pressure side, and with one HFM directly deposited on the suction surface near the leading edge. Simultaneous velocity measurements are made above the heat flux sensors using miniature hot wire probes. Grids are used to produce two turbulence fields of constant inlet turbulence intensity, Tu=5%, but significantly different integral length scales (Ax). Results are compared with a low free stream turbulence baseline condition. Special emphasis is given to frequency domain analysis of the data via coherence function magnitude and phase, energy spectra, and time auto and cross correlations.
Author: David G. Holmberg
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
The relationship of time resolved surface heat flux to the turbulent free stream flow over a turbine blade is investigated. Measurements are made in a transonic linear cascade with a modern high pressure turbine blade profile. Time resolved direct heat transfer measurements are made with Heat Flux Microsensor (HFM) inserts along the pressure side, and with one HFM directly deposited on the suction surface near the leading edge. Simultaneous velocity measurements are made above the heat flux sensors using miniature hot wire probes. Grids are used to produce two turbulence fields of constant inlet turbulence intensity, Tu=5%, but significantly different integral length scales (Ax). Results are compared with a low free stream turbulence baseline condition. Special emphasis is given to frequency domain analysis of the data via coherence function magnitude and phase, energy spectra, and time auto and cross correlations.
Author: David G. Holmberg
Publisher:
ISBN:
Category :
Languages : en
Pages : 438
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Author:
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Category : Mechanical engineering
Languages : en
Pages : 550
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Author:
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Category :
Languages : en
Pages : 20
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Turbine blade endwall heat transfer measurements are given for a range of Reynolds and Mach numbers. Data were obtained for Reynolds numbers based on inlet conditions of 0.5 and 1.0 x 10(exp 6), for isentropic exit Mach numbers of 1.0 and 1.3, and for freestream turbulence intensities of 0.25% and 7.0%. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with 136 deg of turning and an axial chord of 12.7 cm. The large scale allowed for very detailed measurements of both flow field and surface phenomena. The intent of the work is to provide benchmark quality data for CFD code and model verification. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet. Endwall heat transfer data were obtained using a steady-state liquid crystal technique.
Author:
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Category : Mechanical engineering
Languages : en
Pages : 504
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Category : Gas-turbines
Languages : en
Pages : 684
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Author:
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ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 590
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Annotation Volumes 3A and 3B are part of a five-volume set comprising the proceedings of the June 2002 conference held in the Netherlands. Approximately 125 articles address heat transfer, and manufacturing materials and metallurgy. A sampling of topics: the effect of freestream turbulence on film cooling adiabatic effectiveness; the influence of periodic unsteady inflow conditions on leading edge film cooling; and fluid dynamcis of a pre-swirl rotor-stator system. No subject index. Annotation c. Book News, Inc., Portland, OR (booknews.com).
Author: American Society of Mechanical Engineers
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Category : Mechanical engineering
Languages : en
Pages : 200
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Author:
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ISBN:
Category :
Languages : en
Pages : 171
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The influence of freestream turbulence representative of the flow downstream of a modem gas turbine combustor and the first stage vane on turbine blade heat transfer has been measured and analytically modeled in a linear, transonic turbine cascade. Measurements were performed on a high turning, transonic turbine blade. The facility is capable of heated flow with inlet total temperature of 120 degrees C and inlet total pressure of 10 psig. The Reynolds number based on blade chord and exit conditions (5x10(exp 6)) and the inlet and exit Mach numbers (0.4 and 1.2, respectively) are representative of conditions in a modem gas turbine engine. High intensity, large length-scale freestream turbulence was generated using a passive turbulence-generating grid to simulate the turbulence generated in modem combustors after it has passed through the first stage vane row. The grid produced freestream turbulence with intensity of approximately 10-12% and an integral length scale of 2 cm near the entrance of the cascade passages, which is believed to be representative of the core flow entering a first stage gas turbine rotor blade row. Mean heat transfer results showed an increase in heat transfer coefficient of approximately 8% on the suction surface of the blade, with increases on the pressure surface on the order of two times higher than on the suction surface (approximately 17%). This corresponds to increases in blade surface temperature of 5- 10%, which can significantly reduce the life of a turbine blade. The heat transfer data were compared with correlations from published literature with good agreement.
Author:
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Category :
Languages : en
Pages : 24
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