GLORIA

GEOMAR Library Ocean Research Information Access

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
  • 1
    Online Resource
    Online Resource
    American Institute of Aeronautics and Astronautics (AIAA) ; 2005
    In:  Journal of Thermophysics and Heat Transfer Vol. 19, No. 1 ( 2005-01), p. 57-65
    In: Journal of Thermophysics and Heat Transfer, American Institute of Aeronautics and Astronautics (AIAA), Vol. 19, No. 1 ( 2005-01), p. 57-65
    Type of Medium: Online Resource
    ISSN: 0887-8722 , 1533-6808
    Language: English
    Publisher: American Institute of Aeronautics and Astronautics (AIAA)
    Publication Date: 2005
    detail.hit.zdb_id: 2037166-4
    detail.hit.zdb_id: 2026174-3
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
  • 2
    Online Resource
    Online Resource
    American Institute of Aeronautics and Astronautics (AIAA) ; 2000
    In:  Journal of Thermophysics and Heat Transfer Vol. 14, No. 2 ( 2000-04), p. 286-288
    In: Journal of Thermophysics and Heat Transfer, American Institute of Aeronautics and Astronautics (AIAA), Vol. 14, No. 2 ( 2000-04), p. 286-288
    Type of Medium: Online Resource
    ISSN: 0887-8722 , 1533-6808
    Language: English
    Publisher: American Institute of Aeronautics and Astronautics (AIAA)
    Publication Date: 2000
    detail.hit.zdb_id: 2037166-4
    detail.hit.zdb_id: 2026174-3
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
  • 3
    Online Resource
    Online Resource
    American Institute of Aeronautics and Astronautics (AIAA) ; 1999
    In:  Journal of Thermophysics and Heat Transfer Vol. 13, No. 1 ( 1999-01), p. 76-81
    In: Journal of Thermophysics and Heat Transfer, American Institute of Aeronautics and Astronautics (AIAA), Vol. 13, No. 1 ( 1999-01), p. 76-81
    Type of Medium: Online Resource
    ISSN: 0887-8722 , 1533-6808
    Language: English
    Publisher: American Institute of Aeronautics and Astronautics (AIAA)
    Publication Date: 1999
    detail.hit.zdb_id: 2037166-4
    detail.hit.zdb_id: 2026174-3
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
  • 4
    Online Resource
    Online Resource
    ASME International ; 2004
    In:  Journal of Heat Transfer Vol. 126, No. 4 ( 2004-08-01), p. 546-553
    In: Journal of Heat Transfer, ASME International, Vol. 126, No. 4 ( 2004-08-01), p. 546-553
    Abstract: A detailed investigation on the effect of squealer geometries on the blade tip leakage flow and associated heat transfer is presented for a scaled up high pressure turbine blade in a low-speed wind tunnel facility. The linear cascade is made of four blades with the two corner blades acting as guides. The tip profile of a first stage rotor blade is used to fabricate the two-dimensional blade. The wind tunnel accommodates an 116° turn for the blade cascade. The mainstream Reynolds number based on the axial chord length based on cascade exit velocity is 4.83×105. An upstream wake effect is simulated with a spoked wheel wake generator placed upstream of the cascade. A turbulence grid placed even farther upstream generates a free-stream turbulence of 4.8%. The center blade has a tip clearance gap of 1.56% with respect to the blade span. Static pressure measurements are obtained on the blade surface and the shroud. Results show that the presence of the squealer alters the tip gap flow field significantly and produces lower overall heat transfer coefficients. The effects of different squealer arrangements are basically to study the effect of squealer rim placement on tip leakage flow and associated heat transfer. Detailed heat transfer measurements are obtained using a steady state liquid crystal technique. The effect of periodic unsteady wake effect is also investigated by varying the wake Strouhal number from 0–0.4. Results show that suction side squealers may be favorable in terms of overall reduction in heat transfer coefficients over the tip surface. However, the presence of a full squealer is most beneficial in terms of reducing overall heat load on the tip surface. There is reasonable effect of wake induced periodicity on tip heat transfer.
    Type of Medium: Online Resource
    ISSN: 0022-1481 , 1528-8943
    Language: English
    Publisher: ASME International
    Publication Date: 2004
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
  • 5
    Online Resource
    Online Resource
    ASME International ; 2004
    In:  Journal of Turbomachinery Vol. 126, No. 4 ( 2004-10-01), p. 597-603
    In: Journal of Turbomachinery, ASME International, Vol. 126, No. 4 ( 2004-10-01), p. 597-603
    Abstract: In film cooling situations, there is a need to determine both local adiabatic wall temperature and heat transfer coefficient to fully assess the local heat flux into the surface. Typical film cooling situations are termed three temperature problems where the complex interaction between the jets and mainstream dictates the surface temperature. The coolant temperature is much cooler than the mainstream resulting in a mixed temperature in the film region downstream of injection. An infrared thermography technique using a transient surface temperature acquisition is described which determines both the heat transfer coefficient and film effectiveness (nondimensional adiabatic wall temperature) from a single test. Hot mainstream and cooler air injected through discrete holes are imposed suddenly on an ambient temperature surface and the wall temperature response is captured using infrared thermography. The wall temperature and the known mainstream and coolant temperatures are used to determine the two unknowns (the heat transfer coefficient and film effectiveness) at every point on the test surface. The advantage of this technique over existing techniques is the ability to obtain the information using a single transient test. Transient liquid crystal techniques have been one of the standard techniques for determining h and η for turbine film cooling for several years. Liquid crystal techniques do not account for nonuniform initial model temperatures while the transient IR technique measures the entire initial model distribution. The transient liquid crystal technique is very sensitive to the angle of illumination and view while the IR technique is not. The IR technique is more robust in being able to take measurements over a wider temperature range which improves the accuracy of h and η. The IR requires less intensive calibration than liquid crystal techniques. Results are presented for film cooling downstream of a single hole on a turbine blade leading edge model.
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2004
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
  • 6
    In: Journal of Turbomachinery, ASME International, Vol. 133, No. 1 ( 2011-01-01)
    Abstract: Experiments and numerical computations are performed to investigate the convective heat transfer characteristics of a gas turbine can combustor under cold flow conditions in a Reynolds number range between 50,000 and 500,000 with a characteristic swirl number of 0.7. It is observed that the flow field in the combustor is characterized by an expanding swirling flow, which impinges on the liner wall close to the inlet of the combustor. The impinging shear layer is responsible for the peak location of heat transfer augmentation. It is observed that as Reynolds number increases from 50,000 to 500,000, the peak heat transfer augmentation ratio (compared with fully developed pipe flow) reduces from 10.5 to 2.75. This is attributed to the reduction in normalized turbulent kinetic energy in the impinging shear layer, which is strongly dependent on the swirl number that remains constant at 0.7 with Reynolds number. Additionally, the peak location does not change with Reynolds number since the flow structure in the combustor is also a function of the swirl number. The size of the corner recirculation zone near the combustor liner remains the same for all Reynolds numbers and hence the location of shear layer impingement and peak augmentation does not change.
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2011
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
  • 7
    Online Resource
    Online Resource
    ASME International ; 2020
    In:  Journal of Heat Transfer Vol. 142, No. 5 ( 2020-05-01)
    In: Journal of Heat Transfer, ASME International, Vol. 142, No. 5 ( 2020-05-01)
    Abstract: Accurate quantification of local heat transfer coefficient (HTC) is imperative for design and development of heat exchangers for high heat flux dissipation applications. Liquid crystal and infrared thermography (IRT) are typically employed to measure detailed surface temperatures, where local HTC values are calculated by employing suitable conduction models, e.g., one-dimensional (1D) semi-infinite conduction model on a material with the low thermal conductivity and low thermal diffusivity. Often times, this assumption of 1D heat diffusion and ignoring its associated lateral conduction effects leads to significant errors in HTC determination. Prior studies have identified this problem and quantified the associated errors in HTC determination for some representative cooling concepts, by accounting for lateral heat diffusion. In this paper, we have presented a procedure for solution of three-dimensional (3D) transient conduction equation using alternating direction implicit (ADI) method and an error minimization routine to find accurate HTCs at relatively lower computational cost. Representative cases of a single jet and an array jet impingement under maximum crossflow condition have been considered here, for IRT and liquid crystal thermography, respectively. Results indicate that the globally averaged HTC obtained using the 3D model was consistently higher than the conventional 1D model by 7–14%, with deviation levels reaching as high as 20% near the stagnation region. Proposed methodology was computationally efficient and is recommended for studies aimed toward local HTC determination.
    Type of Medium: Online Resource
    ISSN: 0022-1481 , 1528-8943
    Language: English
    Publisher: ASME International
    Publication Date: 2020
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
  • 8
    Online Resource
    Online Resource
    Wiley ; 2012
    In:  AIChE Journal Vol. 58, No. 10 ( 2012-10), p. 3003-3015
    In: AIChE Journal, Wiley, Vol. 58, No. 10 ( 2012-10), p. 3003-3015
    Abstract: Particle image velocimetry was used to investigate the evolution of multiple inlet gas jets located at the distributor base of a two‐dimensional fluidized bed setup. Results were used to estimate the solid circulation rate of the fluidized bed as well as particle‐entrainment into the individual jets. The effects of fluidization velocity, orifice diameter, orifice pitch, particle diameter, and particle density were studied. It was determined from this study that the solid circulation rate linearly increased with an increase in the fluidization velocity until the multiple jet system transitioned from isolated to an interacting system. In the interacting system of jets, the solid circulation increased with fluidization velocity but at a much lower rate. For multiple jet systems, this phenomenon may indicate the presence of an optimum operating condition with high circulation rate and low air input in the bed. © 2011 American Institute of Chemical Engineers AIChE J, 58: 3003–3015, 2012
    Type of Medium: Online Resource
    ISSN: 0001-1541 , 1547-5905
    URL: Issue
    Language: English
    Publisher: Wiley
    Publication Date: 2012
    detail.hit.zdb_id: 2020333-0
    detail.hit.zdb_id: 240008-X
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
  • 9
    In: Journal of Thermal Science and Engineering Applications, ASME International, Vol. 12, No. 6 ( 2020-12-01)
    Type of Medium: Online Resource
    ISSN: 1948-5085 , 1948-5093
    Language: English
    Publisher: ASME International
    Publication Date: 2020
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
  • 10
    Online Resource
    Online Resource
    ASME International ; 2015
    In:  Journal of Thermal Science and Engineering Applications Vol. 7, No. 1 ( 2015-03-01)
    In: Journal of Thermal Science and Engineering Applications, ASME International, Vol. 7, No. 1 ( 2015-03-01)
    Abstract: The study presented in this article provides detailed description about a newly developed experimental technique to determine three key convective heat transfer parameters simultaneously in hot gas path of a modern high pressure turbine–recovery temperature (Tr), heat transfer coefficient (HTC), and adiabatic film cooling effectiveness (Eta). The proposed technique, dual linear regression technique (DLRT), has been developed based on the 1D semi-infinite transient conduction theory, is applicable toward film cooled heat transfer experiments especially under realistic engine environment conditions (high Reynolds number along with high Mach numbers). It addresses the fundamental three temperature problem by a two-test strategy. The current popular technique, curve fitting method (CFM) (Ekkad and Han, 2000, “A Transient Liquid Crystal Thermography Technique for Turbine Heat Transfer Measurements,” Meas. Sci. Technol., 11(7), pp. 957–968), which is widely used in the low speed wind tunnel experiments, is not competent in the transonic transient wind tunnel. The CFM (including schemes for both film cooled and nonfilm cooled experiments) does not provide recovery temperature on the film cooled surface. Instead, it assumes the recovery temperature equal to the mainstream total temperature. Its basic physics model simplifies the initial unsteady flow development within the data reduction period by assuming a step jump in mainstream pressure and temperature, which results in significant under prediction of HTC due to the gradual ramping of the flow Mach/Reynolds number and varying temperature in a transient, cascade wind tunnel facility. The proposed technique is advantageous due to the elimination of these added assumptions and including the effects of compressible flow physics at high speed flow. The detailed discussion on theory and development of the DLRT is followed by validation with analytical calculation and comparisons with the traditional technique by reducing the same set of experimental data. Results indicate that the proposed technique stands out with a higher accuracy and reliability.
    Type of Medium: Online Resource
    ISSN: 1948-5085 , 1948-5093
    Language: English
    Publisher: ASME International
    Publication Date: 2015
    Location Call Number Limitation Availability
    BibTip Others were also interested in ...
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...