A Transient Flow Facility for the Study of the Thermofluid-Dynamics of a Full Stage Turbine Under Engine Representative Conditions

Ainsworth, R. W.; Schultz, D. L.; Davies, M.; Forth, Cccc; Hilditch, M. A.; Oldfield, M. L. G.; Sheard, Anthony G.

doi:10.1115/88-gt-144

Cited by 40 publications

(25 citation statements)

References 14 publications

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“…This Isentropic Light Piston Tunnel facility has been described in detail in several previous publications (for example, Ainsworth et al, 1988;Ainsworth et al, 1989), and only a brief summary of the test apparatus will be provided here. Previously, this test facility has been used to measure the unsteady pressure and unsteady heat transfer on rotating blades, and more recently the interaction between high-pressure turbine and intermediate-pressure guide vanes (Dietz and Ainsworth, 1992;Garside et al, 1994;Miller et al, 2003).…”

Section: Experimental Approachmentioning

confidence: 99%

An investigation of the heat transfer and static pressure on the over-tip casing wall of an axial turbine operating at engine representative flow conditions. (I). Time-mean results

Thorpe

Yoshino

Ainsworth

et al. 2004

International Journal of Heat and Fluid Flow

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Section: Experimental Approachmentioning

confidence: 99%

An investigation of the heat transfer and static pressure on the over-tip casing wall of an axial turbine operating at engine representative flow conditions. (I). Time-mean results

Thorpe

Yoshino

Ainsworth

et al. 2004

International Journal of Heat and Fluid Flow

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“…Hilditch and Ainsworth [13] established the validity of this approach. The turbine stage is a transonic shroudless turbine of 0.5-m tip diameter as explained in [14]. The specific turbine has 36 NGVs and 60 high-pressure turbine blades.…”

Section: Turbine Stage In the Oxford Rotor Facility Ilptmentioning

confidence: 99%

Turbine Aero-Heat Transfer Studies in Rotating Research Facilities

Camcı

2010

Heat Trans Res

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The present paper deals with the experimental aero-heat transfer studies performed in rotating turbine research facilities. Turbine heat transfer research had significant progress in the last few decades. Since the full-scale operational conditions of a modern gas turbine dictate high temperatures well in excess of 3600 o F and pressure ratios ranging from 20 to 50, experimental forced convection heat transfer research on the gas side of a rotating turbine environment is a technically challenging task. The current paper provides a limited review of turbine heat transfer research in various facilities including short-duration blow-down and large-scale/low-speed turbine systems. Since the final status of any forced convection heat transfer problem is closely related to the detailed structure of momentum transfer in highly 3D, unsteady, rotating, and turbulent viscous flow environment, emphasis will also be placed on pertinent turbine aerodynamic features existing in turbines. The most significant parameters to simulate in a rotating aero-heat transfer facility can be listed as Reynolds number based on the blade chord, Mach number for compressibility and shock wave effects, tip speed, intensity and scale of free-stream turbulence, Strouhal number for the unsteady wake passing effects, free-stream to wall temperature ratio, coolant to free-stream temperature ratio, specific heat ratio, molecular Prandtl number of the operating gas and a rotation number for turbine aero-heat transfer work performed under rotational conditions. A flow coefficient and a loading coefficient defined by the actual turbine hardware are typically maintained during laboratory testing.

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“…Experimental investigations of the unsteady heat transfer to flat blade-tips have been conducted using the Oxford rotor facility (see [15] for a description of the facility). This test facility is a short duration wind tunnel that has been used for more than 15 years to investigate the aerothermal performance of an engine representative shroudless high-pressure turbine [14,16].…”

Section: The Oxford Rotor Facilitymentioning

confidence: 99%

Blade-tip heat transfer in a transonic turbine

Thorpe

Yoshino

Thomas

et al. 2005

Proceedings of the Institution of Mechanical Engineers, Part A:

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The blade-tips of high-pressure turbine blades in a gas turbine engine are subjected to strong convective heat transfer and continued to present a significant design challenge to manufacturers. This paper is concerned with developing an understanding of the unsteady flow physics that influences the blade-tip heat transfer. Experimental investigations of bladetip heat transfer and aerodynamics have been conducted in a transonic turbine stage test facility. The data reveal the effect of vane -rotor interactions on the unsteady heat transfer along the blade-tip mean camber line. In particular, the vane shock and potential field interaction establish characteristic unsteady heat transfer signatures at different axial positions along the blade-tip. The fluctuations in heat transfer are discussed in terms of vane-periodic changes in both relative total temperature and aerodynamic conditions.

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A Transient Flow Facility for the Study of the Thermofluid-Dynamics of a Full Stage Turbine Under Engine Representative Conditions

Cited by 40 publications

References 14 publications

An investigation of the heat transfer and static pressure on the over-tip casing wall of an axial turbine operating at engine representative flow conditions. (I). Time-mean results

An investigation of the heat transfer and static pressure on the over-tip casing wall of an axial turbine operating at engine representative flow conditions. (I). Time-mean results

Turbine Aero-Heat Transfer Studies in Rotating Research Facilities

Blade-tip heat transfer in a transonic turbine

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