Aerodynamic and Heat Transfer Measurements on Blading for a High Rim-Speed Transonic Turbine

Kingcombe, R. C.; Harasgama, S. P.; Leversuch, N. P.; Wedlake, E. T.

doi:10.1115/89-gt-228

Cited by 7 publications

(5 citation statements)

References 4 publications

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“…A simulation using a three-dimensional viscous code should therefore provide useful insight on the physics of the flow within a turbine rotor with inlet temperature distortion. The turbine used for this study has been reported upon previously by Kingcombe, Harasgama et at (1989) and has been designed to operate at a high rim speed to drive an axial compressor of around 20:1 pressure ratio. Details of the turbine stage are shown on Figure 2.…”

Section: Simulation Of Temperature Distortionmentioning

confidence: 99%

Combustor Exit Temperature Distortion Effects on Heat Transfer and Aerodynamics Within a Rotating Turbine Blade Passage

Harasgama¹

1990

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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A numerical simulation of temperature distortion at inlet to a rotating turbine rotor has been performed. A 3D Navier-Stokes code the 2D boundary layer code - STAN5, have been used. The results show that the hot gas is transported to the pressure surface of the blade and that hot gas also migrates to the blade pressure side tip. At locations greater than 50–60% axial chord the hot gas enters the tip-gap and emerges over the suction side. These computations are in agreement with previous experimental results. The secondary flows within the turbine rotor are enhanced by the introduction of inlet radial temperature distortion and this is in accord with previous analytical work. It is shown that the heat flux near the tip region on the pressure side of the blade can be increased by up to 76% due to the re-distribution of the inlet temperature distortion.

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Section: Simulation Of Temperature Distortionmentioning

confidence: 99%

Combustor Exit Temperature Distortion Effects on Heat Transfer and Aerodynamics Within a Rotating Turbine Blade Passage

Harasgama¹

1990

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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“…In order to assess the capability of the present PlY technique In making accurate gas path velocity measurements, L.€ the results are compared with predictions from a fully three-dimensional viscous flow solver. This flow solver, by Rmt Ps ,,, Negative Dawes (1986), has been rigorously evaluated and develo It has been shown to be a reasonably accurate meth of Figure 5 Raw PlY 35mm Negative predicting turbine vane aerodynamics and secondary flows (Kingcombe et al, 1989 and Harasgaa el al, 1990).…”

Section: Results and Comparison With Computationsmentioning

confidence: 99%

The Application of Particle Image Velocimetry (PIV) in a Short-Duration Transonic Annular Turbine Cascade

Bryanston-Cross

Towers

Judge

et al. 1992

Journal of Turbomachinery

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A series of experiments have been performed to demonstrate the application of Particle Image Velocimetry (PIV) to turbomachinery flows. The tests were performed at transonic speeds on a fully annular engine size turbine nozzle guide vane. The vane cascade was installed in a short-duration Isentropic Light Piston Cascade (ILPC) test facility operating with high inlet turbulence levels. The technique has been shown to map the whole flow field with a resolution of 0.5 mm. The quality of the results obtained is not significantly affected by local turbulence rates. The accuracy of the measurements is put at around 4 percent of absolute velocity and is limited by the quality of the image on the film plane. The velocities derived from the PIV images have been compared with predictions from a three-dimensional viscous numerical calculation. It is shown that the experimental and predicted results are in good agreement. It is considered that this technique has considerable potential in application to turbomachinery flow field diagnostics.

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“…This flow solver, by Dawes (1986), has been rigorously evaluated and developed. It has been shown to be a reasonably accurate method of predicting turbine vane aerodynamics and secondary flows (Kingcombe et al, 1989 andHarasgama et al, 1990).…”

Section: Results and Comparison With Computationsmentioning

confidence: 99%

The Application of Particle Image Velocimetry (PIV) in a Short Duration Transonic Annular Turbine Cascade

Bryanston-Cross

Towers

Judge

et al. 1991

Volume 1: Turbomachinery

Self Cite

View full text Add to dashboard Cite

A series of experiments have been performed to demonstrate the application of Particle Image Velocimetry (PIV) to turbomachinery flows. The tests were performed at transonic speeds on a fully annular engine size turbine nozzle guide vane. The vane cascade was installed in a short duration Isentropic Light Piston Cascade (ILPC) test facility operating with high inlet turbulence levels. The technique has been shown to map the whole flow field with a resolution of 0.5 mm. The quality of the results obtained are not significantly affected by local turbulence rates. The accuracy of the measurements is put at around 4% of absolute velocity and is limited by the quality of the image on the film plane. The velocities derived from the PIV images have been compared with predictions from a three-dimensional viscous numerical calculation. It is shown that the experimental and predicted results are in good agreement. It is considered that this technique has considerable potential in application to turbomachinery flow field diagnostics.

show abstract

Aerodynamic and Heat Transfer Measurements on Blading for a High Rim-Speed Transonic Turbine

Cited by 7 publications

References 4 publications

Combustor Exit Temperature Distortion Effects on Heat Transfer and Aerodynamics Within a Rotating Turbine Blade Passage

Combustor Exit Temperature Distortion Effects on Heat Transfer and Aerodynamics Within a Rotating Turbine Blade Passage

The Application of Particle Image Velocimetry (PIV) in a Short-Duration Transonic Annular Turbine Cascade

The Application of Particle Image Velocimetry (PIV) in a Short Duration Transonic Annular Turbine Cascade

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