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- W2322337274 abstract "This paper presents results from a endwall study of the tip-gap flow in a low-speed linear compressor cascade wind tunnel at Virginia Tech. The endwall pressure measurements were made on a stationary endwall to obtain the flow features and to determine the measurement profiles of interest. A custom-made miniature 3-orthogonal-velocity-component fiber-optic laser-Doppler velocimetry (LDV) system was used to measure all three components of velocity within a 50 µm spherical measurement volume within the viscous sublayer of the endwall. The endwall high lateral pressure gradient changed U up to 20% after the correction of the pressure gradient. The chord, pitch, and span of the blade was 30.0 cm, 18.0cm, and 43.5cm, respectively. The stagger and inlet flow angle from the axial direction was 22.2 and 45.0 . The Reynolds number based on the chord was 500,000 and the displacement thickness of the inlet endwall boundary layer 140% chord upstream was 2.9 mm. Detailed velocity profiles were acquired with 25 points across the gap at ten chordwise locations. The data displayed similar patterns of leakage flow velocity at the tip gap for two dierent gap sizes. The exit velocity results showed the relationship between the tip leakage flow and the total pressure loss. A core of very low loss fluid bounded by the endwall and a free shear layer at about 75% of the gap height occurred from near the minimum pressure location and all the downstream measurement location. Accordingly, the flow velocity and direction remained nearly invariant in the core. However, the flow direction varied 50 across the shear layer bounded on the surface of the blade tip end. The total pressure and turbulence intensity inside the 4% gap were further measured at the 65% chord plane in the same facility with the same Pitot probe above. 3 For the measurement of turbulence intensity from the near endwall to the blade tip using a single subminiature hot-wire probe with the prongs bent forward to be inserted through the endwall, it was assumed that turbulence in the gap is isotropic so that the probe stayed in the same direction to measure the fluctuating component of velocity normal to the probe. The acquired data demonstrated that the pressure loss and turbulence intensity were negligible around the mid gap while they were huge in the two shear layers bounded on the endwall and the blade tip surface. Static pressure on the blade tip end was measured with 1.0% to 4.0% gaps and provided the signature of flow attachment on the blade tip. The endwall static pressure, the tip blade loading, and the exit velocity of the gap flow were later reported in the same facility above. 4 The endwall pressure distribution exhibited the dierent" @default.
- W2322337274 created "2016-06-24" @default.
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- W2322337274 date "2006-07-09" @default.
- W2322337274 modified "2023-09-26" @default.
- W2322337274 title "Endwall Pressure Measurement and Skin Friction Correction of a Compressor Cascade" @default.
- W2322337274 cites W1983896742 @default.
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- W2322337274 doi "https://doi.org/10.2514/6.2006-4457" @default.
- W2322337274 hasPublicationYear "2006" @default.
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