## Approved

VBI3D Calculation: Purdue Turbine Rig 1st

VB13D Prodictbn Ol Retort Unsteady Pressure at OOTC Span

VBI3D Calculation: Purdue Turbine Rig 1st

VB13U Prediction ':t Ha toil Unsteady Pressure at 1 v/a Span

VBI3D Calculation: Purdue Tuibine Rig 1st

VBI8Q Prodictbn of Rotor 1 Unsteady Prossuro at StBC Spiffi

VBI3D Calculation: Purdue Turbine Rig 1st

VB13D Prodictbn Ol Retort Unsteady Pressure at OOTC Span

VBI3D Calculation: Purdue Turbine Rig 1st

VB13U Prediction ':t Ha toil Unsteady Pressure at 1 v/a Span

VBI3D Calculation: Purdue Tuibine Rig 1st

VBI8Q Prodictbn of Rotor 1 Unsteady Prossuro at StBC Spiffi

Figure 6. Illustrations of the unsteady envelope of the maximum, minimum, and time mean static pressure on the surface of the

Figure 6. Illustrations of the unsteady envelope of the maximum, minimum, and time mean static pressure on the surface of the

Figure 7 is an image of the near surface particle traces for the vane suction surface and the blade pressure surface showing the extent of secondary flow in the blade passage, particularly near the endwalls. Near the vane suction surface, flow from the endwall region was driven radially toward midspan. On the pressure surface of the blade, flow was pushed radially toward the endwalls. The flow at the tip was forced into and through the tip clearance region. Figure 8 shows particle traces near the pressure surface of the vane and the suction surface of the blade. The fluid on the pressure surface of the vane was pressed towards the endwalls, but there was not a great deal of flow migration. On the other hand, the suction surface of the blade indicates that as the flow moves downstream, there was flow migration from the hub towards midspan with probable flow separation near the hub. The secondary flow new the tip, which also migrates toward midspan, was heavily influenced by the tip clearance flow.

PROPRIETARY RIGHTS LEGEND This technical data and the information embodied herein is the property of and proprietary to Rolls-Royce Corporation, and shall not, without prior written permission of Rolls-Royce Corporation, be disclosed in whole or in part to third parties. This legend shall be included on any reproduction of this data in whole or in part. Copyright 2000 - Rolls-Royce Corporation. (unpubBshed)

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