List Of References

Bayley, F.J., and Owen, J.M., 1970, "The Fluid Dynamics of a Shrouded Disk System With a Radial Outflow of Coolant," ASME Journal of Engineering for Power, Vol. 92, pp. 335-341.

Blair, M.F., 1994, "Experimental Study of Heat Transfer in a Large-Scale Turbine Rotor Passage," ASME Journal of Turbomachinery, Vol. 116, pp. 1-13.

Chew, J.W., 1991, "A Theoretical Study Of Ingress For Shrouded Rotating Disk Systems With Radial Outflow," ASME Journal of Turbomachinery, Vol. 113, pp. 91-97.

Chew, J.W., Green, T., and Turner, A.B., 1994, "Rim Sealing of Rotor-Stator Wheelspaces in the Presence of External Flow," ASME Paper 94-GT-126.

Denton, J. D., and Usui, S., 1981, "Use of a Tracer Gas Technique to Study Mixing in a Low Speed Turbine," ASME Paper 81-GT-86.

El-Oun, Z.B., Neller, P.H., and Turner, A. B., 1988, "Sealing of a Shrouded Rotor-Stator System with Preswirl Coolant," ASME Journal of Turbomachinery, Vol. 110, pp. 218225.

Friedrichs, S., Hodson, H.P. and Dawes, W.N., 1996, "Distribution of Film-Cooling Effectiveness on a Turbine Endwall Measured Using the Ammonia and Diazo Technique," ASME Journal of Turbomachinery, Vol. 118, pp. 613-621.

Gallier, K.D., Lawless, P.B., and Fleeter, S, 2000, "Investigation of Seal Purge Flow Effects on the Hub Flow Field In a Turbine Stage Using Particle Image Velocimetry," AIAA Paper 2000-3370.

Gaugler, R.E., and Russell, L.M., 1983, "Comparison Of Visualized Turbine Endwall Secondary Flows And Measured Heat Transfer Patterns," ASME Paper 83-GT-83.

Goldman, L.J., and McLallin, K.L., 1977, "Effect of Endwall Cooling on Secondary Flows in Turbine Stator Vanes," AGARD CP-214.

Granser D., and Schulenberg T., 1990, "Prediction And Measurement Of Film Cooling Effectiveness For A First-Stage Turbine Vane Shroud," ASME Paper 90-GT-95.

Green, T. and Turner A.B., 1994, "Ingestion Into the Upstream Wheelspace of an Axial Turbine Stage," ASME Journal of Turbomachinery, Vol. 116, pp. 327-332.

Hamabe, K., Ishida, K.,. Tanizawa, T., Shiraha, M., and Kimoto, H., 1993, "Heat Transfer Coefficient Distribution On Blade Surfaces And Platform Of Gas Turbine Cascade," JSME International Journal. Series B, Fluids and Thermal Engineering., Vol. 59, pp. 2536-2542.

Hartland, J.C., Gregory-Smith, D.G., and Rose, M.G., 1998, "Non-Axisymmetric Endwall Profiling In A Turbine Rotor Blade," ASME Paper 98-GT-525,.

Heidegger, N.J., Hall, E.J., and Delaney, R.A., 1996, "Parameterized Study of HighSpeed Compressor Seal Cavity Flow," AIAA Paper 96-2807.

Hills, N.J., Green, T., Turner, A., and Chew, J.W., 1997, "Aerodynamics Of Turbine Rim Seal Ingestion," ASME Paper 97-GT-268.

Izenson, M.G., Swift, W.L., and Aungier, R.H., 1994, "Sealing Flow Requirements For A Rotating Disk With External Swirling Flow," ASME Paper 94-GT-86.

Johnson, B.V., Mack, G.J., Paolillo, R.E., and Daniels, W.A., 1994, "Turbine Rim Seal Gas Path Flow Ingestion Mechanisms," AIAA Paper 94-2703.

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Appendix A Four Plane, Axial Velocity Contours, High Seal Flow Rate

Figure A.1 Vane plane A is at time t=6GG.

Figure A.2 Vane plane A is at time t=675.

Figure A.3 Vane plane A is at time t=000

Figure A.4 Vane plane A is at time t=075.

Figure A.5 Vane plane A is at time t=15G.

Figure A.6 Vane plane A is at time t=225.

Figure A.7 Vane plane A is at time t=300.

Figure A.8 Vane plane A is at time t=375.

Figure A.9 Vane plane A is at time t=450.

Figure A.10 Vane plane A is at time t=525.

Appendix B Four Plane, Low Seal Flow Rate, Axial Velocity Contours

Figure B.1 Vane plane A is at time t=6GG.

Figure B.2 Vane plane A is at time t=675.

Figure B.3 Vane plane A is at time t=000.

Figure B.4 Vane plane A is at time t=075.

Figure B.5 Vane plane A is at time t=15G.

Figure B.6 Vane plane A is at time t=225.

Figure B.7 Vane plane A is at time t=300.

Figure B.8 Vane plane A is at time t=375.

Figure B.9 Vane plane A is at time t=450.

Figure B.1G Vane plane A is at time t=525.

Appendix C Four Plane, High Seal Flow Rate Vorticity Contours

Figure C.1 Vane plane A is at time t=600.

Figure C.2 Vane plane A is at time t=675.

Figure C.3 Vane plane A is at time t=000.

Figure C.4 Vane plane A is at time t=075.

Figure C.5 Vane plane A is at time t=150.

Figure C.6 Vane plane A is at time t=225.

Figure C.7 Vane plane A is at time t=300.

Figure C.8 Vane plane A is at time t=375.

Figure C.9 Vane plane A is at time t=450.

Figure C.10 Vane plane A is at time t=525.

Appendix D Four Plane, Low Seal Flow Rate Vorticity Contour

Figure D.1 Vane plane A is at time t=600.

Figure D.2 Vane plane A is at time t=675.

Figure D.3 Vane plane A is at time t=000.

Figure D.4 Vane plane A is at time t=075.

Figure D.5 Vane plane A is at time t=150.

Figure D.6 Vane plane A is at time t=225.

Figure D.7 Vane plane A is at time t=300.

Figure D.8 Vane plane A is at time t=375.

Figure D.9 Vane plane A is at time t=450.

Figure D.10 Vane plane A is at time t=525.

Figure E.1 Vane plane A is at time t=600.

Figure E.2 Vane plane A is at time t=675.

Figure E.3 Vane plane A is at time t=000.

Figure E.4 Vane plane A is at time t=075.

Figure E.5 Vane plane A is at time t=150.

Figure E.6 Vane plane A is at time t=225.

Figure E.7 Vane plane A is at time t=300.

Figure E.8 Vane plane A is at time t=375.

Figure E.9 Vane plane A is at time t=450.

Figure E.10 Vane plane A is at time t=525.

Appendix F Regions Of Negative Radial Velocity For The Low Seal Flow Case

Figure F.1 Vane plane A is at time t=600.

Figure F.2 Vane plane A is at time t=675.

Figure F.3 Vane plane A is at time t=000.

Figure F.4 Vane plane A is at time t=075.

Figure F.5 Vane plane A is at time t=150.

Figure F.6 Vane plane A is at time t=225.

Figure F.7 Vane plane A is at time t=300.

Figure F.8 Vane plane A is at time t=375.

Figure F.9 Vane plane A is at time t=450.

Figure F.10 Vane plane A is at time t=525.

Appendix G 2-Dimensioanl Representation Of Vector Field For Vane Position A At A

High Seal Flow Rate

Figure G.1 Vane plane A is at time t=600.

Figure G.2 Vane plane A is at time t=675.

Figure G.3 Vane plane A is at time t=000.

Figure G.4 Vane plane A is at time t=075.

Figure G.5 Vane plane A is at time t=150.

Figure G.6 Vane plane A is at time t=225.

Figure G.7 Vane plane A is at time t=300.

Figure G.8 Vane plane A is at time t=375.

Figure G.9 Vane plane A is at time t=450.

Figure G.10 Vane plane A is at time t=525.

Appendix H 2-Dimensioanl Representation Of Vector Field For Vane Position A At A

Low Seal Flow Rate

Figure H.1 Vane plane A is at time t=600.

Figure H.2 Vane plane A is at time t=675.

Figure H.3 Vane plane A is at time t=000.

Figure H.4 Vane plane A is at time t=075.

Figure H.5 Vane plane A is at time t=150.

Figure H.6 Vane plane A is at time t=225.

Figure H.7 Vane plane A is at time t=300.

Figure H.8 Vane plane A is at time t=375.

Figure H.9 Vane plane A is at time t=450.

Figure H.10 Vane plane A is at time t=525.

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 parti**. This legend shall be included on any reproduction of this data in Whole or in pail Copyright 2000 - RoHs-Royce Corporation, (unpublished)

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