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Research Papers

Heat Transfer in Turbine Hub Cavities Adjacent to the Main Gas Path

[+] Author and Article Information
Jeffrey A. Dixon

e-mail: Jeffrey.Dixon@Rolls-Royce.com

Antonio Guijarro Valencia

e-mail: Antonio.guijarrovalencia@Rolls-Royce.com

Andreas Bauknecht

e-mail: Andreas.bauknecht@Rolls-Royce.com
Rolls-Royce plc,
PO Box 31,
Sin-D 66 Derby, UK

Daniel Coren

e-mail: d.d.coren@sussex.ac.uk

Nick Atkins

e-mail: n.r.atkins@sussex.ac.uk
Department of Engineering and Design,
University of Sussex,
BN1 9QT Brighton, UK

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received June 17, 2011; final manuscript received November 29, 2011; published online November 8, 2012. Editor: David Wisler.

J. Turbomach 135(2), 021025 (Nov 08, 2012) (14 pages) Paper No: TURBO-11-1083; doi: 10.1115/1.4006824 History: Received June 17, 2011; Revised November 29, 2011

Reliable means of predicting heat transfer in cavities adjacent to the main gas path are increasingly being sought by engineers involved in the design of gas turbines. In this paper, an interim summary of the results of a five-year research program sponsored by the European Union (EU) and several leading gas turbine manufacturers and universities will be presented. Extensive use is made of computational fluid dynamics (CFD) and finite element (FE) modeling techniques to understand the thermo-mechanical behavior of a turbine stator well cavity, including the interaction of cooling air supply with the main annulus gas. The objective of the study has been to provide a means of optimizing the design of such cavities for maintaining a safe environment for critical parts, such as disc rims and blade fixings, while maximizing the turbine efficiency and minimizing the fuel burn and emissions penalties associated with the secondary airflow system. The modeling methods employed have been validated against data gathered from a dedicated two-stage turbine rig running at engine representative conditions. Extensive measurements are available for a range of flow conditions and alternative cooling arrangements. The analysis method has been used to inform a design change, which is also to be tested. Comparisons are provided between the predictions and measurements of the turbine stator well component temperature.

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References

Figures

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Fig. 4

Cooling flow paths

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Fig. 5

Temperature instrumentation

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Fig. 6

Pressure measurement positions

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Fig. 3

Turbine rig section

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Fig. 2

Turbine rig test facility

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Fig. 1

Typical turbine stator well

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Fig. 7

Finite element model

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Fig. 8

CFD analysis model

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Fig. 9

Interstage rim gap mesh

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Fig. 10

CFD mesh—interface planes

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Fig. 11

Rotor 1 trailing edge model

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Fig. 12

Data comparison positions

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Fig. 13

CFD model validation—main annulus

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Fig. 20

Annulus convergence (1.12% coolant)

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Fig. 15

Absolute total temperature r = 0.115 m

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Fig. 18

Air thermocouple locations

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Fig. 19

(a) Air temperature contours—no coolant. (b) Air temperature contours—no coolant.

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Fig. 14

Examples of the meshing approach

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Fig. 16

Mach number at r = 0.115 m

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Fig. 17

Total pressure at an axial plane

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Fig. 24

Relative total temperature — unsteady solution 0.61% coolant supply

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Fig. 25

Cooling effectiveness 0.61% flow

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Fig. 21

Radial velocities in the front cavity — 1.12% coolant flow

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Fig. 22

Cooling effectiveness 1.12%

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Fig. 23

Radial velocity contour plots 0.61% coolant flow case

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Fig. 26

Predicted effect of cooling flow on thermal effectiveness

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Fig. 27

Thermal effectiveness with different cooling flow levels

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Fig. 29

Measured thermal effectiveness

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Fig. 30

Test section temperature comparison

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Fig. 28

Temperature measurement locations

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