Optimization of cooling systems within gas turbine engines is of great interest to engine manufacturers seeking gains in performance, efficiency, and component life. The effectiveness of coolant delivery is governed by complex flows within the stator wells and the interaction of main annulus and cooling air in the vicinity of the rim seals. This paper reports on the development of a test facility which allows the interaction of cooling air and main gas paths to be measured at conditions representative of those found in modern gas turbine engines. The test facility features a two stage turbine with an overall pressure ratio of approximately 2.6:1. Hot air is supplied to the main annulus using a Rolls-Royce PLC Dart compressor driven by an aero-derivative engine plant. Cooling air can be delivered to the stator wells at multiple locations and at a range of flow rates which cover bulk ingestion through to bulk egress. The facility has been designed with adaptable geometry to enable rapid changes of cooling air path configuration. The coolant delivery system allows swift and accurate changes to the flow settings such that thermal transients may be performed. Particular attention has been focused on obtaining high accuracy data, using a radio telemetry system, as well as thorough through-calibration practices. Temperature measurements can now be made on both rotating and stationary disks with a long term uncertainty in the region of 0.3 K. A gas concentration measurement system has also been developed to obtain direct measurement of re-ingestion and rim seal exchange flows. High resolution displacement sensors have been installed in order to measure hot running geometry. This paper documents the commissioning of a test facility which is unique in terms of rapid configuration changes, nondimensional engine matching, and the instrumentation density and resolution. Example data for each of the measurement systems are presented. This includes the effect of coolant flow rate on the metal temperatures within the upstream cavity of the turbine stator well, the axial displacement of the rotor assembly during a commissioning test, and the effect of coolant flow rate on mixing in the downstream cavity of the stator well.

References

References
1.
Dixon
,
J. A.
,
Brunton
,
I. L.
,
Scanlon
,
T. J.
,
Wojciechowski
,
G.
,
Stefanis
,
V.
, and
Childs
,
P. R. N.
,
2006
, “
Turbine Stator Well Heat Transfer and Cooling Flow Optimisation
,”
ASME Paper No. GT2006-90306
.
2.
Dorfman
,
L. A.
,
1963
,
Hydrodynamic Resistance and the Heat Loss of Rotating Solids
,
Oliver & Boyd
, Eidenburgh.
3.
Chew
,
J. W.
,
1998
, “
The Effect of Hub Radius on the Flow Due to a Rotating Disc
,”
ASME J. Turbomach.
,
110
, pp.
417
418
.10.1115/1.3262213
4.
Da Soghe
,
R.
,
Facchini
,
B.
,
Innocenti
,
L.
, and
Micio
,
M.
,
2009
, “
Analysis of Gas Turbine Rotating Cavities by a One-Dimensional Model
,”
Proceedings of ASME Turbo Expo 2009, ASME Paper No. GT2009-59185
.
5.
Coren
,
D. D.
,
Childs
,
P. R. N.
, and
Long
,
C. A.
,
2009
, “
Windage Sources in Smooth-Walled Rotating Disc Systems
,”
Proc. IMechE
,
223
, pp.
873
888
.10.1243/09544062JMES1260
6.
Owen
,
J. M.
, and
Rogers
,
R. H.
,
1989
,
Flow and Heat Transfer in Rotating-Disc Systems: Volume 1—Rotor-Stator Systems
,
John Wiley
,
New York
.
7.
Daily
,
J. W.
, and
Nece
,
R. E.
,
1960
, “
Chamber Dimension Effects on Induced Flow and Frictional Resistance of Enclosed Rotating Discs
,”
J. Basic Eng.
,
82
, pp.
217
232
.10.1115/1.3662532
8.
Gentilhomme
,
O.
,
Hills
,
N.
, and
Turner
,
A. B.
,
2003
, “
Measurement and Analysis of Ingestion Through a Turbine Rim Seal
,”
ASME J. Turbomach.
,
125
, pp.
505
512
.10.1115/1.1556411
9.
Scanlon
,
T.
,
Wilkes
,
J.
,
Bohn
,
D.
, and
Gentilhomme
,
O.
,
2004
, “
A Simple Method for Estimating Ingestion of Annulus Gas Into a Turbine Rotor Stator Cavity in the Presence of External Pressure Variations
,”
ASME Paper No. GT2004-53097
.
10.
Roy
,
R. P.
,
Zhou
,
D. W.
,
Ganesan
,
S.
,
Wang
,
C. Z.
, and
Paolillo
,
R. E.
,
2007
, “
The Flow Field and Main Gas Ingestion in a Rotor-Stator Cavity
,”
Proceedings of GT2007, Paper No. GT2007-27671
.
11.
Bunker
,
R. S.
,
Laskowski
,
G. M.
,
Bailey
,
J. C.
,
Palafox
,
P.
,
Kapetanovic
,
S.
,
Itzel
,
G. M.
,
Sullivan
,
M. A.
, and
Farrell
,
T. R.
,
2009
, “
An Investigation of Turbine Wheelspace Cooling Flow Interactions with a Transonic Hot Gas Path—Part 1: Experimental Measurements
,”
Proceedings of ASME Turbo Expo 2009, ASME Paper No. GT2009-59237
.
12.
Zhou
,
D. W.
,
Roy
,
R. P.
,
Wang
,
C. Z.
, and
Glahn
,
J. A.
,
2009
, “
Main Gas Ingestion in a Turbine Stage for Three Rim Cavity Configurations
,”
Proceedings of ASME Turbo Expo 2009, ASME Paper No. GT2009-59851
.
13.
Mirzamoghadam
,
A. V.
,
Heitland
,
G.
,
Morris
,
M. C.
,
Smoke
,
J.
,
Malak
,
M.
, and
Howe
,
J.
,
2008
, “
3D CFD Ingestion Evaluation of a High Pressure Turbine Rim Seal Disc Cavity
,”
Proceedings of ASME Turbo Expo 2008, ASME Paper No. GT2008-50531
.
14.
Georgakis
,
C.
,
Whitney
,
C.
,
Woolatt
,
G.
,
Stefanis
,
V.
, and
Childs
,
P.
,
2007
, “
Turbine Stator Well Studies: Effect of Upstream Egress Ingestion
,”
ASME Paper No. GT2007-27406
.
15.
Gartner
,
W.
,
1997
, “
A Prediction Method for the Frictional Torque of a Rotating Disc in a Stationary Housing with Superimposed Radial Outflow
,”
ASME Paper No. 97-GT-204
.
16.
Turner
,
A. B.
,
Davies
,
S. J.
,
Childs
,
P. R. N.
,
Harvey
,
C. G.
, and
Millward
,
J. A.
,
2000
, “
Development of a Novel Gas Turbine Driven Centrifugal Compressor
,”
Proc. Inst. Mech. Eng.
,
214
, pp.
423
437
.10.1243/0957650001537985
17.
S. Wittig
,
U.
,
Schelling
,
S.
, and
Kim
,
and Jacobsen, K.
,
1987
, “
Numerical Predictions and Measurements of Discharge Coefficients in Labyrinth Seals
,”
ASME, International Gas Turbine Conference and Exhibition, 32nd
,
Anaheim, CA
, p.
1987
.
18.
Owen
,
J. M.
, and
Phadke
,
U. K.
,
1980
, “
An Investigation of Ingress for a Simple Shrouded Rotating Disc System with a Radial Outflow of Coolant
,”
ASME Paper No. 82-GT-145
.
19.
Phadke
,
U. P.
, and
Owen
,
J. M.
,
1988
, “
Aerodynamic Aspects of the Sealing of Gas Turbine Rotor-Stator Systems Part 1: The Behavior of Simple Shrouded Rotating-Disc Systems in a Quiescent Environment
,”
Int. J. Heat Fluid Flow
,
9
, pp.
98
105
.10.1016/0142-727X(88)90060-4
You do not currently have access to this content.