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Research Papers

An Advanced Multiconfiguration Stator Well Cooling Test Facility

[+] Author and Article Information
N. R. Atkins

e-mail: nra27@cam.ac.uk

S. Davies

Thermo-Fluid Mechanics Research Center,
Department of Engineering and Design,
University of Sussex, Brighton,
BN1 9QT, United Kingdom

P. R. N. Child

Department of Mechanical Engineering,
Imperial College London,
South Kensington,
London, SW7 2AZ, United Kingdom

T. J. Scanlon

Rolls-Royce PLC,
Derby, United Kingdom

1Now at Imperial College London.

2Now at the Whittle Laboratory, University of Cambridge.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received April, 4 2011; final manuscript received July 30, 2011; published online October 18, 2012. Editor: David Wisler.

J. Turbomach 135(1), 011003 (Oct 18, 2012) (12 pages) Paper No: TURBO-11-1056; doi: 10.1115/1.4006317 History: Received April 04, 2011; Revised July 30, 2011

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.

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References

Figures

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Fig. 1

Schematic showing disk entrainment and 2D core flow

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Fig. 2

General stator-well flow field

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Fig. 3

Schematic of the Sussex TSW test facility

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Fig. 4

(a) Test cell arrangement and (b) rapid access rig casing

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Fig. 5

Detail of the TSW facility working section

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Fig. 6

Detail of the drive arm (DA) (a) and (ii) lock plate (LP) (b) coolant configurations

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Fig. 7

Contours showing 10 × the hoop stress normalized by the ultimate tensile strength

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Fig. 8

The turbine stator well test facility internal air system

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Fig. 14

Histogram of the difference in effectiveness for the back to back tests

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Fig. 15

Temperature measurement uniformity

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Fig. 13

The rotating assembly and detail of the thermocouple installation

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Fig. 12

Schematic showing the instrumentation locations

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Fig. 11

TSW facility control and logging panel

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Fig. 10

Schematic of the complete data acquisition system

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Fig. 9

Internal air system network flow model

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Fig. 16

Typical temperature time history (S2)

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Fig. 17

Detail of a temperature transient (S2)

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Fig. 18

Normalized temperature profile on the rear face of R1 for a range of coolant flow rates

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Fig. 19

Normalized temperature profile on the front face of S1 for a range of coolant flow rates

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Fig. 20

Displacement sensor locations

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Fig. 21

Displacement sensor calibration

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Fig. 22

Axial rotor movement during a commissioning test

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Fig. 23

Gas concentration schematic

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Fig. 24

Dilution measurements in the upstream and downstream cavities

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