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Research Papers

Development and Demonstration of a Stability Management System for Gas Turbine Engines

[+] Author and Article Information
D. Christensen, P. Cantin, D. Gutz, P. N. Szucs, A. R. Wadia

 GE Aircraft Engines, Cincinnati, OH 45215

J. Armor, M. Dhingra, Y. Neumeier, J. V. Prasad

 Georgia Institute of Technology, Atlanta, GA 30332

J. Turbomach 130(3), 031011 (May 02, 2008) (9 pages) doi:10.1115/1.2777176 History: Received January 02, 2007; Revised January 19, 2007; Published May 02, 2008

Rig and engine test processes and in-flight operation and safety for modern gas turbine engines can be greatly improved with the development of accurate on-line measurement to gauge the aerodynamic stability level for fans and compressors. This paper describes the development and application of a robust real-time algorithm for gauging fan/compressor aerodynamic stability level using over-the-rotor dynamic pressure sensors. This real-time scheme computes a correlation measure through signal multiplication and integration. The algorithm uses the existing speed signal from the engine control for cycle synchronization. The algorithm is simple and is implemented on a portable computer to facilitate rapid real-time implementation on different experimental platforms as demonstrated both on a full-scale high-speed compressor rig and on an advanced aircraft engine. In the multistage advanced compressor rig test, the compressor was moved toward stall at constant speed by closing a discharge valve. The stability management system was able to detect an impending stall and trigger opening of the valve so as to avoid compressor surge. In the full-scale engine test, the engine was configured with a one-per-revolution distortion screen and transients were run with a significant amount of fuel enrichment to facilitate stall. Test data from a series of continuous rapid transients run in the engine test showed that in all cases, the stability management system was able to detect an impending stall and manipulated the enrichment part of the fuel schedule to provide stall-free transients.

Copyright © 2008 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Illustration of periodicity as observed by over-the-rotor dynamic pressure measurements when the compressor is operating far away from stall

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Figure 2

Illustration of loss of periodicity when the compressor is operating close to stall

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Figure 3

Time variation of the correlation measure at various stall margins obtained with the Georgia Tech compressor along a constant speed line

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Figure 4

Correlation measures obtained on a multistage high-speed compressor at 97% rpm corresponding to stall margins of 21% and 0.5%

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Figure 5

Compressor speed line at 96% corrected speed

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Figure 6

Correlation measure shown in blue, and alarm shown in red (constantly at 0) at an operating condition away from stall

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Figure 7

Distribution of Rotor 2 midchord Kulite signal (dynamic pressure) and correlation measure with time as the compressor is throttled to stall

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Figure 8

Pressure and correlation measure behavior in the stall prevention rig test; the alarm was triggered at DV of 43.6

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Figure 9

Open loop event showing dips in the correlation measure 70ms before the stall event

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Figure 10

Traces of plenum and behind IGV dynamic pressure just before and during a stall event; the straight horizontal lines are due to saturation of the pressure sensors

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Figure 11

Schematic of the stability management system on the engine

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Figure 12

Typical rapid engine transients with enriched fuel flow illustrating the migration of the compressor operating line toward stall

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Figure 13

Autocorrelation from sensors on Stages 3 and 6 and rpm during a blip encountered in open loop bode sequence

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Figure 14

Engine transients showing rpm in green, autocorrelation in blue, and alarm signals from the correlation measure and IGV in red; the alarm threshold in light green is set at 0.2

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Figure 15

Expanded view of second cycle of open loop bodes of Fig. 1.

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Figure 16

Stability management used to cut back the enrichment part of the fuel schedule during acceleration and avoid stall during engine transients

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