Technical Briefs

Telemetry System Integrated in a Small Gas Turbine Engine

[+] Author and Article Information
Stephen A Long

 Rolls-Royce Indianapolis, IN 46206-0420stephen.a.long@rolls-royce.com

Stephen L Edney

 Rolls-Royce Indianapolis, IN 46206-0420steve.edney@rolls-royce.com

Patrick A Reiger

 Rolls-Royce Indianapolis, IN 46206-0420patrick.a.reiger@rolls-royce.com

Michael W Elliott

 Rolls-Royce Indianapolis, IN 46206-0420michael.w.elliott@rolls-royce.com

Frank Knabe

 Rolls-Royce Dahlewitz, Germanyfrank.knabe@rolls-royce.com

Dieter Bernhard

 Rolls-Royce Dahlewitz, Germanydieter.bernhard@rolls-royce.com

J. Eng. Gas Turbines Power 134(4), 044501 (Jan 18, 2012) (5 pages) doi:10.1115/1.4004260 History: Received April 26, 2011; Revised May 16, 2011; Published January 18, 2012; Online January 18, 2012

For the purpose of assessing combustion effects in a small gas turbine engine, there was a requirement to evaluate the rotating temperature and dynamic characteristics of the power turbine rotor module. This assessment required measurements be taken within the engine, during operation up to maximum power, using rotor mounted thermocouples and strain gauges. The acquisition of this data necessitated the use of a telemetry system that could be integrated into the existing engine architecture without affecting performance. As a result of space constraints, housing of the telemetry module was limited to placement in a hot section. To tolerate the high temperature environment, a cooling system was developed as part of the integration effort to maintain telemetry module temperatures within the limit allowed by the electronics. Finite element thermal analysis was used to guide the design of the cooling system. This was to ensure that sufficient airflow was introduced and appropriately distributed to cool the telemetry cavity, and hence electronics, without affecting the performance of the engine. Presented herein is a discussion of the telemetry system, instrumentation design philosophy, cooling system design and verification, and sample of the results acquired through successful execution of the full engine test program.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Schematic of the telemetry unit embedded in the turbine (dots on blisks identify thermocouples)

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Figure 2

Modification of the exhaust collector; (a) original configuration; (b) with casting hub cut out; (c) new hub; (d) new configuration with modified hub and cooling air manifold with tubes; (e) final exhaust assembly

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Figure 3

Cooling can developed to limit exposure temperature of the telemetry system

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Figure 4

Power turbine shafting assembled with turbine blisks and coupling nut

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Figure 5

“Dummy” telemetry modules to verify temperature exposure; (a) preassembly of telemetry rotor; (b) insertion of dummy module; (c) assembled dummy telemetry rotor

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Figure 6

Measured versus STRATA based predicted telemetry module cavity temperatures at full engine power

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Figure 7

Sample of test results during acceleration to full power; (a) blisk rotating metal temperature data; (b) turbine blisk rotating strain gauge data measured via telemetry system; dashed ovals contain airfoil responses, solid ovals contain hub dominant responses



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