Sensor and Actuator Needs for More Intelligent Gas Turbine Engines

Garg, Sanjay; Schadow, K. C.; Horn, Wolfgang; Pfoertner, Hugo; Stiharu, Ion

doi:10.1115/gt2010-22685

Cited by 29 publications

(12 citation statements)

References 19 publications

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“…The fan speed is usually used as a push indicator, while the EGT is the parameter that allows the gas turbine engine health to be monitored. In some engine models, engine pressure ratio (EPR) and N2/N3 speed are used to monitor thrust [5]. The importance of EGT parameter is given below.…”

Section: Main Operation Parameters Of the Enginementioning

confidence: 99%

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Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data

Yildirim

Bulent

2018

International Journal of Aerospace Engineering

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Modern condition monitoring-based methods are used to reduce maintenance costs, increase aircraft safety, and reduce fuel consumption. In the literature, parameters such as engine fan speeds, vibration, oil pressure, oil temperature, exhaust gas temperature (EGT), and fuel flow are used to determine performance deterioration in gas turbine engines. In this study, a new model was developed to get information about the gas turbine engine's condition. For this model, multiple regression analysis was carried out to determine the effect of the flight parameters on the EGT parameter and the artificial neural network (ANN) method was used in the identification of EGT parameter. At the end of the study, a network that predicts the EGT parameter with the smallest margin of error has been developed.

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Section: Main Operation Parameters Of the Enginementioning

confidence: 99%

“…Today's aircraft engines are made safer by increasing the number of control parameters and sensors [5]. The engines have a complex mechanical system.…”

Section: Introductionmentioning

confidence: 99%

Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data

Yildirim

Bulent

2018

International Journal of Aerospace Engineering

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“…The installed MCM must survive temperatures ranging from -60°C at the inlet to 1700°C in the combustor. 25 This effort has focused on providing packaging solutions up to 600°C since that is the limit of HT electronics currently available. It may also need to survive centrifugal acceleration loads in excess of 50,000 g if installed on a rotating part of the engine and vibration in excess of 100 g and beyond 20 kHz if installed on the engine core or case.…”

Section: High-temperature Electronics Packagingmentioning

confidence: 99%

“…It may also need to survive centrifugal acceleration loads in excess of 50,000 g if installed on a rotating part of the engine and vibration in excess of 100 g and beyond 20 kHz if installed on the engine core or case. 25 Each step in this packaging process has been systematically developed by the authors to yield a packaging methodology that meets or exceeds the environmental constraints of current HT electronics components. Results from this effort are summarized in Table 3.…”

Section: High-temperature Electronics Packagingmentioning

confidence: 99%

High-Temperature Sensor and Electronics Packaging Technologies for Distributed Engine Controls

Behbahani¹,

Usrey²,

Liu³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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In-situ deployment of sensors and actuators enables both adaptive engine control and distributed engine control concepts. Currently, there exists a small but increasing pool of commercial electronics components to facilitate these advanced control concepts. As hightemperature operable electronics become more broadly available, electronics packaging must be designed to endure high temperatures, large acceleration loads, and support nonplanar installation. A multi-chip module packaging process is being systematically developed by the authors to yield a packaging methodology that meets or exceeds the environmental constraints of current high-temperature (HT) electronics components. NomenclatureDEC = distributed engine control dB = decibel dBi = decibel isotropic EM = electromagnetic g = acceleration due to gravity (9.81 m/s 2 ) HT = high-temperature Hz = hertz IC = Integrated Circuit JFET = junction gate field-effect transistor kHz = kilohertz MCM = multi-chip module MOSFET = metal-oxide-semiconductor field-effect transistor OEM = original equipment manufacturer psi = per square inch RF = radio frequency RFID = radio frequency identification RPM = revolutions per minute SAW = surface acoustic wave SOI = silicon on insulator SiC = silicon carbide TBC = thermal barrier coating °C = degrees centigrade 1 Vice President, , 515 Courtney Way -Suite B, Regular Member.

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“…Control of the gap between turbine blade tips and casing seals can have damaging effects on the turbine performance if it is not sufficiently managed to reduce leakage flow [1,2]. The most commonly employed leakage management techniques have been: active thermal, active mechanical, passive thermal, active pneumatic, passive pneumatic, and regeneration [3].…”

Section: Introductionmentioning

confidence: 99%

Innovative Measurement Techniques for a Cooled Turbine Casing Operating at Engine Representative Thermal Conditions

Dann

Thorpe

Lewis

et al. 2014

Volume 5B: Heat Transfer

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To optimize the efficiency of modern aero-gas turbine engines the turbine tip clearances must be tightly controlled so as to minimize leakage losses. In addition, the clearance control system must be able to respond with sufficient rapidity to engine thermal transients. One method of achieving turbine tipclearance control is to manipulate the turbine casing temperature, and thereby radial growth, by convective cooling. The consequent clearance control system represents a particularly complex thermo-mechanical design problem. The current experimental study aims to simulate the heat loads to which the internal surfaces of the casing are typically exposed and to characterize the radial and axial displacement of the free-body casing under varying external cooling conditions. Importantly, the newly commissioned test facility allows a realistic assessment of the casing cooling impact on dimensional control, and also the rapid characterization and comparison of different concepts. The test facility comprises a model of a high-pressure/intermediate-pressure * Address all correspondence to this author. turbine casing with generic impingement cooling manifolds. A radiant heater is mounted within the casing model such that a near-uniform heat flux condition can be established on the casing wall inner surface. Extensive surface mounted thermocouples are welded to the casing wall to monitor variations in metal temperature. Radial and axial displacement of the casing is monitored using laser triangulation and linear variable differential transformer sensors. Experiments have been conducted over a range of heat load conditions and with engine representative levels of casing cooling applied. Importantly, the new test facility allows for the characterization of the casing cooling system as a whole. NOMENCLATURED displacement. E axial expansion. l casing axial length. r HP casing radius. Downloaded From: http://proceedings.asmedigitalcollection.asme.org/ on 05/29/2015 Terms of Use: http://asme.org/terms RDG reading. FSO full scale output.

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Sensor and Actuator Needs for More Intelligent Gas Turbine Engines

Cited by 29 publications

References 19 publications

Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data

Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data

High-Temperature Sensor and Electronics Packaging Technologies for Distributed Engine Controls

Innovative Measurement Techniques for a Cooled Turbine Casing Operating at Engine Representative Thermal Conditions

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