Smart, In Situ, Wide Range Pressure Sensor for Advanced Engine Controls

Usrey, Michael W.; Harsh, Kevin; Brand, Alexander; McKown, R Steve; Behbahani, Alireza

doi:10.4271/2014-01-2167

Cited by 2 publications

(1 citation statement)

References 31 publications

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“…13 Combustion byproducts are corrosive and compressor discharge pressures are predicted to exceed 1300 psi in the near future. 4 Combustion temperatures can reach 1800 o C. 15 In spite of these conditions, in situ sensors must have high reliability, accuracy, and stability. The ability to accurately sense, as well as achieving control stability and making appropriate accommodations to fuel scheduling, is critically important when engine limits are approached.…”

Section: B Turbine Engine Environment and Sensor Requirementsmentioning

confidence: 99%

Demonstration of Smart, High-Temperature Pressure Sensors in an Engine Harsh EnvironmentDemonstration of Smart, High-Temperature Pressure Sensors in an Engine Harsh Environment

Usrey¹,

Knowles²,

Brand³

et al. 2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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Gas turbine engine efficiency, safety, and life cycle cost are directly influenced by the durability and performance of the turbine hot section. Numerous advances have been applied to improve the capabilities of turbines including new structural materials, innovative thermal barrier coatings, and advanced heat transfer techniques; however, improved designs are still dependent on accurate knowledge of true turbine environmental conditions during operation. In conjunction with ongoing advances in physics-based modeling, physical measurement of actual turbine conditions remains a necessity. The Small CAESAR project supports the demonstration and maturation of advanced components, including sensors, under the VAATE program. Sporian Microsystems provided smart pressure/temperature sensor suite probes for testing under Small CAESAR. These probes survived in situ conditions in three engine locations: compressor discharge, high pressure turbine inlet and low pressure turbine inlet, in a test designed to demonstrate TRL 6. Nomenclature% = Percent °C = Degree Celsius °F = Degree Fahrenheit A = Amp BNC = Bayonet Neill-Concelman CAESAR = Component and Engine Structural Assessment Research CAD = Computer Aided Design DC = Direct Current DEC = Distributed Engine Control DECWG = Distributed Engine Controls Working Group DIRCT = Distributed Intelligent Robust Controls Technologies EGT = Exhaust Gas Temperature ERA = Environmentally Responsible Aviation FADEC = Full Authority Digital Engine Control

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Section: B Turbine Engine Environment and Sensor Requirementsmentioning

confidence: 99%