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Title: Transducer Installation Effects on Pressure Measurements in PGC Devices

Conference · · 2018 AIAA Aerospace Sciences Meeting
DOI:https://doi.org/10.2514/6.2018-0158· OSTI ID:1774979

Pressure gain devices such as rotating detonation engines present an extremely harsh environment, generally precluding the use of any intrusive probe measurement. The most widely used diagnostic is the measurement of high frequency pressure which can be used to determine the pressure amplitude, number of waves and their direction and the wave structure. The preferred approach for making pressure measurements is to install the sensing element flush with the combustion chamber wall, but is almost always inhibited by the extremely high heat fluxes that can damage the sensor. Alternately, recessed cavity or infinite probe installation is seldom used for high frequency pressure measurements. While amplitude attenuation and phase distortion of the pressure signal can be introduced by these installation types, its characterization in the presence of high amplitude steep fronted pressure waves encountered in PGC devices has not been previously performed. In the current work a highly modular calibration test-bed is designed to enable characterization of pressure transducers based on their installation in the presence of steep fronted high amplitude pressure waves. Two transducer types, piezoelectric PCB® 113B26 and water-cooled piezoresistive Kulite®WCT-312M were used and installed in the flush, recessed cavity and infinite tube probe configuration. The recessed cavity probe showed 5-26% amplitude attenuation and almost negligible time lag compared to the flush transducer, the infinite tube pressure (ITP) transducer showed a significantly higher delay and as much as 50% reduction in measured pressure amplitude. Secondary wave features from reflections within the test article, that were captured by the flush and recessed cavity transducer were damped by the infinite probe measurement.

Research Organization:
Purdue Univ., West Lafayette, IN (United States)
Sponsoring Organization:
USDOE Office of Fossil Energy (FE), Oil & Natural Gas
DOE Contract Number:
FE0025343
OSTI ID:
1774979
Journal Information:
2018 AIAA Aerospace Sciences Meeting, Conference: 2018 AIAA Aerospace Sciences Meeting, Kissimmee, 8–12 January 2018
Country of Publication:
United States
Language:
English

References (7)

Self-Excited, Multi-kHz Dynamics in a Linear, Semi-Bounded Detonation Channel conference January 2017
Pressure measurement by fast-response piezo-electric sensors during continuous spin detonation in the combustor journal January 2017
Experimental Study of Rotating Detonation Combustor Performance under Preheat and Back Pressure Operation conference January 2017
Rotating Detonation Engine Interaction with an Annular Ejector conference January 2014
Experimental Study of the Performance of a Rotating Detonation Engine with Nozzle journal May 2016
Effects of Installation on Dynamic Pressure Measurements conference June 2012
A Parametric Study of Combustion Dynamics in a Single-Element Lean Direct Injection Gas Turbine Combustor: Part II: Experimental Investigation conference January 2014

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