KOSEN 한인과학기술자네트워크

High Temperature, High Bandwidth, Pressure Transducer Primary Sponsor: Department of Defense Deadline: 4/11/2001 KEYWORDS TECHNOLOGY AREAS: Materials / Processes OBJECTIVE: Develop and demonstrate a high frequency response pressure transducer capable of operating at 1100 C or higher. DESCRIPTION: Jet engine turbines operate in a high temperature environment with high frequency pressure and temperature variations caused by combustion instabilities, blade-row interactions, and unsteady aerodynamic phenomena. In addition, the turbine operates in a harsh environment with products of combustion present. In order to more completely understand the effects of pressure fluctuations on the operation and lifetime wear of a turbine, a device capable of making unsteady pressure measurements at up to 125 kHz, at temperatures of 2000 F (1100 C) or higher (up to 1400 C would be desirable) and pressures up to 750 psi (5170 kPa) absolute, with combined uncertainties of less than 1% of full scale is desired. It is envisioned that such a device could be based on a high temperature fiber optic lead coupled to either an optical etalon or a MEMS-based sensor. This will require research and development efforts involving the use of high temperature fiber optics or MEMS substrates, fabrication techniques, coating materials, and device design, calibration and stability characterization, etc. The resulting device would be a surface mounted pressure transducer for use on turbine vanes or casing walls and would provide a point measurement of the unsteady pressure fluctuation in the turbine at the surface of a vane or casing wall. These measurements would be useful both in test rig applications, and in lifetime wear characterization for operating engines. Ideally, this device would be insensitive to temperature variations, or would include a co-located temperature sensor of comparable operating range and frequency response in order to provide temperature corrections. All aspects of the device design and operation should be considered, including calibration, readout fibers or leadwires, corrosion resistance, electronics, and device mounting requirements. The total device must be compact and capable of surviving long duration operation in a turbine engine environment. The device should be minimally intrusive and capable of being flush-mounted on a stator or casing wall with minimal modification to the existing engine components. Ideally the system would be rugged enough to be capable of applications in flight. Device bandwidth, operational temperature, sensitivity, compactness, mounting requirements, calibration requirements, and ruggedness of the design will all be considered in evaluating candidate sensor concepts, and should be addressed in the proposed effort. PHASE I: Conceptually design the pressure sensors and develop preliminary estimates of frequency response, accuracy and upper limits of temperature operating range. Test preliminary designs and demonstrate the survivability of the sensor components and/or materials by testing samples in lab-level demonstrations at elevated temperatures and pressures. PHASE II: Build and test a working prototype of sensor proposed in Phase I. Characterize the frequency response, accuracy and resolution of the sensor. Test the prototype in a suitable test rig to demonstrate operation at elevated temperatures and pressures. PHASE III DUAL USE APPLICATIONS: An improved pressure sensor capable of operation in a harsh, high temperature environment would be a useful device in the development of both internal combustion and gas turbine engines. Such a device would provide new experimental validation capabilities in laboratory setups and may also provide for lifetime monitoring of critical engine components in both military and civilian applications. REFERENCES: 1. Propulsion Instrumentation Working Group, Dynamic Pressure Measurements Subteam requirements, www.oai.org/PIWG/tabl/table2.html 2. Rahnavardy, K., Arya, V., Wang, A., and Weiss, J.M., "Investigation and application of the frustrated-total-internal-reflection phenomenon in sapphire optical fibers," Applied Optics, Vol. 36, No. 10, pp. 2183-2187 (1997). 3. Chalker, P.R., and Johnston, C., "Thin Film Diamond Sensor Technology," Published in Diamond Thin Films, edited by John I.B. Wilson, Wilhelm Kulisch, Academie Verlag, 1996. KEYWORDS: High Temperature, High Bandwidth, Sensor, Turbine, Temperature, Pressure, Fiberoptics DoD Notice: Between January 2 and February 28, 2001, you may talk directly with the DoD scientists and engineers who authored the solicitation topics, to ask technical questions about the topics. The Topic Author is listed in the box below. For reasons of competitive fairness, direct communication between proposers and topic authors is not allowed after February 28, 2001, when DoD begins accepting proposals under this solicitation. TPOC: Thomas Beutner, PHONE: 703-696-6961 EMAIL: Thomas.beutner@afosr.af.mil After February 28, 2001 proposers may still submit written questions about solicitation topics through the SBIR/STTR Interactive Topic Information System (SITIS). If you have general questions about DoD SBIR program, please contact the DoD SBIR Help Desk at (800) 382-4634 or email to SBIRHELP@teltech.com. NOTE: The Solicitations listed on this site are copies from the various SBIR agency solicitations and are not necessarily the latest and most up-to-date. For this reason, you should use the agency link listed below which will take you directly to the appropriate agency server where you can read the official version of this solicitation and download the appropriate forms and rules. The official link for this solicitation is: http://www.acq.osd.mil/sadbu/sbir/sttr01/dod_sttr01.htm. DoD will begin accepting proposals on March 1, 2001. The solicitation closing date is April 11, 2001.