N093-185 TITLE: Robust Pressure Transducer for Propulsion Control Systems

TECHNOLOGY AREAS: Air Platform, Space Platforms

ACQUISITION PROGRAM: PMA-276 Light Attack Helicopter Program

OBJECTIVE: Develop innovative hi-fidelity, environmentally robust, and low cost pressure transducers for aircraft engine control systems.

DESCRIPTION: Pressure transducers are a critical component in the control of aircraft gas turbine engines. However, these devices are subject to extreme environmental conditions and are routinely exposed to combustion contaminants � all of which reduce transducer reliability and accuracy. In particular, contaminated air flowing inside the sensor body creates a buildup of carbon and other deposits on the sensing mechanism reducing accuracy, lowering engine performance, and ultimately resulting in sensor failure.

The goal is to develop innovative technology that provides hi-fidelity, environmentally robust, contaminant resistant, drift resistant, and low cost pressure transducers that can interface with current technology aircraft engine controllers, i.e. Full Authority Digital Engine Controllers (FADECs). The technology should be applicable to all pressure sensors used for gas-turbine engine control, with the main focus being compressor inlet, compressor discharge, and turbine exhaust. Coordination with military engine manufacturer is highly encouraged.

PHASE I: Identify, define, and develop a conceptual design of the proposed technology. Develop detailed analysis of predicted performance and prove feasibility.

PHASE II: Construct and demonstrate the operation of a prototype and conduct cradle-to-grave life cycle and environmental testing. Provide a detailed plan for practical deployment of the proposed technology, such as incorporating the technology to fleet supply lines and the training needed for fleet maintainers, as well as the associated implementation and supportability costs involved. Perform a risk assessment of the proposed technology.

PHASE III: Transition the developed technology for fleet use, and provide a detailed supportability plan.

PRIVATE SECTOR COMMERCIAL POTENTIAL/DUAL-USE APPLICATIONS: Harsh engine operating environments are also prevalent in the commercial air travel industry. The commercial industry would benefit from improvements to engine control systems via more robust pressure transducers.

REFERENCES:
1. "High Temperature Dynamic Pressure." Propulsion Instrumentation Working Group Sensor Specifications. http://www.piwg.org/sensor/sensor_hdpressure.html#table

2. A.D. Kurtz, J.W. Chivers, A.A. Ned, and A.H. Epstein. "Sensor Requirements for Active Gas Turbine Engine Control." RTO A VT Symposium on Active Control Technology for Enhanced Performance Operational Capabilities of Military Aircraft, Land Vehicles and Sea Vehicles, Braunschweig, German-,8-11 May 2000.

KEYWORDS: pressure transducer; engine control system; pressure sensor; FADEC; turbine engine operability; combustion contaminants

** TOPIC AUTHOR (TPOC) **

DoD Notice:   Between July 27 through August 23, 2009, you may talk directly with the Topic Authors to ask technical questions about the topics. Their contact information is listed above. For reasons of competitive fairness, direct communication between proposers and topic authors is not allowed starting August 24, 2009, when DoD begins accepting proposals for this solicitation.

However, proposers may still submit written questions about solicitation topics through the DoD's SBIR/STTR Interactive Topic Information System (SITIS), in which the questioner and respondent remain anonymous and all questions and answers are posted electronically for general viewing until the solicitation closes. All proposers are advised to monitor SITIS (09.3 Q&A) during the solicitation period for questions and answers, and other significant information, relevant to the SBIR 09.3 topic under which they are proposing.

If you have general questions about DoD SBIR program, please contact the DoD SBIR Help Desk at (866) 724-7457 or email weblink.