TECHNOLOGY AREAS: Air Platform, Materials/Processes

ACQUISITION PROGRAM: Joint Strike Fighter

OBJECTIVE: Develop and demonstrate high-speed continuous blade health monitoring technology for turbine engines that deterministically calculates blade vibration modes from continuous time-series data, rather than the currently employed undersampled approach.

DESCRIPTION: Current non-contacting stress measurement systems (NSMS) utilize sensors optimized for determining the exact time of arrival of each blade, and process the collected data in an undersampled manner to infer blade vibration modes. Assumptions are made and pre-defined specific circumferential transducer positions are required based on vibration modes of interest. As a result the capability and flexibility of using current systems on turbine engines is severely limited. Innovative turbine engine blade vibration sensors and associated algorithms are sought, with the ability to sense blade vibration in a continuous manner suitable for collecting time series data that will support Fourier Analysis techniques to deterministically calculate blade vibration modes. The spacing and number of the sensors will need to be optimized for determining various blade modes. The desire is to overcome these constraints and limitations via sensors that will sense blade location in a continuous manner over a given arc, and the associated algorithms to process this data and extract blade vibration modes in a deterministic, non-aliased manner.

PHASE I: Demonstrate feasibility of proposed sensors to make continuous measurements of blade position for each blade through a predefined arc of travel. Develop and demonstrate proof of concept sensors and associated algorithms that are capable of making the required measurements

PHASE II: Develop a prototype continuous blade health monitoring system. Refine the sensor design to ensure robust, reliable operation in the required operational environments. Design a robust means of attaching the through-the-case sensor, with provision for sensor removal as required. Design a flexible sensor installation and removal procedure. Refine the algorithms to robustly and deterministically calculate blade vibration modes.

PHASE III: Finalize sensor integration with major DoD end users, airframe, and engine manufacturers; and conduct necessary qualification testing.

PRIVATE SECTOR COMMERCIAL POTENTIAL/DUAL-USE APPLICATIONS: This advanced sensing capability would significantly enhance the state of the art for commercial aviation engine tests and inspections requiring NSMS instrumentation. The technology is directly transferable to commercial gas turbine engine applications.

REFERENCES:
1. Michael Zielinski, Gerhard Ziller; "Noncontact Blade Vibration Measurement System for Aero Engine Application"; International Symposium of Air Breathing Engines, ISABE-2005-1220
http://www.mtu.de/channel/files/pdf/noncontact_blade_vibration.pdf

2. NSMS Data Acquisition Using an Alternative Multi-Point Approach; http://www.hcf.utcdayton.com/HCF05_pdfs/11_0430_Hill_paper.pdf

KEYWORDS: Turbine Engine; Blade Vibration; NSMS; Vibration Modes; Sensors; Propulsion

TPOC: (301)757-0508
2nd TPOC: (301)757-0462

** TOPIC AUTHOR (TPOC) **

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