1. NON-PROPRIETARY DATA NASA SBIR/STTR Technologies Novel Design of Orifice Type Control Element for Mitigating Instabilities Identification and Significance of Innovation Technical Objectives: The objective in the Phase II effort is to demonstrate through a combination of analysis and testing that the instability mitigation device works effectively in full-scale systems such as ones used at NASA SSC rocket engine test facilities. Secondary objectives include correlating the resistance of the device with different operating conditions including different fluids and refining the design and fabrication process. NASA and Non-NASA Applications Orifice elements are ubiquitous in component test cells and test stands for liquid rocket engines. They are used in propellant lines, propellant conditioning systems, feed systems, water cooling systems in flame buckets and suppression systems to quench the flame. Instabilities that arise due to their operation compromise the safety of the test stands, increase loads on the test article, lead to premature shutdown of tests and cause costly delays. Such events have been observed at NASA SSC during J2-X testing, RS-25 testing, IPD LOX turbopump testing. The instability mitigation device developed in this program can suppress instabilities, substantially reduce risk and the likelihood of such events. The device can replace orifice elements in experimental/testing loops at NASA SSC/JSC/MSFC/KSC/GRC and Plumbrook. The commercial market for our product is very large and includes plant installations and industrial facilities that use extensive piping systems such as nuclear power generation, chemical process plants etc. The technology proposed here can play a critical and imminent role in addressing an important safety concern in pressurized water reactors where orifices are used in the emergency core cooling systems (ECCS) in conjunction with throttle valves. Firm Contacts Estimated TRL (1 – 9) at beginning and end of contract Start TRL 4 / End TRL 6 Combustion Research and Flow Technology, Inc. Pipersville, PA Proposal No.: T10.01-9977 An orifice element is commonly used in liquid rocket engine test facilities to provide a large reduction in pressure over a very small distance in the piping system. Orifice elements are used in propellant lines, feed systems, plume suppression systems and steam ejector trains. While the orifice as a device is largely effective in stepping down pressure, it is also susceptible to a wake-vortex type instability and cavitation instability that propagate downstream and interact with other elements of the test facility resulting in structural vibration. In this proposal a new proprietary instability mitigation device has been developed that steps down the pressure, straightens the flow and suppresses all instability modes. The device is scalable and can be used for different mass flow rates and varying levels of de-pressurization conditions. In Phase I, the device has been successfully demonstrated in a sub-scale cryogenic test facility. In Phase II the performance of the device will be calibrated for full-scale operation in a cryogenic test facility and a water test facility. Vineet Ahuja, Senior Research Scientist Phone: 215-766-1520; Fax: 215-766-1524; Email: vineet@craft-tech.com Work Plan FFT of Full-Scale tests of Traditional Orifice and New Device showing mitigation of instability through system. Vortex Shedding and Cavitation create instabilities when facility pressure is stepped down with an orifice element. Full Scale Analysis of Single Hole Orifice in Liquid Nitrogen Analysis of Instability Mitigation Device in Liquid Nitrogen Characterization of Resistance of Device Design with Flow Conditions Design and Fabrication of Device Sub-scale cryogenic Testing and Characterization of Device Full Scale cryogenic Testing of Device Analysis and Testing of Device in Water Red – Orifice Black - Device