March 10, 2008
New Purdue facility aims to improve NASA moon rocket engineWEST LAFAYETTE, Ind. -
More efficient cooling improves performance and reduces the need for costly overhauls, said William Anderson, an associate professor in Purdue's School of Aeronautics and Astronautics.
The new hydrogen facility allows Purdue researchers to study fundamental processes in hydrogen-oxygen engines, such as the J-2X and the engine that will be used by astronauts during their descent to the moon.
In addition to its use as a fuel in these engines, liquid hydrogen serves as a coolant before entering the combustion chamber. The frigid liquid hydrogen, which is about 420 degrees below zero Fahrenheit, circulates through channels in a cooling jacket surrounding the combustor, absorbing heat and raising its temperature before it is injected into the chamber.
The Purdue research focuses on accurately measuring the heat flux, which is caused by differences in temperature between the hot combustion gases and the cooled walls of the combustor. Combusted gases in the rocket's chamber reach 6,000 degrees Fahrenheit, which is more than three times higher than the melting temperature of the combustor's copper wall.
The measurements are used to improve detailed computational models of how propellants mix inside the combustor. The work also aims at better understanding the behavior of coolant inside channels surrounding the combustor.
"Extreme heating takes place in specific locations, and this localized heating tends to limit the combustor life," Anderson said. "Without knowing exactly how the overheating occurs, we tend to overcool the whole combustor. This limits how much propellant energy can be converted into useful thrust."
High-purity hydrogen is provided by the new hydrogen facility, located at Purdue's Maurice J. Zucrow Laboratories.
The hydrogen source is made possible by an intricate feed system designed by Timothee Pourpoint, a senior research scientist in the School of Aeronautics and Astronautics who is in charge of the hydrogen facility, which became operational in 2007. Another major focus of the facility is work funded by General Motors Corp. to develop a hydrogen-storage system for future cars.
Hydrogen gas not used for rocket research is piped 1,000 feet away to the Hydrogen Systems Laboratory for the General Motors hydrogen research.
"Because of the new facility, we are able to conduct research on a scale that is directly comparable to the J-2X," Anderson said. "That's because the facility allows significant hydrogen-flow rates at pressures exceeding 5,000 pounds per square inch."
It is critical to measure the heat flux because engineers need to know how much liquid hydrogen or liquid oxygen to flow through the outside of the engine in order to keep it cool, said Lloyd Droppers, a doctoral student in Purdue's School of Aeronautics and Astronautics.
Purdue researchers measured how much the heat flux varied at different points on the inner wall of the combustion chamber when propellant was being fed into the chamber with a carefully designed set of injectors.
"Until now, these detailed measurements were made using only one injector element, whereas this experiment contains seven elements." Anderson said. "This is important because having seven elements allows you to get precise spatial measurements to tell you how the heat flux changes due to interactions between elements and how it changes relative to the location of the injector elements."
The J-2X rocket is an upgraded version of the J-2 rocket, which was part of the Saturn V vehicles that carried astronauts to the moon in the Apollo missions. The J-2X is part of the Ares rocket that will be used to launch the Orion spacecraft to the International Space Station after the end of the Space Shuttle program in 2010. The rocket also will be needed to carry materials into Earth orbit for retrieval by other spacecraft bound for the moon and Mars.
Measurements taken in the experiments will help engineers more precisely size the cooling jacket for optimal cooling in the J-2X. Better cooling could be achieved by changing the size of the tubing or channels to match areas of highest and lowest heating.
Better computational models would enable engineers to see how a design would perform before building the engine, saving time and money.
"It costs millions of dollars to build these engines, and additional millions of dollars to test them," Anderson said. "So before building a rocket engine, you want to have a good idea of how it's going to perform."
Doctoral student Reuben Schuff is leading work ultimately aimed at improving designs for the cooling channels.
Heat is controlled in such rockets with a method called "regenerative cooling," so called because the fuel serves as a coolant before it is injected into the combustion chamber.
The research is being funded through NASA's Constellation University Institute Program, which supports rocket research at universities around the nation. Missions using the J-2X rocket are planned for the next decade.
The new hydrogen facility is funded primarily by General Motors and NASA, with additional support from the Indiana 21st Century Research and Technology Fund and Purdue's Energy Center in Discovery Park.
Research findings were detailed in two research papers presented last summer during the American Institute of Aeronautics and Astronautics' joint propulsion conference in Cincinnati.
Writer: Emil Venere, (765) 494-4709, email@example.com
Sources: William Anderson, (765) 496-2658, firstname.lastname@example.org
Timothee Pourpoint, (765) (494) 1541, email@example.com
Purdue News Service: (765) 494-2096; firstname.lastname@example.org
Note to Journalists: Electronic copies of the research papers are available from Emil Venere, Purdue News Service, at (765) 494-4709, email@example.com
A publication-quality photo is available at http://news.uns.purdue.edu/images/+2008/pourpoint-hydrogen.jpg
Experimental Investigation of Asymmetric Heating
Reuben Z. Schuff1, Hogirl Jung2, and Charles L. Merkle3, and William E. Anderson4
A single channel model of the application of High Aspect Ratio Cooling Channels (HARCC) to a typical expander cycle engine was designed and tested. Aspect ratios of 4 and 8 were tested at Reynolds numbers between 800,000 and 2,000,000. The test section is asymmetrically heated with a heat flux of approximately 1 Btu/(in2-s) applied to a superscale model of the channel. All the walls except for the heated wall are designed to be adiabatic. Supercritical nitrogen is used to simulate hydrogen at a reduced temperature and pressure comparable with rocket cooling operation. The test article is 32.5 inches long, with 20 inches of heated section, 0.30 inches in width, with an open flow width of 0.10 inches. One side wall of the test section is instrumented with 105 thermocouples to capture the temperature contour of the fin. Local Nusselt numbers are reported for the fin and web portions of the test section, and a comparison is made with traditional Nusselt number correlations. The results provide detailed data for CFD validation purposes and empirical model comparisons. There is a large dissimilarity between the calculated Nusselt numbers along the web as compared to the fin of the test section. This follows from the classical assumptions of uniform bulk temperature and highlights the limits of traditional Nu approximations when applied to non-tubular asymmetric heating.
Study of Heat Transfer in a Gaseous Hydrogen Liquid Oxygen Multi-Element Combustor
Lloyd J. Droppers1 and Reuben Schuff2,
A model combustor using gaseous hydrogen and liquid oxygen was designed, built, and tested at realistic rocket conditions to obtain validation measurements of the three-dimensional effects due to interelement interactions near the chamber wall and injector face. The experiment largely parallels single element research conducted previously at The Pennsylvania State University and expands that work to include the multiple injector element effects. To complete the work the best practices for measuring near-wall spatially resolved thermal environments were investigated and a new hydrogen test capability was brought on line. A seven-element heat sink test chamber with a water-cooled throat was built for tests ranging from 3 to 6 in mixture ratio, and chamber pressures from 300 to 1200 psia. Instrumentation included three heat flux measurements at the face, and 14 heat flux measurements in the chamber wall. Two different types of coaxial thermocouple arrangements were studied. Although the propellant supply system was carefully designed to provide even propellant distributions, an apparent assembly anomaly resulted in injector elements with uneven oxidizer-to-fuel ratios. Measured heat flux was calculated based on coaxial thermocouple data, and subsequently non-dimensionalized by a reference value derived from the Bartz equation. Values of heat flux are compared to the single element data.
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