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Boeing Tests Future Rocket Engine Component to Record Levels

The RS-84 was the Boeing Rocketdyne Lox/Kerosene design for NASA's Space Launch Initiative. The design borrowed extensively from Russian technology developed in the forty years since the USA began its last such design, the F-1. The engine featured a high-pressure chamber and staged combustion cycle in comparison with the F-1's lower pressure chamber and gas generator. Another requirement was to produce the first US reusable Lox/Kerosene engine. This made it necessary to limit the kerosene temperature while cooling the thrust chamber, and limit soot build-up in the turbine. To accomplish this the RS-84 included an arrangement of small section manifolds along the combustion chamber and engine nozzle. These manifolds were spaced so the kerosene is not heated above the coking limit. Some manifolds also injected a small amount of kerosene directly into the thrust chamber to create film wall cooling. The oxygen-rich staged combustion used a cleaner, heated oxygen gas to drive the turbine to avoid problems inherent in kerosene-rich gas products. Caption by Encyclopedia Astronautica
St. Louis - Dec 11, 2003
Boeing has successfully tested a key component of its RS-84 prototype rocket engine, reaching pressures never before attained in an American-built engine of this type. The RS-84 is a reusable, liquid booster engine being developed by the Rocketdyne Propulsion & Power Division of Boeing in Canoga Park, Calif., for NASA's Next Generation Launch Technology Program.

The engine program is one of two competing efforts now under way to develop an alternative to conventional, hydrogen-fueled engine technologies and is a reusable, staged combustion type, fueled by kerosene a relatively low-maintenance fuel with high performance and high density, meaning it takes less fuel-tank volume to permit greater propulsive force than other technologies.

In the recent successful test, a subscale preburner, which produces high-pressure, oxidizer-rich combustion gases to spin the engine's oxidizer and fuel turbopumps, achieved a chamber pressure in excess of 6800 pounds per square inch, well beyond the levels seen in current domestic oxygen/kerosene rocket engines.

"The tests demonstrate the capability of the preburner to perform at chamber pressure levels that are representative of the full-scale engine," said John Vilja, Rocketdyne RS-84 program director, for Boeing.

The subscale preburner is roughly one-fifth the size of the one that will be used on the full-scale, one-million-pound-thrust RS-84, a prototype oxidizer-rich staged combustion cycle engine that could be tested in the summer of 2007. The new preburner is in the midst of a hot-fire test series that will conclude in January after approximately 10-12 more tests at the Stennis Space Center, Miss.

"The purpose of the test series is to demonstrate the performance, durability and combustion product uniformity of the component," Vilja said. "When the current series is complete, we'll change out the injector that's now in the preburner with an alternate design and run a second test series.

If selected by NASA for further development, the RS-84 will be the first American oxidizer-rich engine ever built. The ability to put key components through their paces at this point of the development process confirms the viability of the physics-based model design.

"No engine yet conceived meets the kinds of high reliability, cost efficiencies, and responsiveness that are part of the RS-84 design," said Danny Davis, NASA project manager for the RS-84 project at the Marshall Space Flight Center in Huntsville, Ala. "Our design incorporates the latest in materials development, advanced software to monitor and predict problems, and lessons learned from past engine technology efforts."

The benefits of the RS-84 engine translate to more compact engine systems, easier fuel handling and loading on the ground, and shorter turnaround time between launches. All these gains, in turn, reduce the overall cost of launch operations, making routine space flight cheaper and more attractive to commercial enterprises.

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India Conducts Endurance Test Of New Cryogenic Engine
Bangalore - Dec 08, 2003
An endurance test for duration of more than 16 minutes on the indigenous Cryogenic Engine for Geo-synchronous Satellite Launch Vehicle, GSLV, was successfully conducted today (December 5, 2003) at ISRO's Liquid Propulsion Systems Centre (LPSC) at Mahendragiri in Tamil Nadu.

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