Key milestones achieved on next-generation engine
NASA NEWS RELEASE
Posted: November 24, 2003
NASA, the U.S Air Force and two prime aerospace contractors have successfully completed testing of two key rocket engine components - critical milestones in the development of innovative engine systems that could, within decades, power a new generation of American space launch vehicles.
Both tests are part of component-level, risk-reduction studies, intended to lead to development of a hydrogen-fueled, full-flow, staged-combustion rocket engine - the first of its kind. The engine will employ preburners featuring both oxygen-rich and hydrogen-rich staged combustion, which help to cool engines during flight, achieve higher engine efficiency and reduce exhaust emissions.
"Completion of these tests moves us two steps closer to full-scale, integrated testing of the entire IPD system," said Garry Lyles, manager of the Next Generation Launch Technology program, which manages the IPD project for NASA. "America 's future in space hinges on cutting-edge technology development, and together with our Air Force and industry partners, we're focused on creating a more reliable, robust engine system."
"These testing successes wrap up a very exciting year for the IPD project," said Jeffrey Thornburg, IPD project manager for the Department of Defense at the Air Force Research Laboratory. "I can't say enough about how well the NASA, Air Force and industry team has come together to overcome many technical challenges to help us complete this testing."
Integrated system testing is scheduled to begin in late 2004 at NASA's Stennis Space Center near Bay St. Louis, Miss.
The turbopump is designed to provide high-pressure hydrogen to the rocket engine thrust chamber, enabling the combustion process and generating thrust. The turbopump extracts energy from hot gases, which are generated by the fuel preburner and flow through the turbine, causing the turbopump rotor to spin at more than 50,000 rpm. As the rotor spins, an impeller attached to the other end of the shaft pumps the hydrogen to pressures greater than 6,600 psi. These high pressures are necessary to generate the 3,000 psi combustion gases in the thrust chamber, which expand through the chamber and nozzle to produce 250,000 pounds of thrust.
The design and technologies of the fuel turbopump address key life limitations of current reusable rocket engines, and is intended to achieve a lifespan goal of 200 flight missions and 100 flights between periods of engine refurbishment - 10 times the current capability of reusable rocket engines.
"We are very pleased with the results of the turbopump testing," said Don McAlister, IPD program manager at Boeing Rocketdyne. "We've met all our objectives and we've learned valuable lessons for future rocket engine design and testing. With the turbopumps well characterized, we can now move confidently into engine system testing next year."
"With the successful completion of the fuel turbopump component test series, we have substantially lowered the risks associated with pursuing the future integrated engine system test series," said Harry Ryan, IPD project manager at the Stennis Center. "Incremental component testing provides a building-block approach to identify key requirements and reduce risks associated with integrated engine development."
Testing of the oxidizer preburner was conducted by component designer Aerojet Corp. at its Sacramento, Calif., facilities. The test series was completed Oct. 28.
The oxidizer preburner - which initiates the combustion process - is designed to generate oxygen-rich steam for use by the oxygen turbopump's turbine. The preburner burns a large quantity of liquid oxygen with a small quantity of hydrogen to produce this steam, which then mixes with additional hydrogen fuel to be burned in the main combustion chamber.
The preburner is the first flight-capable, oxygen-rich preburner developed in the United States for a large-scale engine. The use of oxygen-rich steam to power the oxygen turbopump is intended to dramatically increase safety of engine system operation, limiting seal failure between the pump and the turbine that could leak extremely hot gases into the turbine and cause them to burn prematurely.
"We are very excited about the operating characteristics demonstrated during the preburner testing," said Robert Werling, project manager for Aerojet. "They provided the thermal environments required to meet the extended turbine life goals, while providing the power necessary to realize the performance goals of the integrated engine system."
The Integrated Powerhead Demonstrator is a cornerstone of NASA's Next Generation Launch Technology program, which seeks to provide safe, dependable, cost-cutting technologies for future space launch systems, increasing engine operability and leading to aircraft-like flight operations. The project also is part of the Department of Defense's Integrated High Payoff Rocket Propulsion Technology program, which seeks to double the performance and capability of today's state-of-the-art rocket propulsion systems while decreasing costs associated with military and commercial access to space.