Air Force Reusable Rocket Engine Program XLR129-P-1. Volume 1
Annual rept. no. 1, 6 Nov 1967-6 Nov 1968
PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FL FLORIDA RESEARCH AND DEVELOPMENT CENTER
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The objective of this program is to demonstrate the performance and mechanical integrity of a 250,000-lb thrust reusable oxygenhydrogen rocket engine designated the XLR129-P-1. The program consists of design, analysis, fabrication, and test of all the engine components and the complete demonstrator engine. The first year, experimental evaluation was conducted in the areas of a fixed fuel area preburner injector, hydrogen cooled roller bearings, compact pump inlets, lightweight nozzle fabrication techniques, and selected control valves. A new full-scale preburner injector was designed, fabricated, and tested that produced a uniform temperature profile suitable for use in the engine. Four bearing configurations surpassed the test duration goal at the design operating conditions. An elbow type of inlet with turning vanes was selected for both the fuel and oxidizer turbopumps. The nozzle fabrication investigation concluded that the internal corrugated type of construction was best for the two-position nozzle. Both a hoop shutoff seal and a cam-actuated shutoff seal have proven to be potentially feasible types of seals for use in the main chamber oxidizer valve, which is a butterfly valve. Pressure balance configurations of piston rings used in the preburner oxidizer valve have demonstrated acceptable wear leakage and actuator force characteristics. Designs have been initiated for the preburner injector, main burner injector, main burner chamber, nozzles, transition case, fuel turbopump, oxidizer turbopump, fuel low-speed inducer, oxidizer low-speed inducer, and the control components.
- Liquid Propellant Rocket Engines