SPACE SHUTTLE ORBIT MANEUVERING ENGINE REUSABLE THRUST CHAMBER PROGRAM TASK Ⅻ DATA DUMP (PHASE 1)OME INTEGRATED THRUST CHAMBER TEST REPORT

摘要

A total of 40 tests were conducted on the integrated thrust chamber with the like-doublet No. 1 injector and 72:1 area ratio solid nozzle. The total duration accunulated during these tests was 445 seconds.nVacuum specific impulse was 310 seconds at nominal conditions, with a 14.7 inch combustor and 2.7 percent auxiliary film coolant, which is in agreement with data obtained using the same injector in the demonstrator thrust chamber on the previous test progtam at WSTF. Performance was relatively insensitive to either saturation or temperature conditions of the propellants at the thrust chamber inlet. Performance (Is ) increased 1 1/2 seconds when chamber pressure was increased 25 psia, and decreased 2 1/2 seconds when chamber pressure was decreased 25 psia. The total performance variation was 5 seconds over the entire OME operating range of mixture ratio (1.45 to 1.85) and chamber pressure (110 to 140 psia).