Abstract
A feasibility analysis was performed on the use of spiral-groove gas bearings in a ring seal between counter rotating shafts in advanced turbofan engines The analysis focused on the lift force characteristics of the spiral grooves for steady state conditions A computer program for predicting the performance of gas lubricated face seals was used to optimize the spiral groove geometry to produce maximum lift force. Load capacity curves (lift force as a function of film thickness) were generated for four advanced turbofan engine operating conditions at relative seal speeds ranging from 17,850 to 29,800 rpm, sealed air pressures from 6 to 42 N/cm (9 60 psi) absolute, and temperatures from 95 to 327 C (203 620 F) The relative seal sliding speed range was 152 255 m/s (500 to 836 ft/s) The analysis showed that the spiral grooves are capable of producing sufficient lift force under steady state conditions such that the ring seal will operate in a noncontacting mode over the operating range of typical advanced turbof an engines
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