A study was conducted to assess the feasibility of an advanced technology High Pressure Intercooled Turbine (HIPIT) engine for prime propulsion applications. A cycle performance analysis was conducted for a hypothetical HIPIT gas turbine sized to deliver 1000 hp output with and without a reheat combustor. Selection of candidate designs with an overall compressor pressure ratio of 41.7 were predicted to have respective specific fuel consumptions of 0.358, and 0.434 lb/hp.hr with corresponding weights of 503 lb., and 374 lb.
Three conceptual HIPIT engine preliminary mechanical design configurations were studied, and part load performance characteristics of the HIPIT are also presented.
As a result of the high pressure ratio, reheating was predicted to provide a power boost of 35%, ideal for emergency power demands.