The Low Cost Gas Generator (LCGG) program addresses the task of designing and demonstrating gas generator components with low cost as the primary objective. The components are sized to provide a turbojet engine configuration in the 9000-N thrust class (SLS, 288 K) and are applicable to a turbofan engine. By demonstrating these components in the actual engine environment, as a turbojet, a solid base will be established for transitioning this technology into engineering development as specific firm mission requirements become available. The program is sponsored by the U.S. Air Force Aero Propulsion Laboratory and consists of three phases covering a 39-month period as follows:
Phase I – Preliminary Design (7 months)
Phase II – Component Detail Design, Fabrication & Testing
Phase III – Gas Generator Design, Fabrication & Testing (1 2 months).
The Phase I portion of the program was completed in December 1976 and the results are discussed in this paper. The Phase I, preliminary design, consisted of performing cycle analysis, aero-thermo analyses, mechanical design, and manufacturing analyses to determine the best turbine engine configuration which satisfied the program objectives. The results of Phase I indicate that a turbojet in the 9000-N thrust class can be produced for approximately 2.4 $/N SLS thrust (1976 dollars) by making maximum use of casting technology and mechanical design simplicity. The SFC is 10 to 20 percent higher than existing engines in the same thrust class; however, the thrust to weight is comparable or better than engines used for RPV, missile, or drone applications.