Power Plant Study for Shaft-Driven Heavy-Lift Rotary-Wing Aircraft

摘要

Studies were conducted on various multiengine gas turbine propulsion systems for a shaft-driven, heavy-lift helicopter. The helicopter was based on a design gross weight of 75,000 to 85,000 pounds, having a 40,000-pound payload. Growth versions of existing gas turbine engines were applied to the study. The following types of engine systems were investigated: free-power turbine, mechanical coupling, regenerative, front drive, fixed-power turbine, gas coupling, nonregenerative, and rear drive. The engine packaging arrangements were vertical and horizontal installations in single-, tandem-, and quad-rotor helicopters. The prime study criteria were weight savings (fuel plus installed engine) and helicopter performance. Additional subjects of study were: power augmentation by water-methanol injection or increased turbine-inlet temperature; electrical, hydraulic, and pneumatic starting systems; and control problems concerning load sharing, engine-out operation, and stability. (Author)