POWER PLANT STUDY FOR SHAFT-DRIVEN HEAVY-LIFT ROTARY-WING AIRCRAFT

Abstract

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.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1967
Accession Number
AD0649534

Entities

People

  • Heinz Moellmann
  • William O'connor

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircraft Industry
  • Aircrafts
  • Airframes
  • Alcohols
  • Auxiliary Power Units
  • Classification
  • Control Systems
  • Flight Speeds
  • Fuselages
  • Gas Turbines
  • Geometry
  • Helicopters
  • Methanols
  • Propulsion Systems
  • Rotary Wing Aircraft
  • Test And Evaluation
  • Turbines

Fields of Study

  • Engineering

Readers

  • Aerospace Engineering