Altitude-Wind-Tunnel Investigation of Thrust Augmentation of a Turbojet Engine. 2 - Performance with Water Injection at Compressor Inlet
Abstract
Wind-tunnel tests were conducted on thrust augmentation by injecting water at the inlet of the axial-flow compressor of a turbojet engine with a fixed-area tail-pipe nozzle 16.375 inches in diameter at an inlet-air temperature of 520 deg R. With a tail-pipe temperature of 1680 deg R and at a simulated flight Mach number of 0.265, the net thrust was increased 15% at a pressure altitude of 5000 feet and a water-air ratio of 0.0407 and 12% at a pressure altitude of 20000 feet and a water-air ratio of 0.0535. Specific fuel consumption was 22 and 28% greater, respectively, with water injection.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 19, 1947
- Accession Number
- ADA801402
Entities
People
- Robert O. Dietz
- William A. Fleming
Organizations
- Glenn Research Center