Accession Number:

ADA801402

Title:

Altitude-Wind-Tunnel Investigation of Thrust Augmentation of a Turbojet Engine. 2 - Performance with Water Injection at Compressor Inlet

Descriptive Note:

Research memo.

Corporate Author:

FLIGHT PROPULSION RESEARCH LAB CLEVELAND OH

Personal Author(s):

• Dietz, Robert O.
• Fleming, William A.

Report Date:

1947-05-19

Pagination or Media Count:

37.0

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.

Descriptors:

• *TURBOJET ENGINES
• WIND TUNNEL TESTS
• FUEL CONSUMPTION
• MACH NUMBER
• THRUST AUGMENTATION
• INLETS
• WATER INJECTION
• AXIAL FLOW COMPRESSORS
• PRESSURE
• ALTITUDE

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE