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Theoretical performance of an axial-flow compressor in a gas-turbine engine operating with inlet water injection
- Author / Creator
- Available as
- Online
- Summary
-
The performance of an axial-flow compressor operating in a gas-turbine engine with inlet water injection and compressor-outlet saturation was theoretically evaluated. Changes in compressor pressure...
The performance of an axial-flow compressor operating in a gas-turbine engine with inlet water injection and compressor-outlet saturation was theoretically evaluated. Changes in compressor pressure ratio, compressor efficiency, and compressor work due to water injection were determined for altitudes up to 50,000 feet, Mach numbers up to 2.0, and normal compressor pressure ratios of 4, 8, and 16.
Details
- Creator
- by Reece V. Hensley
- Format
- Books
- Language
- English
- Contributors
- Publication
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- Washington, D.C. : National Advisory Committee for Aeronautics, 1952
- Physical Details
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- 1 online resource (25 pages) : illustrations
- OCLC
- on1350395536
- "Lewis Flight Propulsion Laboratory."
- Date of issue: March 1952.
- Title from title screen (viewed November 7, 2022)
- Report no. NACA-TN-2673.
- Includes bibliographical references (page 15)
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.