- Author
-
Marchionna, N. R.
- Title
- Performance of a Modular Combustor Designed for a VTOL Tip-Turbine Life Fan.
- Coporate
- Lewis Research Center, Cleveland, OH
- Report
-
NASA TN D-6542,
November 1971,
19 p.
- Keywords
-
combustion chambers
|
fans
|
combustion
|
VSTOL aircraft
|
flame holders
- Identifiers
- VTOL combustor; swirl can combustor
- Abstract
- A modular combustor array of 16 swirl-can modules was tested with liquid ASTM A-1 fuel in a circular duct with a diameter of 27.3 centimeters (10.75 in.) at the combustion plane. Combustors with both a conical and a flat flame holder design were tested and evaluated for combustion efficiency, total-pressure loss, and pattern factor. Combustion tests were conducted at an inlet air temperature of 589 K (600 deg F), an inlet total pressure of 77 N/cm2 (111 psia), and reference velocity of 50 meters per second (165 ft/sec), simulating the design operating point for a 44 482-N (10 000-lbf) thrust VTOL lift engine.