Design Characteristics and Performance of a Combustor for Use as an Ionized Gas Source in Magnetohydrodynamic Power Generation Studies

Abstract

September 1969This document has been approved for public release e* f^-Vi.' its distribution is unlimited, .^/>Ot-r 71^ This document io nubjeefr-te^pixräi^xprnina)ltl.lOlS , Jlidnationals may rw made-only-with-pcieM-approvaLof -Air Force -Aere-Pfeputeien-JsafeeRttory-(AP.IEa2),»JWtighiPa«eMen=iAF'B»se^Ohiö-45433. ROCKET TEST FACILITY ARNOLD ENGINEERING DEVELOPMENT CENTER AIR FORCE SYSTEMS COMMAND ARNOLD AIR FORCE STATION, TENNESSEEWOHER OF U n S" m E02CB mim when U. S. Government drawings specifications, or other data are used for any purpose other than a definitely related Government procurement operation, the Government thereby incurs no responsibility nor any obligation whatsoever, and the fact that the Government may have formulated, furnished, or in any way supplied the said drawings, specifications, or other data, is not to be regarded by implication or otherwise, or in any manner licensing the holder or any other person or corporation, or conveying any rights or permission to manufacture, use, or sell any patented invention that may in any way be related thereto.Qualified users may obtain copies of this report from the Defense Documentation Center.References to named commercial products in this report are not to be considered in any sense as an endorsement of the product by the United States Air Force or the Government. AEDCTR-69- ABSTRACTDesign characteristics and performance of a combustor for use as a high energy, ionized gas source in magnetohydrodynamic power generator studies are described. The liquid oxygen (LC»2)/JP-4 combustor was operated over a chamber pressure range from 240 to 300 psia and at a characteristic exhaust velocity efficiency of 91 ± 1 percent for oxidizer/fuel ratios ranging from 2. 0 to 3. 1. Combustor power output was approximately 17.5 to 20.5 megawatts (MW) over its range of operation. Provisions were incorporated into the design for injection of a saturated solution of water and cesium carbonate seeding agent into the thrust chamber to provide a high ion concentration in the exhaust gases.This document is subject to special export controls and each transmittal to foreign governments or foreign nationals may be made only with prior approval of Air Force Aero-Propulsion Laboratory (APIE-2), WrightPatterson AF Base, Ohio 45433.Ill AEDC-TR.69.167 CONTENTS

Operating Characteristics of a 45-Deg-Slant, Segmented Wall, Magnetohydrodynamic Generator Channel under No-Power Conditions

“…These data are in excellent agreement with the theoretical heat-transfer rates presented in Ref. 3 where the heat-transfer rate at the combustor nozzle exit (or channel inlet) was calculated to be 4. 8 Btu/sec-in.…”

“…Details of combustor design considerations and operating characteristics are presented in Ref. 3. The combustor injector assembly (Fig.…”