Accession Number : ADP200296

Title :   Laser Schlieren and Ultraviolet Diagnostics of Rocket Combustion,

Corporate Author : ROCKWELL INTERNATIONAL CANOGA PARK CA ROCKETDYNE DIV

Personal Author(s) : Fisher,S. C.

Report Date : OCT 1984

Pagination or Media Count : 15

Abstract : A low pressure oxygen/hydrogen turbine drive combustor hot-fire test series was conducted on the Turbine Drive Combustor Technology Program. The first objective of the test series was to gather data on an axisymmetric combustion system to support anchoring of a new combustion/fluid dynamics computer code under development on the same contract. The second objective was to gain insight into low mixture ratio combustion characteristics of coaxial injector elements. This paper discusses the diagnostic test setup used in the hot-fire test program and the results obtained. Most of the data collected is in the form of high-speed laser Schlieren cinematography and ultraviolet cinematography of the actual ignition and combustion process inside a combustion chamber system. Details of the 9000 frames/sec laser Schlieren system and the ultraviolet cinematography system are described. The combustion model utilized in the program was designed to simulate the Space Shuttle Main Engine (SSME) oxidizer preburner ignition conditions. (Author)

Descriptors :   *ROCKET ENGINES, *COMBUSTION, *CINEMATOGRAPHY, GAS TURBINES, DRIVES, COMBUSTORS, TEST METHODS, HIGH TEMPERATURE, HYDRODYNAMIC CODES, IGNITION, OXIDIZERS, LASER APPLICATIONS, ULTRAVIOLET RADIATION, SIMULATION, SPACE SHUTTLES, INJECTORS, SYMPOSIA

Subject Categories : Photography
      Combustion and Ignition
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE