Accession Number:

AD0754852

Title:

Ramjet Engine Fuel Injection Studies

Descriptive Note:

Technical rept. 5 Oct 1970-15 Sep 1971

Corporate Author:

AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1972-11-01

Pagination or Media Count:

44.0

Abstract:

The purpose of the investigation was to develop empirical methods for designing a fuel injection system applicable to sudden expansion burners using a coaxial inlet. An integral rocketramjet missile may utilize this type of fuel system. The primary objective of a liquid fuel injection system is to provide the combustion chamber with the proper amount of fuel in a pattern that will result in efficient combustion over the flight path of the missile. The relative amounts of fuel and air at the flameholding region are important in determining the efficiency of combustion. From the local fuelair ratio relationship, a family of curves was plotted, which are functions of downstream distance and overall fuelair ratio. With these curves, the injector was placed at the appropriate distance from the flameholding region to obtain stoichiometric conditions at that region. Subsequent tests using the AFAPL Ramjet Burner Thrust Stand Facility verified that efficient combustion was achieved.

Subject Categories:

  • Combustion and Ignition
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE