Can-Type Combustor Design for a Low Cost Subsonic Ramjet Engine

Abstract

This study investigates the feasibility of using a low cost can combustor in a subsonic ramjet engine in the flight envelope of Mach 0.7 to 0.9, altitude 20,000 to 30,000 feet. A simple can combustor without close fabrication tolerances was designed and fabricated. The can was installed in a subsonic ramjet which was ground tested in a direct-connect pipe set-up. The combustion efficiency and thrust were determined at conditions representative of the flight envelope. These results are compared with results of a model subsonic ramjet engine cycle analysis. The end result of the program is a developed combustor system for a subsonic ramjet which is an inexpensive and attractive propulsion device for one-mission remotely piloted vehicles and target drones.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1975
Accession Number
ADA023471

Entities

People

  • Charles E. Hornbeck

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Flow
  • Air Force
  • Combustion
  • Combustion Products
  • Combustors
  • Equations
  • Fuel Injection
  • Fuel Injectors
  • Fuel Nozzles
  • Heat Energy
  • Mach Number
  • Measurement
  • Pressure Measurement
  • Ramjet Engines
  • Remotely Piloted Vehicles
  • Static Pressure
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Internal Combustion Engine (ICE) Technology.

Technology Areas

  • Autonomy