Fundamental Problems of Injector DesignThe principal control of the combustion within a liquid-propellant rocket thrust chamber is provided by the injector. Only when precise control of the injection process is attained can optimum performance, dynamic stability, heat transfer compatibility and reproducibility be provided. Control must be designed into each step of the injection process with sufficient isolation provided to insure stability. In the design of the injector manifolding, the main desire is to provide mass and mixture ratio regulation across the injector face. The design of the injector orifices must be such that this mass and mixture ratio control is retained through the orifices and imparted to the droplet sprays that are produced. Furthermore, the orifice design must control the size and distribution of the droplets generated so that combustion will be completed within the chamber. Mechanical damping devices are often required to protect the early mixing zone from transverse velocities and associated displacement effects in the chamber. Only when each phase of the injection process is carefully controlled can the design aims be reached.
Document ID
19690030799
Acquisition Source
Headquarters
Document Type
Conference Paper
Authors
David T Harrje (Princeton University Princeton, New Jersey, United States)
Date Acquired
August 5, 2013
Publication Date
August 1, 1968
Publication Information
Publication: Advances in Tactical Rocket Propulsion Conference Proceedings
Publisher: Advisory Group for Aerospace Research and Development (AGARD)
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: AGARD Colloquium on Progress in Tactical Rocket Propulsion