THE PROBLEM OF FLAME STABILIZATION IN THE AFTERBURNER OF A GAS TURBINE ENGINE,
Abstract
A new ejector-type flame holder was developed for afterburners in gas turbine combustion chambers. Conventional V-shaped flame holders cause considerable flow resistance, particularly in regimes without afterburning. The proposed ejector system is located directly behind the turbine or at the end of the diffuser. It consists of two annular airfoils which have a negligible flow resistance compared with V-shaped flame holders. The air foils are perforated on one side and the perforations are connected with the duct which becomes the mixing duct behind the chamber. When the afterburner chamber is operated, high pressure air from the last compressor stage is introduced through nozzle into the mixing duct. Thus, the air jet from the compressor acts as the active gas which generates a rarefaction zone in the mixing duct and thus moves the passive gas from the afterburner chamber. As a result of the partial or complete removal of gas between the airfoils at the end of the annular duct, a rarefaction zone is created. The gas which flows on the outside of the airfoils expands at the trailing edge of the airfoils and causes reverse vortex flows which stabilize the flames. A design method for the ejector-type flameholder was developed and formulas for calculating the ejection coefficient and the geometry factor were derived. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 03, 1968
- Accession Number
- AD0682806
Entities
People
- I. N. Dyatlov
Organizations
- National Air and Space Intelligence Center