THE PROBLEM OF CREATING INTERMEDIATE GAS PREHEAT COMBUSTION CHAMBERS IN A GAS TURBINE UNIT,
Abstract
A preliminary research study on the development of an annular combustion chamber with a preheating process is described. The chamber design is shown. The external liner and internal liner circumscribe the chamber volume which contains stabilizer combined with the fuel nozzle. The internal channel of the stabilizer-fuel nozzle unit contains blading apparatus with a 45 degrees flow deflection angle. The fuel flows from annular collector through a series of slots 0.35 mm in diameter. The fuel is injected at a pressure exceeding that of gases by 0.5-1.5 ata. The fuel-air mixing takes place in internal channels of the stabilizer-fuel nozzle. The telescopic liner confines the flame to the combustion zone. Up to 25 percent of the air is bypassed through annular channels and for cooling purposes. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 13, 1969
- Accession Number
- AD0695892
Entities
People
- E. I. Savoshchenko
- V. I. Kurbatova
- V. P. Lebedev
- Yu. M. Pchelkin
Organizations
- National Air and Space Intelligence Center