Combustion chamber structure for a turbojet engine

US4805397A · kind A · utility

Assignee

• Societe Nationale d'Etude et de Construction de Moteurs d'Aviation - S.N.E.C.M.A · FR

Inventors

• Gerard Y. G. Barbier · Morangis, FR
• Gerard J. P. B. Laboure · Albertville, FR
• Michel A. A. Desaulty · Le Mée-sur-Seine, FR
• Francois Duchene · Melun, FR
• Pascal M. Truvillot · Courbevoie, FR

Key dates

• Filing date: Jun 3, 1987
• Grant date: Feb 21, 1989
• Expiry date: Jun 3, 2007

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05B2260/202
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A combustion chamber for a turbojet engine is disclosed which utilizes double walled construction. Hot walls are attached to adjacent cold walls solely by an orifice member which defines an orifice to supply primary of dilution air to the combustion chamber. The attachment allows relative radial movement of the hot walls with respect to the cold walls so as to accommodate the thermal expansion and contraction of the hot walls. The sleeves forming the walls also cooperate so as to provide an internal cooling film on the interior surface of the hot walls. Convection cooling may also be utilized between the walls to prevent structural damage due to high temperatures.