Robert A Vogt

US Patent:

49169068, Apr 17, 1990

Filed:

Mar 25, 1988

Appl. No.:

7/176482

Inventors:

Robert L. Vogt - Marblehead MA

Assignee:

General Electric Company - Lynn MA

International Classification:

F23R 304

US Classification:

60757

Abstract:

The present invention comprises a method and apparatus for improving cooling of a wall in a gas turbine engine. The method and apparatus provide breach cooling of an imperforate wall, such as a combustor liner, for improving the cooling thereof. The breach cooling includes structure for channeling a cooling fluid as a jet toward an outer surface of the imperforate wall, with the jet having sufficient memontum to breach a boundary layer of the cooling fluid which forms over the wall outer surface to allow the jet to contact the wall outer surface for more effective cooling thereof. In an exemplary embodiment of the invention, the breach-cooled wall is an upstream portion of the gas turbine engine combustor, and the inner surface of the combustor liner facing the combustion gases is characterized by not having a film-cooling boundary layer of air to reduce quenching of the combustion gases for reducing exhaust emissions.

US Patent:

50834223, Jan 28, 1992

Filed:

Mar 7, 1990

Appl. No.:

7/489627

Inventors:

Robert L. Vogt - Marblehead MA

Assignee:

General Electric Company - Lynn MA

International Classification:

F02G 300

US Classification:

60 3902

Abstract:

The present invention comprises a method and apparatus for improving cooling of a wall in a gas turbine engine. The method and apparatus provide breach cooling of an imperforate wall, such as a combustor liner, for improving the cooling thereof. The breach cooling includes structure for channeling a cooling fluid as a jet toward an outer surface of the imperforate wall, with the jet having sufficient momentum to breach a boundary layer of the cooling fluid which forms over the wall outer surface to allow the jet to contact the wall outer surface for more effective cooling thereof. In an exemplary embodiment of the invention, the breach-cooled wall is an upstream portion of the gas turbine engine combustor, and the inner surface of the combustor liner facing the combustion gases is characterized by not having a film-cooling boundary layer of air to reduce quenching of the combination gases for reducing exhaust emissions.