Annular combustor with outer transition liner cooling

Patent · Tue Aug 24 04:00:00 EDT 1993

OSTI ID:6271270

Harris, M M; Marsh, D N

A reverse flow annular combustor for a gas turbine engine is described having an upstream end and a downstream end comprising at least one annular wall, extending radially from an inner end to an outer end which is upstream of the inner end, the wall disposed at the downstream end of the combustor and having an interior surface exposed to the hot gas in the combustor, and an annular shroud disposed about an exterior surface of the angular wall and abutting thereto at a plurality of points thereby defining a plurality of passages between the wall and shroud, the passages receiving air through a plurality of holes through the inner radial end of the shroud and delivering air to a plurality of apertures through the outer radial end of the wall.

• Assignee: Allied-Signal Inc., Morris Township, NJ (United States)
• Patent Number(s): A; US 5237813
• Application Number: PPN: US 7-934053
• OSTI ID: 6271270
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
ANNULAR SPACE
COMBUSTORS
CONFIGURATION
ENGINES
FLUID FLOW
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
SPACE
WALLS