Radial inflow combustor

Patent · Tue Dec 03 04:00:00 EST 1991

OSTI ID:5580817

Shekleton, J R

This paper describes a gas turbine engine. It comprises: radial compressor means for compressing air entering through a compressor inlet opening; axial turbine means in axially spaced relation to the radial compressor means; the radial compressor means being operatively associated with the axial turbine means; radial combustor means intermediate the radial compressor means and axial turbine means; turbine nozzle means proximate the axial turbine means for directing gases of combustion thereto; the radial combustor means including a pair of axially spaced radially extending walls joined at radially outward extremes by a generally cylindrical wall, the walls defining a radial combustion space in communication with both the radial compressor means and the turbine nozzle means, and including means for introducing compressed air into the radial combustion space in a manner avoiding formation of an air film on the generally cylindrical wall.

• Assignee: Sundstrand Corp., Rockford, IL (United States)
• Patent Number(s): US 5069033; A
• Application Number: PPN: US 7-455559
• OSTI ID: 5580817
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
COMBUSTORS
DESIGN
ENGINES
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
NOZZLES