Compact gas turbine engine

Patent · Tue Jul 23 04:00:00 EDT 1991

OSTI ID:5775145

Shekleton, J R; Lafferty, M K

This patent describes a gas turbine engine; a rotor including turbine blades and a nozzle adjacent the turbine blades, the nozzle being adapted to direct hot gases of combustion at the turbine blades to cause rotation of the rotor; an annular combustor about the rotor defined by spaced inner and outer walls connected by a radially extending wall, an annular combustor housing substantially surrounding the combustor in generally concentric spaced relation to the inner, outer and radially extending walls thereof, the housing including a pair of spaced apart turbine shrouds disposed relative to one another so as to define the nozzle and to cover the turbine blades, the one of the turbine shrouds nearest the combustor, together with the remainder of the housing and the inner, outer and radially extending walls, defining a dilution air flow path extending from a compressed air inlet in communication with a source of dilution air to a compressed air outlet; means for positioning the combustor within the housing including abutment means between the outer wall of the combustor and the one of the turbine shrouds furthest from the combustor for accommodating axial movement of the outer wall of the combustor toward and away from the one of the turbine shrouds furthest from the combustor.

• Assignee: Sundstrand Corp., Rockford, IL (USA)
• Patent Number(s): US 5033263; A
• Application Number: PPN: US 7-324688
• OSTI ID: 5775145
• Country of Publication: United States
• Language: English

Related Subjects

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