Aircraft system architecture

An integrated aircraft system comprising an aircraft frame, a nacelle cowl mounted to said aircraft frame, a primary gas turbine engine mounted within said nacelle cowl, a secondary power system incorporated within said nacelle cowl and being driven by a flow of air created by or through said primary gas turbine engine, an electrical power and cooling unit for supplying electrical power and cabin cooling air, said electrical power and cooling unit being pneumatically driven by engine bleed air, an inner core cowl and a casing assembly, said casing assembly defining an engine core compartment within said inner core cowl and said inner core cowl defining an annular by-pass passage with said nacelle cowl, said secondary power system being positioned within said engine core compartment, said second power system including a secondary gas turbine engine, and a radial inlet plenum for allowing air to be drawn directly into said secondary gas turbine engine.

An integrated aircraft system comprising an aircraft frame, a nacelle cowl mounted to said aircraft frame, a primary gas turbine engine mounted within said nacelle cowl, a secondary power system incorporated within said nacelle cowl and being driven by a flow of air created by or through said primary gas turbine engine, an electrical power and cooling unit for supplying electrical power and cabin cooling air, said electrical power and cooling unit being pneumatically driven by engine bleed air, an inner core cowl and a casing assembly, said casing assembly defining an engine core compartment within said inner core cowl and said inner core cowl defining an annular by-pass passage with said nacelle cowl, said secondary power system being positioned within said engine core compartment, said secondary power system including a secondary gas turbine engine, and said primary gas turbine engine having a fan and during ground operation air is drawn in through said fan while said fan is stationary, through said by-pass passage, and then into said secondary gas turbine engine before being discharged back into an aft portion of said by-pass passage.

An integrated aircraft system comprising an aircraft frame, a nacelle cowl mounted to said aircraft frame, a primary gas turbine engine mounted within said nacelle cowl, a secondary power system incorporated within said nacelle cowl and being driven by a flow of air created by or through said primary gas turbine engine, an electrical power and cooling unit for supplying electrical power and cabin cooling air, said electrical power and cooling unit being pneumatically driven by engine bleed air, said electrical power and cooling unit having a shaft and a power turbine, an electrical generator, and a cooling turbine mounted on said shaft, said power turbine and said cooling turbine being supplied with bleed air from said primary gas turbine engine, and said primary gas turbine engine having two bleed ports for delivering at least one of high temperature, high pressure high stage bleed air and mid-stage bleed air to said electrical power and cooling unit.

An integrated aircraft system comprising an aircraft frame, a nacelle cowl mounted to said aircraft frame, a primary gas turbine engine mounted within said nacelle cowl, a secondary power system incorporated within said nacelle cowl and being driven by a flow of air created by or through said primary gas turbine engine, an electrical power and cooling unit for supplying electrical power and cabin cooling air, said electrical power and cooling unit being pneumatically driven by engine bleed air, said electrical power and cooling unit having a shaft and a power turbine, an electrical generator, and a cooling turbine mounted on said shaft, a fan positioned within a ram air duct, said fan being mounted to said shaft, a first heat exchanger means for cooling bleed air from said primary gas turbine engine and secondary heat exchanger means for removing heat from said bleed air exiting said first heat exchanger means.

An integrated aircraft system comprising an aircraft frame, a nacelle cowl mounted to said aircraft frame, an inner core cowl defining an annular by-pass passage within said nacelle cowl, a primary gas turbine engine mounted within said nacelle cowl, a secondary power system incorporated within said nacelle cowl and being driven by a flow of air created by or through said primary gas turbine engine, an axial exhaust duct for directing expanded gases from said secondary power system into said by-pass passage, an electrical power and cooling unit for supplying electrical power and cabin cooling air, and said electrical power and cooling unit being pneumatically driven by engine bleed air.

An integrated aircraft system comprising an aircraft frame, a nacelle cowl mounted to said aircraft frame, a primary gas turbine engine mounted within said nacelle cowl, a secondary power system incorporated within said nacelle cowl and being driven by a flow of air created by or through said primary gas turbine engine, an electrical power and cooling unit for supplying electrical power and cabin cooling air, said electrical power and cooling unit being pneumatically driven by engine bleed air, and a radial inlet plenum for allowing air to be drawn directly into said secondary power system.

An integrated aircraft system comprising an aircraft frame, a nacelle cowl mounted to said aircraft frame, a primary gas turbine engine mounted within said nacelle, a secondary power system incorporated within said nacelle cowl and being driven by a flow of air created by or through said primary gas turbine engine, an electrical power and cooling unit for supplying electrical power and cabin cooling air, said electrical power and cooling unit being pneumatically driven by engine bleed air, said primary gas turbine engine having a fan and during ground operation air is drawn in through said fan while said fan is stationary, through a by-pass passage, and into said secondary power system before being discharged back into an aft portion of said by-pass passage.

An integrated aircraft system comprising an aircraft frame, a nacelle cowl mounted to said aircraft frame, a primary gas turbine engine mounted within said nacelle, a secondary power system incorporated within said nacelle cowl and being driven by a flow of air created by or through said primary gas turbine engine, an electrical power and cooling unit for supplying electrical power and cabin cooling air, said electrical power and cooling unit being pneumatically driven by engine bleed air, and said primary gas turbine engine having two bleed ports for delivering at least one of high temperature, high pressure high stage bleed air and mid-stage bleed air to said electrical power and cooling unit.