Variable cycle engine with split fan section

Claim 2

An improved variable cycle gas turbine engine of the type having an inlet for supplying a gas flow to a gas generator comprising a compressor, a combustor, and a high pressure turbine in serial flow relation, wherein the improvement comprises: a fan disposed in the inlet having a front section for receiving and compressing the total inlet airflow and an aft section axially displaced downstream from the front fan section, duct means for bypassing a portion of the inlet gas flow around the aft fan section and gas generator, and diverter valve means disposed intermediate the aft fan section and gas generator for controlling the amount of gas flow from the front fan section to the bypass duct means, aft fan section and gas generator and movable between a first position in which the total gas flow exiting the front fan section is directed to and compressed by the aft fan section and the airflow exiting the aft fan section is divided between the bypass duct means and gas generator, and a second position in which the gas flow exiting the front fan section is divided between the bypass duct means and aft fan section, and the total gas flow exiting the aft fan section is directed to the gas generator.

Claim 3

The gas turbine engine of claim 1 wherein: the bypass duct means is movable to all positions intermediate the first and second positions.

Claim 4

A variable cycle gas turbine engine comprising: a gas generator comprising a compressor, combustor, and high pressure turbine in serial flow relation, all circumscribed by an inner nacelle, an outer nacelle circumscribing and spaced apart from the inner nacelle so as to form a bypass duct around the gas generator and extending upstream of the inner nacelle to form the inlet to the engine and downstream of the inner nacelle to provide an exhaust system for the engine, a front fan section disposed in the inlet for compressing the total inlet gas flow, an intermediate nacelle spaced radially inward from the outer nacelle and disposed intermediate and axially spaced apart from the front fan section and inner nacelle to form an intermediate passageway therethrough whereby the gas flow exhausted from the front fan section is divided between the bypass duct and intermediate passageway and the gas flow exhausted from the intermediate passageway is divided between the gas generator and bypass duct, an aft fan section disposed in the intermediate passageway for compressing the gas flow therethrough, and diverter valve means rotatably disposed about the downstream end of the intermediate nacelle and movable between positions to selectively abutt the inner and outer nacelles for selectively controlling the amount of gas flow from the front fan section to the bypass duct and intermediate passageway and the amount of gas flow from the intermediate passageway to the bypass duct and gas generator.

Claim 5

A variable cycle gas turbine engine comprising: a gas generator comprising a compressor, combustor, and high pressure turbine in serial flow relation, all circumscribed by an inner nacelle, an outer nacelle circumscribing and spaced apart from the inner nacelle so as to form a bypass duct around the gas generator and extending upstream of the inner nacelle to form the inlet to the engine and downstream of the inner nacelle to provide an exhaust system for the engine, a front fan section disposed in the inlet for compressing the total inlet gas flow, an intermediate nacelle spaced radially inward from the outer nacelle and disposed intermediate and axially spaced apart from the front fan section and inner nacelle to form an intermediate passageway therethrough whereby the gas flow exhausted from the front fan section is divided between the bypass duct and intermediate passageway and the gas flow exhausted from the intermediate passageway is divided between the gas generator and bypass duct, an aft fan section disposed in the intermediate passageway for compressing the gas flow therethrough, and diverter valve means rotatably disposed about the downstream end of the intermediate nacelle and movable between positions to selectively abutt the inner and outer nacelles for selectively controlling the amount of gas flow from the front fan section to the bypass duct and intermediate passageway and the amount of gas flow from the intermediate passageway to the bypass duct and gas generator.

Claim 6

The gas turbine engine of claim 3 when the diverter valve means is movable between a first position in which the total gas flow exiting the front fan section is directed to the intermediate passageway and the gas flow exiting the intermediate passageway is divided between the bypass duct and gas generator, and a second position in which the gas flow exiting the front fan section is divided between the bypass duct and intermediate passageway and the total gas flow exiting the intermediate passageway is directed to the gas generator.

Claim 7

The gas turbine engine of claim 4 wherein the diverter valve means comprises: a rotatable hinged flap pivotally secured to the downstream end of the intermediate nacelle and extending into the bypass duct so as to obtrude the bypass duct at a point downstream of the aft fan section when the diverter valve is in the first position and to obtrude flow between the intermediate passageway and the bypass duct when the diverter valve is in the second position, and a linear actuator having a control arm in driving engagement with the flap for rotating the flap about the downstream end of the intermediate nacelle between the first and second positions.

Claim 8

The variable cycle engine of claim 5 further comprising: a variable area exhaust nozzle secured to the downstream end of the outer nacelle, and a variable area mixer disposed intermediate the gas generator and exhaust nozzle for combining the gas generator and bypass duct exhaust streams.

Claim 9

The gas turbine engine of claim 6 futher comprising: a low pressure turbine disposed downstream of and in serial flow relation with the gas generator for supplying rotational energy to the front fan section, and wherein the rotational energy to the aft fan section is supplied through a driveshaft interconnecting the aft fan section and high pressure turbine.