Floating speed electrically driven suction system

Claim 2

A suctioning system for drawing a high volume of an ambient fluid flow at a low ambient pressure P, comprising: a variable speed, mechanically driven, permanent magnet generator with a low reactance, variable voltage, variable frequency, alternating electrical current output; an electrical induction motor directly connectable to receive said output from said generator in an unconditioned state and drive an output shaft associated with the motor; a suction compressor having an inlet receiving the ambient fluid flow and rotatably driven by said shaft to suction said ambient fluid flow; and adjustable inlet guide vanes at said inlet for variably preswirling said ambient fluid flow before reaching said compressor; and control means for adjusting said guide vanes to maintain ΔP/P substantially constant, where: ΔP=(ambient pressure-compressor inlet pressure).

Claim 3

A suctioning system for drawing a high volume flow of low pressure boundary layer airflow through a plurality of openings on an external surface of an aircraft into an enclosed cavity within the external surface, comprising: an electrical generator adapted to be driven at variable speeds; an electrical induction motor directly connectable to said generator to rotatably drive an output shaft at variable speeds; a suction compressor having an inlet and being rotatably driven by said shaft at variable speeds to draw airflow into said inlet; a first conduit extending from said cavity to said inlet, whereby said compressor draws said boundary layer into said cavity; adjustable guide vanes at said inlet for variably preswirling airflow delivered to said inlet; a second conduit for delivering ambient airflow to said inlet in parallel flow relation to that in said first conduit; a surge control valve in said second conduit for opening and closing communication of said inlet with the ambient airflow; and control means for adjusting said guide vanes and for opening and closing said surge control valve.

Claim 4

A suctioning system for drawing a high volume flow of low pressure boundary layer airflow through a plurality of openings on an external surface of an aircraft into an enclosed cavity within the external surface, comprising: an electrical generator adapted to be driven at variable speeds; an electrical induction motor directly connectable to said generator to rotatably drive an output shaft at variable speeds; a suction compressor having an inlet and being rotatably driven by said shaft at variable speeds to draw airflow into said inlet; a first conduit extending from said cavity to said inlet, whereby said compressor draws said boundary layer into said cavity; adjustable guide vanes at said inlet for variably preswirling airflow delivered to said inlet; a second conduit for delivering ambient airflow to said inlet in parallel flow relation to that in said first conduit; a surge control valve in said second conduit for opening and closing communication of said inlet with the ambient airflow; and control means for adjusting said guide vanes and for opening and closing said surge control valve.

Claim 5

A suctioning system as set forth in claim 2, wherein said control means is operable to adjust said guide vanes to maintain ΔP/P substantially constant, where: ΔP=(ambient pressure-compressor inlet pressure) and P=compressor inlet pressure.

Claim 6

A suctioning system as set forth in claim 3, wherein said control means is operable to open said second conduit to deliver ambient airflow to said inlet to maintain total airflow through said compressor above a preselected minimum.

Claim 7

A suctioning system as set forth in claim 2, wherein said control means is operable to open said second conduit to deliver ambient airflow to said inlet to maintain total airflow through said compressor above a preselected minimum.

Claim 8

A suctioning system as set forth in claim 2, further including first sensing means for sensing compressor inlet pressure (P), and second sensing means for sensing ambient pressure, said control means responsive to said first and second sensing means to maintain ΔP/P substantially constant, where: ΔP=(ambient pressure-compressor inlet pressure).

Claim 9

A suctioning system as set forth in claim 6, further including third sensing means for sensing the rate of discharge airflow from said compressor, said control means responsive to said third sensing means to open said second conduit to deliver ambient airflow to said inlet to maintain total airflow through said compressor above a preselected minimum.

Claim 10

A suctioning system as set forth in claim 7, wherein said generator is a permanent magnet generator developing a low reactance, variable frequency, variable voltage, multi-phase, sine wave, alternating current electrical output power in an unconditioned state and about 100 kilowatts.

Claim 11

A suctioning system as set forth in claim 8, wherein said induction motor is a multi-phase synchronous induction motor directly connectable to receive said output power in said unconditioned state and to rotate said power output shaft.

Claim 12

A suctioning system as set forth in claim 2, wherein said generator is a permanent magnet generator with a low reactance, variable frequency, variable voltage, three-phase, sine wave, alternating current electrical output power in an unconditioned state and about 100 kilowatts.

Claim 13

A suctioning system as set forth in claim 10, wherein said induction motor is directly connectable to receive said output power in said unconditioned state and to rotate said power output shaft.

Claim 14

A suctioning system adapted to draw a high volume flow of low pressure boundary layer airflow through a plurality of openings on an external surface of an aircraft into an enclosed cavity within the external surface, comprising: an electrical generator adapted to be directly driven by an engine on the aircraft at variable speeds; an electrical induction motor directly connectable to said generator to rotatably drive an output shaft at variable speeds; a suction compressor having an inlet and being rotatably driven by said shaft at variable speeds to draw airflow into said inlet; a first conduit adapted to deliver airflow from said cavity to said inlet, whereby said compressor is adapted to draw the boundary layer airflow into said cavity; adjustable guide vanes at said inlet for variably preswirling airflow delivered to said inlet; a second conduit adapted to deliver ambient airflow to said inlet in parallel flow relation to that in said first conduit; a surge control valve in said second conduit for opening and closing communication of said inlet with the ambient airflow; and control means for adjusting said guide vanes and for opening and closing said surge control valve.

Claim 15

A suctioning system adapted to draw a high volume flow of low pressure boundary layer airflow through a plurality of openings on an external surface of an aircraft into an enclosed cavity within the external surface, comprising: an electrical generator adapted to be directly driven by an engine on the aircraft at variable speeds; an electrical induction motor directly connectable to said generator to rotatably drive an output shaft at variable speeds; a suction compressor having an inlet and being rotatably driven by said shaft at variable speeds to draw airflow into said inlet; a first conduit adapted to deliver airflow from said cavity to said inlet, whereby said compressor is adapted to draw the boundary layer airflow into said cavity; adjustable guide vanes at said inlet for variably preswirling airflow delivered to said inlet; a second conduit adapted to deliver ambient airflow to said inlet in parallel flow relation to that in said first conduit; a surge control valve in said second conduit for opening and closing communication of said inlet with the ambient airflow; and control means for adjusting said guide vanes and for opening and closing said surge control valve.

Claim 16

A suctioning system as set forth in claim 12, further including first sensing means for sensing compressor inlet pressure (P), and second sensing means for sensing ambient pressure, said control means responsive to said first and second sensing means to maintain ΔP/P substantially constant, where: ΔP=(ambient pressure-compressor inlet pressure).

Claim 17

A suctioning system as set forth in claim 13, further including third sensing means for sensing the rate of discharge airflow from said compressor, said control means responsive to said third sensing means to open said second conduit to deliver ambient airflow to said inlet to maintain total airflow through said compressor above a preselected minimum.

Claim 18

A suctioning system as set forth in claim 14, wherein said generator is a permanent magnet generator with a low reactance, variable frequency, variable voltage, multi-phase, sine wave, alternating current electrical output power in an unconditioned state and about 100 killowatts.

Claim 19

A suctioning system as set forth in claim 15, wherein said induction motor is a multi-phase synchronous induction motor directly connectable to receive said output power in said unconditioned state and to rotate said output shaft.

Claim 20

In combination with an aircraft having a propulsion engine, an external surface with a plurality of openings therein, and an internal chamber for drawing boundary layer airflow from said external surface through said openings, a boundary layer airflow suctioning system, comprising: an electrical generator directly driven by the aircraft engine at variable speeds; an electrical induction motor directly connected to said generator to rotatably drive an output shaft at variable speeds; a suction compressor having an inlet and being rotatably driven by said shaft at variable speeds to draw airflow into said inlet; a first conduit extending from said chamber to said inlet, whereby said compressor draws said boundary layer airflow into said chamber; adjustable guide vanes at said inlet for variably preswirling airflow delivered to said inlet; a second conduit for delivering ambient airflow to said inlet in parallel flow relation to that in said first conduit; a surge control valve in said second conduit for opening and closing communication of said inlet with the ambient airflow; and control means for adjusting said guide vanes and for opening and closing said surge control valve.

Claim 21

In combination with an aircraft having a propulsion engine, an external surface with a plurality of openings therein, and an internal chamber for drawing boundary layer airflow from said external surface through said openings, a boundary layer airflow suctioning system, comprising: an electrical generator directly driven by the aircraft engine at variable speeds; an electrical induction motor directly connected to said generator to rotatably drive an output shaft at variable speeds; a suction compressor having an inlet and being rotatably driven by said shaft at variable speeds to draw airflow into said inlet; a first conduit extending from said chamber to said inlet, whereby said compressor draws said boundary layer airflow into said chamber; adjustable guide vanes at said inlet for variably preswirling airflow delivered to said inlet; a second conduit for delivering ambient airflow to said inlet in parallel flow relation to that in said first conduit; a surge control valve in said second conduit for opening and closing communication of said inlet with the ambient airflow; and control means for adjusting said guide vanes and for opening and closing said surge control valve.

Claim 22

A combination as set forth in claim 17, wherein said control means is operable to adjust said guide vanes to maintain ΔP/P substantially constant, where: ΔP=(ambient pressure-compressor inlet pressure) and P=compressor inlet pressure.

Claim 23

A combination as set forth in claim 18, wherein said control means is operable to open said second conduit to deliver ambient airflow to said inlet to maintain total airflow through said compressor above a preselected minimum.