US3659422A — Method and apparatus for aircraft propulsion

Claim 1

Independent Claim 137 words

An aircraft propulsion system comprising a main gas generator, an air bypass duct associated with said main gas generator for passing air around said main gas generator; at least one auxiliary gas generator located adjacent to said main gas generator; means for compressing inlet air, said means being driven by said main gas generator; means for directing the output air of said compressor means to the inlet of said main gas generator, said air bypass duct and said auxiliary gas generator; said main gas generator, bypass duct and auxiliary engine each having a separate exhaust nozzle means; and means for selectively and alternatively governing the airflow in said bypass duct and said auxiliary engine, said last named means including means for varying the area of at least said bypass duct and auxiliary gas generator exhaust nozzle means.

Claim 2

Dependent Claim 137 words

An aircraft propulsion system comprising a main gas generator, an air bypass duct associated with said main gas generator for passing air around said main gas generator; at least one auxiliary gas generator located adjacent to said main gas generator; means for compressing inlet air, said means being driven by said main gas generator; means for directing the output air of said compressor means to the inlet of said main gas generator, said air bypass duct and said auxiliary gas generator; said main gas generator, bypass duct and auxiliary engine each having a separate exhaust nozzle means; and means for selectively and alternatively governing the airflow in said bypass duct and said auxiliary engine, said last named means including means for varying the area of at least said bypass duct and auxiliary gas generator exhaust nozzle means.

Claim 3

Dependent Claim 51 words

The aircraft propulsion system of claim 1 wherein said main gas generator is a turbofan engine and said auxiliary gas generator is a turbojet engine, and wherein said last named means includes means for providing a secondary airflow through said turbojet engine when said main airflow is through said bypass duct.

Claim 4

Dependent Claim 22 words

The aircraft propulsion system of claim 1 wherein said main gas generator exhaust nozzle means includes means for varying the exhaust area.

Claim 5

Dependent Claim 33 words

The aircraft propulsion system of claim 1 including at least one inlet duct connected to the intake of said air compressing means, and means for controlling the airflow characteristics of said inlet duct.

Claim 6

Dependent Claim 23 words

The aircraft propulsion system of claim 1 wherein said airflow governing means includes an air diverting valve located in said air directing means.

Claim 7

Dependent Claim 35 words

The aircraft propulsion system of claim 5 including means for bypassing a selected portion of air around said bypass duct to pass through said auxiliary engines when the main airflow is through said bypass duct.

Claim 8

Dependent Claim 32 words

The aircraft propulsion system of claim 1 wherein said bypass duct forms an annular passage around said main gas generator, and including a plurality of auxiliary engines located around said annular passage.

Claim 9

Dependent Claim 43 words

The aircraft propulsion system of claim 7 including means for diverting air from said Annular passage into said auxiliary engines, and means responsive to said diverting means for varying the area of said exhaust nozzle means of said bypass duct and auxiliary engine.

Claim 10

Dependent Claim 25 words

The aircraft propulsion system of claim 1 wherein said auxiliary gas generator has an afterburner located between said generator and its associated exhaust nozzle means.

Claim 11

Dependent Claim 163 words

A propulsion system for use at subsonic and supersonic speeds comprising a first propulsion unit adapted for use at subsonic speeds and at least one other propulsion unit adapted for use at supersonic speeds both of said propulsion units having air inlets connected to a common plenum, means for selectively operating said units, compressor means at the inlet end of said plenum, said compressor means being connected to and driven by said first propulsion unit, air inlet duct means connected to the intake of said compressor, bypass duct means adjacent said first propulsion unit, means for selectively controlling the airflow from said plenum to the intake of said other propulsion unit and to said bypass so that when said other units are not operating said airflow is primarily through said first unit and said bypass, said first propulsion unit and said other propulsion unit having separate exhaust nozzles, and means for varying the exhaust nozzle area in response to said selective control means.

Claim 12

Dependent Claim 163 words

A propulsion system for use at subsonic and supersonic speeds comprising a first propulsion unit adapted for use at subsonic speeds and at least one other propulsion unit adapted for use at supersonic speeds both of said propulsion units having air inlets connected to a common plenum, means for selectively operating said units, compressor means at the inlet end of said plenum, said compressor means being connected to and driven by said first propulsion unit, air inlet duct means connected to the intake of said compressor, bypass duct means adjacent said first propulsion unit, means for selectively controlling the airflow from said plenum to the intake of said other propulsion unit and to said bypass so that when said other units are not operating said airflow is primarily through said first unit and said bypass, said first propulsion unit and said other propulsion unit having separate exhaust nozzles, and means for varying the exhaust nozzle area in response to said selective control means.

Claim 13

Dependent Claim 146 words

An aircraft propulsion system comprising an inlet duct means, compressor means having its inlet connected to said inlet duct; a main gas generator, said main gas generator being connected to and driving said compressor means; collector duct means connected to the outlet of said compressor means and to the inlet of said main gas generator; bypass duct means around said main gas generator; at least one auxiliary engine; said collector duct means being connected to the inlets of said bypass duct and said auxiliary engine; said auxiliary engine, bypass duct, and main gas generator each having a separate exhaust nozzle; means for controlling said main gas generator, said auxiliary engine and said exhaust nozzles to maintain proper airflow and engine performance characteristics; and diverter valve means in said collector duct for selectively and alternatively directing air into either said bypass duct or said auxiliary engine inlet.

Claim 14

Dependent Claim 146 words

An aircraft propulsion system comprising an inlet duct means, compressor means having its inlet connected to said inlet duct; a main gas generator, said main gas generator being connected to and driving said compressor means; collector duct means connected to the outlet of said compressor means and to the inlet of said main gas generator; bypass duct means around said main gas generator; at least one auxiliary engine; said collector duct means being connected to the inlets of said bypass duct and said auxiliary engine; said auxiliary engine, bypass duct, and main gas generator each having a separate exhaust nozzle; means for controlling said main gas generator, said auxiliary engine and said exhaust nozzles to maintain proper airflow and engine performance characteristics; and diverter valve means in said collector duct for selectively and alternatively directing air into either said bypass duct or said auxiliary engine inlet.

Claim 15

Independent Claim 102 words

A method of operating an aircraft propulsion system having a primary subsonic engine and at least one auxiliary supersonic engine comprising the steps of mechanically pressurizing a quantity of air sufficient to sustain full operation of said engines, energizing said primary engine to operate in a subsonic mode while maintaining said auxiliary engine in a standby condition, said primary engine utilizing a portion of said air quantity while the remainder is directed through a bypass, energizing said auxiliary engine while simultaneously increasing the airflow through said auxiliary engine and reducing the airflow through said bypass, said primary engine being maintained in operation.

Claim 16

Independent Claim 102 words

A method of operating an aircraft propulsion system having a primary subsonic engine and at least one auxiliary supersonic engine comprising the steps of mechanically pressurizing a quantity of air sufficient to sustain full operation of said engines, energizing said primary engine to operate in a subsonic mode while maintaining said auxiliary engine in a standby condition, said primary engine utilizing a portion of said air quantity while the remainder is directed through a bypass, energizing said auxiliary engine while simultaneously increasing the airflow through said auxiliary engine and reducing the airflow through said bypass, said primary engine being maintained in operation.

Claim 17

Dependent Claim 26 words

The method of claim 12 including the step of increasing the exhaust area of said auxiliary engine while simultaneously decreasing the exhaust area of said bypass.

Claim 18

Dependent Claim 46 words

The method of claim 12 wherein said auxiliary engine has an afterburner and said method includes the step of initiating afterburner operation when said auxiliary engine has reached a preselected dry operating temperature and increasing the nozzle area of said auxiliary engine with increased afterburner temperature.

Claim 19

Independent Claim 137 words

A method of operating a turbofan engine and at least one turbojet engine in a plurality of modes for propelling an aircraft at selected speeds in both subsonic and supersonic ranges comprising the steps of varying the combustor temperature of the turbofan engine for fan mode operation while maintaining the turbojet engine in an inactive condition and while bypassing air around the turbofan engine; changing the airflow from the bypass path to the turbojet while initiating the operation of the turbojet; the turboFan engine operating at high RPM while the combustor temperature of the turbojet engine is varied to control the speed during the dry mode of operation, and minimizing drag in each operating mode by varying the exhaust nozzle areas of said engines and said air bypass to maintain a predetermined airflow for each operating mode.

Claim 20

Independent Claim 137 words

A method of operating a turbofan engine and at least one turbojet engine in a plurality of modes for propelling an aircraft at selected speeds in both subsonic and supersonic ranges comprising the steps of varying the combustor temperature of the turbofan engine for fan mode operation while maintaining the turbojet engine in an inactive condition and while bypassing air around the turbofan engine; changing the airflow from the bypass path to the turbojet while initiating the operation of the turbojet; the turboFan engine operating at high RPM while the combustor temperature of the turbojet engine is varied to control the speed during the dry mode of operation, and minimizing drag in each operating mode by varying the exhaust nozzle areas of said engines and said air bypass to maintain a predetermined airflow for each operating mode.

Claim 21

Dependent Claim 52 words

The method of claim 15 wherein said turbojet includes an afterburner including the steps of initiating afterburner operation of the turbojet engine when increased power is required while maintaining the turbofan and turbojet engines at high RPM and varying the afterburner fuel flow to control the power in the afterburner operating mode.

Claim 22

Dependent Claim 36 words

The method of claim 15 including the step of windmilling the turbojet engine in its inactive condition during the fan operating mode so that the time required to initiate operation of the turbojet engine is minimized.

Claim 23

Dependent Claim 31 words

The method of claim 15 including the step of decreasing the exhaust area for the bypassing air while simultaneously increasing the exhaust area of the turbojet exhaust to change said airflow.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1975-05-02	1975-11-01	1976-05-02	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1979-05-02	1979-11-01	1980-05-02	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1983-05-02	1983-11-01	1984-05-02	$7700.00	Window Closed / Lapsed

Method and apparatus for aircraft propulsion

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