US3792584A — Increased or variable bypass ratio engines

Claim 1

Independent Claim 69 words

In a propulsion engine, flow control system for establishing the effective bypass ratio of said engine comprising first and second smooth aerodynamically clean duct means for inverting the spatial relationship of separated adjacent concentric annular flow patterns within the confines of an annular passageway having an area substantially equal to the combined area of the two separate flow patterns at substantially all locations along the length of said passageway.

Claim 2

Dependent Claim 69 words

In a propulsion engine, flow control system for establishing the effective bypass ratio of said engine comprising first and second smooth aerodynamically clean duct means for inverting the spatial relationship of separated adjacent concentric annular flow patterns within the confines of an annular passageway having an area substantially equal to the combined area of the two separate flow patterns at substantially all locations along the length of said passageway.

Claim 3

Dependent Claim 49 words

The system of claim 1 wherein said first and second duct means are each divided at their entrance and exit sections into n/2 circumferentially extending annular sectors and said means for switching flow patterns comprises means for causing relative rotational displacement between said forward and aft portions of 360*/n.

Claim 4

Dependent Claim 64 words

A turbine engine with a fluid flow control system located between two blade elements comprising means for inverting the respective positions of two separate flow patterns between the entrance and exit ends of said system, and means for switching the respective positions of said two flow patterns from their inverted positions to the same respective positions at each of said entrance and exit ends.

Claim 5

Dependent Claim 64 words

A turbine engine with a fluid flow control system located between two blade elements comprising means for inverting the respective positions of two separate flow patterns between the entrance and exit ends of said system, and means for switching the respective positions of said two flow patterns from their inverted positions to the same respective positions at each of said entrance and exit ends.

Claim 6

Dependent Claim 97 words

An air breathing turbine engine comprising a forwardly located fan, a centrally located core gas generator system including compressor and turbine stages, an annular bypass duct communicating with a discharge nozzle, and a flow control system located just downstream of said fan comprising: separated annular first and second duct means shaped and arranged to cross-over and invert two air flow patterns within the confines of an annular passageway, wherein each of said first and second duct means have constant cross-sectional areas the total combined area of which is substantially equal to the area of said annular passageway.

Claim 7

Dependent Claim 97 words

An air breathing turbine engine comprising a forwardly located fan, a centrally located core gas generator system including compressor and turbine stages, an annular bypass duct communicating with a discharge nozzle, and a flow control system located just downstream of said fan comprising: separated annular first and second duct means shaped and arranged to cross-over and invert two air flow patterns within the confines of an annular passageway, wherein each of said first and second duct means have constant cross-sectional areas the total combined area of which is substantially equal to the area of said annular passageway.

Claim 8

Dependent Claim 56 words

The engine of claim 4 wherein said first and second duct means are each longitudinally divided into separate forward and aft portions, and which further includes means for selectively switching flow patterns between said forward and aft portions to thereby eliminate the inversion of flow patterns and cause said flow to pass straight through said passageway.

Claim 9

Dependent Claim 207 words

In an air breathing turbine engine which includes a forwardly located fan, a centrally located core gas generator having compressor and turbine stages, and an annular bypass duct, an improved flow control system for establishing the effective bypass ratio of said engine comprising an annular passageway located downstream of said fan and divided by a central wall means into separate first and second duct means having a combined area substantially equal to the total area of said annular passageway at any position along its length; said first duct means having an annular entrance cross-section extending from an inner wall of said passageway to said central wall means and an annular exit cross-section extending from the outer wall of said passageway to said central wall means such that air is received from said fan and delivered directly to said bypass duct; said second duct means having an annular entrance cross-section extending from the outer wall of said passageway to said central wall means and an annular exit cross-section extending from the inner wall of said passageway to said central wall means such that inlet air which has not been acted upon by said fan is received and delivered directly to a compressor stage of said core gas generator.

Claim 10

Dependent Claim 207 words

In an air breathing turbine engine which includes a forwardly located fan, a centrally located core gas generator having compressor and turbine stages, and an annular bypass duct, an improved flow control system for establishing the effective bypass ratio of said engine comprising an annular passageway located downstream of said fan and divided by a central wall means into separate first and second duct means having a combined area substantially equal to the total area of said annular passageway at any position along its length; said first duct means having an annular entrance cross-section extending from an inner wall of said passageway to said central wall means and an annular exit cross-section extending from the outer wall of said passageway to said central wall means such that air is received from said fan and delivered directly to said bypass duct; said second duct means having an annular entrance cross-section extending from the outer wall of said passageway to said central wall means and an annular exit cross-section extending from the inner wall of said passageway to said central wall means such that inlet air which has not been acted upon by said fan is received and delivered directly to a compressor stage of said core gas generator.

Claim 11

Dependent Claim 70 words

The engine of claim 6 wherein each of said first and second duct means are longitudinally divided into separate forward and aft portions, and which further includes means for switching flow patterns between said forward and aft portions to eliminate the inverting of the spatial relationship of the flow patterns such that the flow passes straight through the annular passageway and thereby changes the effective bypass ratio of said engine.

Claim 12

Dependent Claim 101 words

A propulsion engine comprising a flow control system for internal management and routing of propulsive fluid comprising: a plurality of adjacent basic duct element means located within a longitudinally extending passageway for establishing individual flow patterns characterized by constant cross-sectional areas, and cross-sectional shapes which make smooth gradual longitudinal transitions from a generally rectangular section extending only partially across the passageway at one end of the flow pattern, to a three-sided section extending entirely across the passageway at an intermediate section, and then to a generally rectangular section extending entirely across the passageway at the opposite end of the flow pattern.

Claim 13

Dependent Claim 101 words

A propulsion engine comprising a flow control system for internal management and routing of propulsive fluid comprising: a plurality of adjacent basic duct element means located within a longitudinally extending passageway for establishing individual flow patterns characterized by constant cross-sectional areas, and cross-sectional shapes which make smooth gradual longitudinal transitions from a generally rectangular section extending only partially across the passageway at one end of the flow pattern, to a three-sided section extending entirely across the passageway at an intermediate section, and then to a generally rectangular section extending entirely across the passageway at the opposite end of the flow pattern.

Claim 14

Independent Claim 177 words

A method for improving the efficiency of a propulsion engine having an annular passageway for control of propulsive fluid, said method comprising; dividing said passageway into first and second smooth aerodynamically clean annular flow patterns such that said first flow pattern is located adjacent to, inside of, and concentric with, said second flow pattern at the entrance end of said passageway and such that the combined total cross-sectional area of the first and second flow patterns is substantially equal to the cross-sectional area of said passageway at substantially all locations between the entrance and exit ends of said passageway; compressing the fluid flowing into the first flow pattern; discharging said first and second flow patterns at the exit end of said passageway in an inverted spatial relationship to that which exists at the entrance end of said passageway such that said second flow pattern is located adjacent to, inside of, and concentric with, said first flow pattern; and directing fluid flowing out of said passageway into an annular bypass duct for delivery to a discharge nozzle system.

Claim 15

Independent Claim 177 words

A method for improving the efficiency of a propulsion engine having an annular passageway for control of propulsive fluid, said method comprising; dividing said passageway into first and second smooth aerodynamically clean annular flow patterns such that said first flow pattern is located adjacent to, inside of, and concentric with, said second flow pattern at the entrance end of said passageway and such that the combined total cross-sectional area of the first and second flow patterns is substantially equal to the cross-sectional area of said passageway at substantially all locations between the entrance and exit ends of said passageway; compressing the fluid flowing into the first flow pattern; discharging said first and second flow patterns at the exit end of said passageway in an inverted spatial relationship to that which exists at the entrance end of said passageway such that said second flow pattern is located adjacent to, inside of, and concentric with, said first flow pattern; and directing fluid flowing out of said passageway into an annular bypass duct for delivery to a discharge nozzle system.

Claim 16

Dependent Claim 52 words

The method of claim 9 which further includes: selectively changing the bypass ratio of said engine by switching the relative positions of said first and second flow patterns at the exit end of said passageway such that said first flow pattern remains located inside of and concentric with said second flow pattern.

Claim 17

Dependent Claim 173 words

A propulsion engine configuration which includes a flow control system fOr inverting two flow patterns within a longitudinally extending annular fluid passageway, said system comprising separate first and second smooth aerodynamically clean duct means having adjacent annular cross-sections at the entrance end and the exit end of said passageway and having a combined total cross-sectional area substantially equal to the cross-sectional area of said annular fluid passageway at substantially all locations between said entrance and exit ends; and wherein the entrance cross-section of said first duct means is concentric with and surrounds the entrance cross-section of said second duct means; and wherein said first and second duct means are shaped and arranged to invert the flow pattern such that the exit cross-section of said second duct means is concentric with and surrounds the exit cross-section of said first duct means; thereby discharging two separate flow patterns at the exit end of said passageway in an annular adjacent relationship which is inverted from that existing at said entrance end of said annular fluid passageway.

Claim 18

Dependent Claim 173 words

A propulsion engine configuration which includes a flow control system fOr inverting two flow patterns within a longitudinally extending annular fluid passageway, said system comprising separate first and second smooth aerodynamically clean duct means having adjacent annular cross-sections at the entrance end and the exit end of said passageway and having a combined total cross-sectional area substantially equal to the cross-sectional area of said annular fluid passageway at substantially all locations between said entrance and exit ends; and wherein the entrance cross-section of said first duct means is concentric with and surrounds the entrance cross-section of said second duct means; and wherein said first and second duct means are shaped and arranged to invert the flow pattern such that the exit cross-section of said second duct means is concentric with and surrounds the exit cross-section of said first duct means; thereby discharging two separate flow patterns at the exit end of said passageway in an annular adjacent relationship which is inverted from that existing at said entrance end of said annular fluid passageway.

Claim 19

Dependent Claim 183 words

The system of claim 11 comprising a circular inner wall and a circular outer wall defining the boundaries of said annular passageway, and center wall means for controlling the internal flow within said passageway; said center wall means forming first and second duct means having adjoining first and second duct elements; said first duct element having, at said entrance end, a cross-section extending radially between said outer wall and said center wall means; said second duct element having, at said entrance end, a cross-section adjoining said first duct element at said center wall means and extending radially therefrom to said inner wall; said first and second duct elements having, at a section intermediate said entrance and exit ends, adjoining cross-sections extending radially substantially across said passageway between said inner and outer walls; said first duct element having, at said exit end, a cross-section extending radially between said inner wall and said center wall means; said second duct element having, at said exit end, a cross-section adjoining said first duct element at said center wall means and extending radially therefrom to said outer wall.

Claim 20

Dependent Claim 82 words

The system of claim 12 wherein said first and said second duct means have substantially equal constant areas and wherein said center wall means includes a wall segment the opposite sides of which provide boundary surfaces for said two adjoining duct elements, said wall segment being continuously reshaped and rotated about a locus line which extends parallel to said longitudinal axis such that the cross-sectional areas of said adjoining duct elements will remain substantially equal along the longitudinal extent of said passageway.

Claim 21

Dependent Claim 83 words

The flow control system of claim 13 wherein the system is divided into separated forward and aft portions at a section intermediate said entrance and exit ends at which the duct elements have adjoining cross-sections extending radially substantially across the passageway; and wherein there is provided means for selectively switching flow patterns between adjoining duct elements of said forward and aft portions to thereby cause the flow control system to function as a valve means for switching from inverted to straight through flow.

Claim 22

Dependent Claim 31 words

The flow control system of claim 14 wherein said valve means comprises means for causing relative rotation between said forward and said aft portions to selectively realign next adjacent duct elements.

Claim 23

Dependent Claim 218 words

A propulsion engine configuration comprising a flow system for changing the relative positions of two separated adjacent flow patterns within the confines of a longitudinally extending fluid passageway having an area substantially equal to the combined total area of the two flow patterns at any location along the longitudinal extent of said passageway; said system comprising center wall means forming a first duct means and a second duct means; said first and second duct means sharinG a common wall segment of said center wall means, the opposite sides of said wall segment acting as boundary surfaces for said first and second duct means; said wall segment being rotated and reshaped about a longitudinally extending locus line such that, at the entrance end of said passageway said first duct means comprises a cross-section extending from one side of said passageway to said wall segment, and said second duct means comprises a cross-section extending from said wall segment to the opposite side of said passageway; and at a longitudinal position located downstream from said entrance section said first and second duct means have first and second duct elements which have adjoining cross-sections extending substantially across said passageway and separated by said wall segment which extends substantially across said passageway from said one side to said opposite side of said passageway.

Claim 24

Dependent Claim 218 words

A propulsion engine configuration comprising a flow system for changing the relative positions of two separated adjacent flow patterns within the confines of a longitudinally extending fluid passageway having an area substantially equal to the combined total area of the two flow patterns at any location along the longitudinal extent of said passageway; said system comprising center wall means forming a first duct means and a second duct means; said first and second duct means sharinG a common wall segment of said center wall means, the opposite sides of said wall segment acting as boundary surfaces for said first and second duct means; said wall segment being rotated and reshaped about a longitudinally extending locus line such that, at the entrance end of said passageway said first duct means comprises a cross-section extending from one side of said passageway to said wall segment, and said second duct means comprises a cross-section extending from said wall segment to the opposite side of said passageway; and at a longitudinal position located downstream from said entrance section said first and second duct means have first and second duct elements which have adjoining cross-sections extending substantially across said passageway and separated by said wall segment which extends substantially across said passageway from said one side to said opposite side of said passageway.

Claim 25

Dependent Claim 31 words

The system of claim 16 wherein each of said first and second duct means comprise cross-sectional areas which remain substantially constant at all locations along the longitudinal extent of said passageway.

Claim 26

Dependent Claim 36 words

The system of claim 16 wherein the cross-sectional area of said first duct means is substantially equal to the cross-sectional area of said second duct means at all locations along the longitudinal extent of said passageway.

Claim 27

Dependent Claim 51 words

The system of claim 16 wherein each of said first and second duct elements is characterized by a constant area cross-section making a smooth longitudinal transition from a generally rectangular entrance section, downstream to a generally triangular section, and further downstream to a generally rectangular section extending entirely across said passageway.

Claim 28

Dependent Claim 67 words

The system of claim 16 wherein said passageway has a circular configuration and each of said first and second duct elements is characterized by a constant area cross-section making a smooth longitudinal transition from a segment of an annulus extending only partially across said passageway, downstream to a three-sided section having three curved sides, and downstream to a segment of an annulus extending entirely across said passageway.

Claim 29

Dependent Claim 106 words

The system of claim 18 wherein said first and second duct means extend integrally and continuously to said position at which said first and second duct elements have adjoining cross-sections extending substantially across said passageway, and wherein at said position said first and second duct means are sectioned into separate forward and aft portions each having identical interface cross-sections on opposite sides of said position, and wherein said system includes valve means for selectively switching flow patterns between adjoining duct elements of said forward and aft portions to thereby cause said system to function as a valve means for switching from inverted to straight through flow.

Claim 30

Dependent Claim 28 words

The system of claim 21 wherein said valve means comprises means for causing relative movement between said forward and aft portions to selectively realign next adjacent duct elements.

Claim 31

Dependent Claim 32 words

The engine of claim 3 wherein said system is located within the confines of a fluid passageway having a cross-sectional area substantially equal to the combined area of said two flow patterns.

Claim 32

Dependent Claim 61 words

The engine of claim 23 wherein the boundaries of said system are defined by two oppositely facing walls and the boundaries of said two separated flow patterns are defined by central wall means; and wherein said means for switching includes means for selectively moving at least a portion of said central wall means to cause either inverted or straight through flow.

Claim 33

Dependent Claim 34 words

The engine of claim 23 wherein said system comprises duct elements characterized by generally rectangular cross-sections at said entrance end, generally three-sided cross-sections intermediate said ends, and generally rectangular sections at said exit ends.

Claim 34

Dependent Claim 53 words

The engine of claim 23 wherein the oppositely facing walls are circular in shape and said system includes duct elements characterized by Cross-sections which are segments of an annulus at said entrance end, are curvilinear sections having three curved sides intermediate said ends, and are segments of an annulus at said exit end.

Claim 35

Dependent Claim 24 words

The engine of claim 26 wherein said duct elements have walls the opposite sides of which provide boundary surfaces between said two flow patterns.

Claim 36

Dependent Claim 40 words

The engine of claim 27 wherein said fluid passageway is symmetrically disposed around the longitudinal axis of said engine and said duct elements cross-sections each maintain a plane of symmetry extending along a radial plane passing through said longitudinal axis.

Claim 37

Independent Claim 180 words

A method for improving the efficiency of a propulsion engine having an annular passageway for control of propulsive fluid, said method comprising: dividing said passageway into first and second annular flow patterns such that said first flow pattern is located adjacent to, inside of, and concentric with, said second flow pattern at the entrance end of said passageway; compressing the fluid flowing into the first flow pattern; discharging said first and second flow patterns at the exit end of said passageway in an inverted spatial relationship to that which exists at the entrance end of said passageway such that said second flow pattern is located adjacent to, inside of, and concentric with, said first flow pattern; directing fluid flowing out of said passageway into an annular bypass duct for delivery to a discharge nozzle system; and selectively changing the bypass ratio of said engine by switching the relative positions of said first and second flow patterns at the exit end of said passageway such that said first flow pattern remains located inside of and concentric with said second flow pattern.

Claim 38

Independent Claim 180 words

A method for improving the efficiency of a propulsion engine having an annular passageway for control of propulsive fluid, said method comprising: dividing said passageway into first and second annular flow patterns such that said first flow pattern is located adjacent to, inside of, and concentric with, said second flow pattern at the entrance end of said passageway; compressing the fluid flowing into the first flow pattern; discharging said first and second flow patterns at the exit end of said passageway in an inverted spatial relationship to that which exists at the entrance end of said passageway such that said second flow pattern is located adjacent to, inside of, and concentric with, said first flow pattern; directing fluid flowing out of said passageway into an annular bypass duct for delivery to a discharge nozzle system; and selectively changing the bypass ratio of said engine by switching the relative positions of said first and second flow patterns at the exit end of said passageway such that said first flow pattern remains located inside of and concentric with said second flow pattern.

Claim 39

Dependent Claim 24 words

The method of claim 29 which additionally comprises directing fluid flowing out of said passageway into an annular duct for delivery to a compressor.

Claim 40

Dependent Claim 33 words

The method of claim 29 which additionally comprises dividing said passageway such that at least one of said flow patterns maintains a substantially constant cross-sectional area between said entrance and said exit ends.

Claim 41

Dependent Claim 23 words

The method of claim 31 which additionally comprises dividing said one of said flow patterns into a plurality of separated flow pattern elements.

Claim 42

Dependent Claim 56 words

The method of claim 32 which additionally comprises dividing said one of said flow patterns into a plurality of separated flow pattern elements such that each element has a generally rectangular cross-section at said entrance end, a generally three-sided cross-section intermediate said entrance and said exit ends, and a generally rectangular section at said exit end.

Claim 43

Dependent Claim 35 words

The method of claim 29 wherein said passageway is divided such that said first flow pattern has approximately the same cross-sectional area as said second flow pattern at each of said entrance and exit ends.

Claim 44

Dependent Claim 114 words

In a propulsion engine, a flow control system for establishing the effective bypass ratio of said engine comprising first and second duct means for inverting the spatial relationship of separated adjacent concentric annular flow patterns within the confines of an annular passageway having an area substantially equal to the combined area of the two separated flow patterns, wherein each of said first and second duct means are longitudinally divided into separate forward and aft portions, and which further includes means for switching flow patterns between said forward and aft portions to thereby eliminate the inverting of the spatial relationship of the flow patterns such that the flow effectively passes straight through the annular passageway.

Claim 45

Dependent Claim 114 words

In a propulsion engine, a flow control system for establishing the effective bypass ratio of said engine comprising first and second duct means for inverting the spatial relationship of separated adjacent concentric annular flow patterns within the confines of an annular passageway having an area substantially equal to the combined area of the two separated flow patterns, wherein each of said first and second duct means are longitudinally divided into separate forward and aft portions, and which further includes means for switching flow patterns between said forward and aft portions to thereby eliminate the inverting of the spatial relationship of the flow patterns such that the flow effectively passes straight through the annular passageway.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1977-02-18	1977-08-20	1978-02-19	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1981-02-18	1981-08-20	1982-02-19	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1985-02-18	1985-08-20	1986-02-19	$7700.00	Window Closed / Lapsed

Increased or variable bypass ratio engines

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