US4699340A — Laminar vortex pump system

Claim 1

Independent Claim 271 words

An improvement in an aircraft having a wing with a lower surface and an upper surface, the two surfaces being joined at a leading and a trailing edge, the thickness of the wing increasing from the leading edge to a maximum thickness and then decreasing to the trailing edge such that in flight the wing generates a static pressure on the upper surface that is lower than on the lower surface to generate lift, the wing having a streamwise direction and a spanwise direction transverse to the streamwise direction, the improvement comprising: a plurality of substantially uninterrupted ridges on at least the upper of the surfaces, the ridges extending from in front of the maximum thickness and past the maximum thickness towards the trailing edge of the wing, generally in a parallel array and generally in the streamwise direction, the height, orientation and length of each ridge being such that the cross-coupling terms of the streamwise accelerations are an order of magnitude greater than the acceleration of the streamwise flow due to the wing shape and friction over substantially the entire wing, i.e., ##EQU9## whereby the spanwise flow over each of the ridges generates a standing vortex on its lee side, each vortex: (1) providing a suction source to collect low energy boundary layer fluid near the surface of the wing and formed from flow in the freestream direction, (2) providing a conduit to transport such spent fluid aft for discharge into the wake beyond the wing trailing edge, and (3) forcing continuous replenishment by fresh fluid from the outer stream to maintain laminar flow on the surface of the wing.

Claim 2

Dependent Claim 271 words

An improvement in an aircraft having a wing with a lower surface and an upper surface, the two surfaces being joined at a leading and a trailing edge, the thickness of the wing increasing from the leading edge to a maximum thickness and then decreasing to the trailing edge such that in flight the wing generates a static pressure on the upper surface that is lower than on the lower surface to generate lift, the wing having a streamwise direction and a spanwise direction transverse to the streamwise direction, the improvement comprising: a plurality of substantially uninterrupted ridges on at least the upper of the surfaces, the ridges extending from in front of the maximum thickness and past the maximum thickness towards the trailing edge of the wing, generally in a parallel array and generally in the streamwise direction, the height, orientation and length of each ridge being such that the cross-coupling terms of the streamwise accelerations are an order of magnitude greater than the acceleration of the streamwise flow due to the wing shape and friction over substantially the entire wing, i.e., ##EQU9## whereby the spanwise flow over each of the ridges generates a standing vortex on its lee side, each vortex: (1) providing a suction source to collect low energy boundary layer fluid near the surface of the wing and formed from flow in the freestream direction, (2) providing a conduit to transport such spent fluid aft for discharge into the wake beyond the wing trailing edge, and (3) forcing continuous replenishment by fresh fluid from the outer stream to maintain laminar flow on the surface of the wing.

Claim 3

Dependent Claim 45 words

The improvement claimed in claim 1 wherein the ridges are spaced at a lateral distance "l" less than the product of the chord length "c" of the wing and the ratio of the maximum spanwise velocity "V" to the maximum streamwise velocity "U", i.e.: ##EQU10##

Claim 4

Dependent Claim 22 words

The improvement claimed in claim 2 wherein the values of spanwise velocity and freestream velocity are taken at cruise and level flight.

Claim 5

Dependent Claim 49 words

The improvement claimed in claim 2 wherein the ridges have an inclination on their windward side at least on the upper wing surface aft the maximum thickness to utilize freestream fluid velocity in addition to spanwise flow in the driving of the standing vortex aft of the maximum thickness.

Claim 6

Dependent Claim 39 words

The improvement claimed in claim 1 wherein the ridges have a greatest height proximate the maximum thickness of the wing, the height of the ridges being no greater than an order of magnitude greater than the boundary layer thickness.

Claim 7

Dependent Claim 19 words

The improvement claimed in claim 5 wherein the ridges fair smoothly into the wing surface proximate the trailing edge.

Claim 8

Dependent Claim 25 words

The improvement claimed in claim 2 wherein the ridges increase in section in both height and width from the leading edge to their greatest section.

Claim 9

Dependent Claim 25 words

The improvement claimed in claim 1 wherein the height of the ridges is no greater than an order of magnitude of the boundary layer thickness.

Claim 10

Dependent Claim 20 words

The improvement claimed in claim 8 wherein the height of the ridges is no greater than the boundary layer thickness.

Claim 11

Dependent Claim 242 words

An improvement in an aircraft having a wing of finite span and both a lower surface and an upper surface, the two surfaces being joined at a leading and trailing edge, the improvement comprising: a plurality of spaced apart and substantially continuous ridges on at least the upper of the surfaces oriented to utilize the spanwise flow induced by the finite span to relocate the trailing vortices onto the surface of the wing, the vortices providing a suction source to collect the stagnant sub-boundary layer from the upper surface of the wing, the vortices then providing conduits to transport such low energy fluid aft for discharge into the wake beyond the wing trailing edge and forcing continuous replacement of the low energy fluid by fresh fluid from the outer stream to maintain laminar flow on the upper surface of the wing, the ridges, having a height, width and shape such that the streamwise accelerations due to cross-coupling effects are an order of magnitude greater than the acceleration of the streamwise flow due to the wing shape, i.e., ##EQU11## where v is spanwise velocity, y is spanwise distance, w is vertical velocity, z is vertical distance, u is streamwise velocity and x is streamwise distance; and the ridges are spaced a lateral distance "l" less than the product of the chort length "c" of the wing and the ratio of the maximum spanwise velocity "V" to the maximum streamwise velocity "U", i.e., ##EQU12##

Claim 12

Dependent Claim 242 words

An improvement in an aircraft having a wing of finite span and both a lower surface and an upper surface, the two surfaces being joined at a leading and trailing edge, the improvement comprising: a plurality of spaced apart and substantially continuous ridges on at least the upper of the surfaces oriented to utilize the spanwise flow induced by the finite span to relocate the trailing vortices onto the surface of the wing, the vortices providing a suction source to collect the stagnant sub-boundary layer from the upper surface of the wing, the vortices then providing conduits to transport such low energy fluid aft for discharge into the wake beyond the wing trailing edge and forcing continuous replacement of the low energy fluid by fresh fluid from the outer stream to maintain laminar flow on the upper surface of the wing, the ridges, having a height, width and shape such that the streamwise accelerations due to cross-coupling effects are an order of magnitude greater than the acceleration of the streamwise flow due to the wing shape, i.e., ##EQU11## where v is spanwise velocity, y is spanwise distance, w is vertical velocity, z is vertical distance, u is streamwise velocity and x is streamwise distance; and the ridges are spaced a lateral distance "l" less than the product of the chort length "c" of the wing and the ratio of the maximum spanwise velocity "V" to the maximum streamwise velocity "U", i.e., ##EQU12##

Claim 13

Dependent Claim 33 words

The improvement claimed in claim 10 wherein the ridges have a greatest height at and proximate to the maximum thickness of the wing, the ridges aft of their greatest height decreasing in height.

Claim 14

Dependent Claim 33 words

The improvement claimed in claim 1 wherein the ridges have a greatest width at and proximate to the maximum thickness of the wing, the ridges aft of their greatest width decreasing in width.

Claim 15

Dependent Claim 43 words

The improvement claimed in claim 10 wherein the ridges are asymmetric in section having a modest inclination on their windward side to provide a smooth flow up that side and a more vertical inclination on their lee side to generate the standing vortex.

Claim 16

Dependent Claim 23 words

The improvement claimed in claim 13 wherein the values of the spanwise velocity and freestream velocity are taken at cruise and level flight.

Claim 17

Dependent Claim 54 words

The improvement claimed in claim 14 wherein the ridges have an inclination in the spanwise direction on their windward side at least on the upper wing surface and aft the maximum thickness to utilize freestream fluid velocity in addition to spanwise flow in the driving ot he standing vortex aft of the maximum thickness.

Claim 18

Dependent Claim 33 words

The improvement claimed in claim 15 wherein the ridges have a greatest height at and proximate to the maximum thickness of the wing, the ridges aft of their greatest height decreasing in height.

Claim 19

Dependent Claim 70 words

The improvement claimed in claim 16 wherein the ridges have a greatest width at and proximate to the maximum thickness of the wing, the ridges aft of their greatest width decreasing in width, and the ridges are asymmetric in section having a modest inclination on their windward side to provide a smooth flow up that side and a more vertical inclination on their lee side to generate the standing vortex.

Claim 20

Dependent Claim 26 words

The improvement claimed in claim 10 wherein the height of the ridges is no greater than an order of magnitude greater than the boundary layer thickness.

Claim 21

Dependent Claim 128 words

In a streamlined body of revolution having a series of ridges, an improvement comprising: (a) the body having a forward apex, an intermediate surface of greatest circumference after the apex, and an aft closure after the intermediate surface, all disposed about an axis; and (b) the ridges being inclined at a small angle to the axis and originating between the apex and the surface of greatest diameter, a first short set of the ridges decreasing in section, fairing out smoothly and terminating on the surface, and a second set of the ridges continuing past the termination of the first set to increase vortex size by merger of adjacent vortices formerly confined by short ridges of the first set alternating every other one with ridges of the second set.

Claim 22

Dependent Claim 128 words

In a streamlined body of revolution having a series of ridges, an improvement comprising: (a) the body having a forward apex, an intermediate surface of greatest circumference after the apex, and an aft closure after the intermediate surface, all disposed about an axis; and (b) the ridges being inclined at a small angle to the axis and originating between the apex and the surface of greatest diameter, a first short set of the ridges decreasing in section, fairing out smoothly and terminating on the surface, and a second set of the ridges continuing past the termination of the first set to increase vortex size by merger of adjacent vortices formerly confined by short ridges of the first set alternating every other one with ridges of the second set.

Claim 23

Dependent Claim 38 words

The improvement claimed in claim 19 wherein the ridges on one side of the body are inclined all in the same sense and the ridges on the opposite side of the body are inclined in the opposite sense.

Claim 24

Independent Claim 216 words

A method of reducing drag on an air foil of finite span having an upper surface and a lower surface, the upper surface being longer than the lower surface along a freestream direction, the method comprising the steps of: (a) providing relative motion between a fluid and the air foil in a freestream direction; (b) inducing vortices along the upper surface from the spanwise flow resulting from the finite span of the air foil being intercepted by continuous ridges running generally in the freestream direction from ahead of the air foil's maximum thickness aft; (c) inducing by the height and shape of the ridges an acceleration of the fluid in the boundary layer in the freestream direction due to cross-coupling terms of an order of magnitude greater than the acceleration of the fluid in the freestream direction from friction and air foil shape; (d) collecting low energy boundary layer fluid formed by the motion in the freestream direction in the vortices by the relatively low pressure there; (e) transporting the collected fluid in the vortices in the freestream direction and discharging the spent fluid in a wake aft of the trailing edge of the airfoil; and (f) replacing the low energy fluid by fresh fluid from the freestream through low pressure close to the wing surface.

Claim 25

Independent Claim 216 words

A method of reducing drag on an air foil of finite span having an upper surface and a lower surface, the upper surface being longer than the lower surface along a freestream direction, the method comprising the steps of: (a) providing relative motion between a fluid and the air foil in a freestream direction; (b) inducing vortices along the upper surface from the spanwise flow resulting from the finite span of the air foil being intercepted by continuous ridges running generally in the freestream direction from ahead of the air foil's maximum thickness aft; (c) inducing by the height and shape of the ridges an acceleration of the fluid in the boundary layer in the freestream direction due to cross-coupling terms of an order of magnitude greater than the acceleration of the fluid in the freestream direction from friction and air foil shape; (d) collecting low energy boundary layer fluid formed by the motion in the freestream direction in the vortices by the relatively low pressure there; (e) transporting the collected fluid in the vortices in the freestream direction and discharging the spent fluid in a wake aft of the trailing edge of the airfoil; and (f) replacing the low energy fluid by fresh fluid from the freestream through low pressure close to the wing surface.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1990-10-12	1991-04-13	1991-10-13	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1994-10-12	1995-04-13	1995-10-13	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1998-10-12	1999-04-13	1999-10-13	$7700.00	Window Closed / Lapsed

Laminar vortex pump system

Abstract

Inventors

Bibliographic Details

Claims Analysis

References Cited (Backward Citations)

USPTO Annuity & Maintenance Windows

Assigned Categories & Tags

Assign Category Tag