U.S. patent application number 13/373144 was filed with the patent office on 2013-05-09 for wide faced propeller / turbine blade assembly.
The applicant listed for this patent is John E. Tharp. Invention is credited to John E. Tharp.
Application Number | 20130115093 13/373144 |
Document ID | / |
Family ID | 48223810 |
Filed Date | 2013-05-09 |
United States Patent
Application |
20130115093 |
Kind Code |
A1 |
Tharp; John E. |
May 9, 2013 |
Wide faced propeller / turbine blade assembly
Abstract
An improved propeller/turbine blade assembly with wide faced
blades in order to more efficiently convert a moving fluid's
kinetic energy into mechanical rotational energy by optimizing the
bladed assembly's frontal surface interaction with the swept blade
area of a moving fluid. This improved blade surface interaction is
accomplished through new and novel design features of the
assembly's blades. These design features include the following;
that the designed assembly has a much larger total blade footprint
than prior bladed assemblies, that the assembly's blades overlap
each other with the leading edge of the following blade overlapping
the trailing edge of the preceding blade, that the assembly has
multiple designed blade twist angles that occur within each blade
and at segmented lengths along each blade and that the assembly's
blades are dimensionally segmented with width to length ratios as a
percentage of overall length.
Inventors: |
Tharp; John E.; (Ft. Myers,
FL) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Tharp; John E. |
Ft. Myers |
FL |
US |
|
|
Family ID: |
48223810 |
Appl. No.: |
13/373144 |
Filed: |
November 7, 2011 |
Current U.S.
Class: |
416/226 ;
416/223A; 416/229A; 416/241R |
Current CPC
Class: |
F01D 5/14 20130101; F01D
5/12 20130101 |
Class at
Publication: |
416/226 ;
416/223.A; 416/229.A; 416/241.R |
International
Class: |
F01D 5/14 20060101
F01D005/14; F01D 5/28 20060101 F01D005/28 |
Claims
1. A wide faced propeller/turbine blade assembly is disclosed for
the conversion of a moving fluid's kinetic energy into mechanical
rotational torque energy in which the assembly will; be located and
aligned within a moving fluid in such a manner that the assembly
will be made to rotate as the result of being subjected to the
kinetic energy contained within said moving fluid, be constructed
with a plurality of wide faced propeller/turbine blades, which will
be placed in a symmetrical fan type configuration,
circumferentially and in an angular equidistantly spaced manner on
to the assembly's rotational hub, the assembly's rotational hub
will be located coaxially about a longitudinal centerline axis and
be connected to a rotational horizontal shaft along the
longitudinal centerline axis, wherein the horizontal shaft will
convey the rotating assembly's produced mechanical rotational
energy.
2. The propeller/turbine blade assembly of claim 1 wherein each
blade has: a blade root that is joinable to the assembly hub, a
blade tip, a blade leading edge extending from said root to said
tip, a blade trailing edge extending from said root to said tip, a
blade frontal facing surface extending from said blade root to said
blade tip and extending between the blade leading edge and the
blade trailing edge, a blade rearward facing surface extending from
said blade root to said, blade tip and extending between the blade
leading edge and the blade trailing edge.
3. The propeller/turbine blade assembly of claim 1 where each blade
has contained within it's body an internal center spine support;
and that the internal center spine support runs from the blade root
hub connection plate, in a radial direction from the hub, to the
internal tip spine curve support plate, and that the internal
center spine support adds the required structural support, blade
thickness and rigidity to the areas of the blade occurring along
the internal spine curvature separation line, as seen on the
frontal facing surface of the blade, and thus the internal center
spine support creates the internal spine curvature separation line
on the frontal surface of the blade, and that the internal spine
curvature separation line starts at the root section of the blade
on an almost straight radial line, at the hub and becomes curved
towards the trailing edge of the blade as it reaches the blade
tip's internal spine curve support plate, and that the separation
line between the frontal facing surface's leading edge blade area
and the frontal facing surface's trailing edge blade area is
created by and lies generally over the internal center spine
support, and that the separation line between the rearward facing
surface's leading edge blade area and the rearward facing surface's
trailing edge blade area is created by and lies generally over the
internal center spine support.
4. The propeller/turbine blade assembly of claim 1 wherein each
blade has contained within its body a series of internal rib
supports; and that these internal rib supports are attached to the
internal center spine support contained within each blade, and that
these internal rib supports run internally from each side of the
internal center spine support outwardly towards the leading and
trailing edges of the blade, and that these multiple sets of
internal ribs begin above the root hub support plate and continue
repetitively until ending at the tip spine curve support plate, and
that these internal rib supports add the required structural
support, rigidity and complex convex/concave designed curvatures to
the frontal facing and rearward facing surfaces of the blade.
5. The propeller/turbine blade assembly of claim 1 wherein each
blade may have a layer of expanded metal mesh, woven metal fabric,
alternating directional strips of metal forming a metal weave, or
another form of the internal structural metal mesh type layer, and
that this structural metal mesh layer may be attached to the
internal center spine supports and or the internal rib supports,
and that this structural metal mesh layer may be attached to the
internal center spine supports and or the internal rib supports
with either mechanical fasteners, welding, heat fusion of the
materials, or the use of glue like substances and or a combination
of these methods to attach the structural mesh layer to the other
internal structural components of the blades.
6. The propeller/turbine blade assembly of claim 1 wherein each
blade may have the interior of each blade being comprised of and
consist of any number of commonly known closed cell insulation
materials, and that the closed cell insulation material may be
chosen from the available insulation types commonly known based on
standard design properties such as the material weight, the
structural integrity of the material, the cohesion factors of the
material, the expansion or contraction factors of the material and
the material's resistance to water intrusion, especially under
pressure.
7. The propeller/turbine blade assembly of claim 1 wherein each
blade will have a designed leading edge convex curve in the blade's
direction of rotation and also have a designed dissimilar trailing
edge convex curve which is opposite from the direction of
rotation.
8. The propeller/turbine blade assembly of claim 1 wherein each
blade is designed so that between 30 to 45% of the blade's volume
lies in the direction of rotation, forward of the internal center
spine support and that between 55 to 70% of each blade's volume
lies rearward of the internal center spine support.
9. The propeller/turbine blade assembly of claim 1 wherein each
blade is; rotationally twisted about the blade's internal center
spine support and that the internal center spine support of each
blade is generally located perpendicular to the longitudinal
centerline axis of the blade's assembly hub.
10. The propeller/turbine blade assembly of claim 1 wherein each
blade has a range of segmented blade lengths that occur along the
blade, from the blade root towards the blade tip, and that
occurring at those segmented blade lengths along the blade are a
corresponding range of segmented blade widths, and that both the
segmented blade lengths and blade widths are a designed percentage
of each blade's overall length.
11. The propeller/turbine blade assembly of claim 1 wherein each
blade's horizontal rotational twist around it's internal center
support spine creates a range of blade twist angles occurring at
the noted range of segmented blade lengths along the blade, and
that these range of blade twist angles are relative to the
assembly's longitudinal centerline axis, which is also
perpendicular to the blade's assembly hub, and that these blade
twist angles are clockwise in nature.
12. The propeller/turbine blade assembly of claim 1 wherein each
blade has a designed complex concave and convex blade cross section
that results from a combination of: the range of segmented blade
lengths, the range of segmented blade widths, the rotational twist
about the internal center spine support at the segmented blade
lengths the design of the internal rib supports the internal
structural metal mesh applied to both the frontal facing and
rearward facing sub surfaces of the blade and the internal
structural metal mesh's attachment to the blade's internal rib
supports and/or the blade's internal center spine support.
13. The propeller/turbine blade assembly of claim 1 wherein each
blade's trailing edge and leading edge protrudes generally
perpendicular to and in front of and to the rear of the blade's
assembly hub, when the blade is viewed from the tip looking towards
the blade's root and the assembly hub, and that these designed
leading and trailing blade protrusions are the result of the
combination of the following design factors: the range of the
segmented blade lengths, the range of the segmented blade widths,
the rotational twist angles about the internal center spine support
at the corresponding segmented blade lengths, the design of the
internal rib supports which occur at the corresponding segmented
blade lengths. and the internal structural metal mesh applied to
both the frontal facing and rearward facing sub surfaces of the
blade.
14. The propeller/turbine blade assembly of claim 1 wherein the
values for: the segmented blade lengths of: (L1, L2, L3, L4, and
L5) are: 10-15%, 20-30%, 25-35%, 20-30% and 10-15% of the overall
blade length (L), respectfully, the segmented blade widths of: (WA,
WB, WC and WD) are: 24-29%, 60-70%, 63-72% and 40-47% of the
overall blade length (L), respectfully, the blade twist angles of:
(21, 22, 23, 24 and 25) are: 30-40 degrees, 30-40 degrees, 60-70
degrees, 70-80 degrees and 80-90 degrees, respectfully, relative to
the longitudinal axis of 0 degrees, and that these blade twist
angles occur in a clockwise manner.
15. The propeller/turbine blade assembly of claim 1, wherein each
of the following blade's leading edge partially overlaps each of
the preceding blade's trailing edge, when the bladed assembly is
viewed from the front;
16. The propeller/turbine blade assembly of claim 1, wherein
adjoining overlapping blades have a designed space between their
corresponding rearward facing surfaces and the overlapped blade's
frontal facing surface, and that the space between the adjoining
overlapped blades is designed to channel the moving fluid between
the adjoining blades as the assembly rotates.
17. The propeller/turbine blade assembly of claim 1, wherein the
designed overlap of the adjoining blades occurs as combination of
the following design factors: the number of blades in the assembly,
the diameter of the completed assembly and the percentage of swept
blade area coverage required of the assembly.
18. The propeller/turbine blade assembly of claim 1, wherein the
assembly shall be comprised of multiple blades and that an assembly
of 8 blades has been disclosed.
19. The propeller/turbine blade assembly of claim 1, in which the
assembly may be changed to a clockwise rotational assembly and that
in that case; the design of the blades, and all other required
assembly components shall be altered in order to accomplish the new
rotational direction.
20. The propeller/turbine blade assembly of claim 1, in which a
further embodiment to the bladed assembly disclosed may include the
addition of a common component to such a propeller/turbine blade
assembly which is known in the art as a nose cone or spinner.
Description
FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
[0001] N/A
BACKGROUND OF THE INVENTION
[0002] These propeller/turbine blade assemblies will be used in the
field of kinetic energy conversion. These propeller/turbine blade
assemblies will more efficiently convert the kinetic energy of a
moving fluid into mechanical rotational energy.
SUMMARY OF THE INVENTION
[0003] What is needed in the kinetic energy conversion field of
moving fluids is a more efficient blade assembly to convert the
moving fluid's kinetic energy into the desired mechanical
rotational energy form that can then be coupled to rotational shaft
driven machinery. That machinery can be any number of mechanical
rotational shaft driven types. Those machines would include, but
not be limited to, electric generators and mechanical pumps.
[0004] The following disclosed invention will accomplish this
energy conversion by contacting and redirecting more of the swept
blade area of the moving fluid than prior bladed assemblies have
accomplished in the past. Common bladed assemblies up to now have
relied primarily on the difference in the positive and negative
pressure on the front and back of the blades in order to cause a
rotational movement of the bladed assembly. This has been the
common aeronautical and nautical propeller engineering approach,
but these common propellers were originally designed to screw or
chop their way through a fluid while moving forward with their
attached shaft driven motor. Most previous blade designs were based
on motor driven blades, primarily to achieve forward movement
through a fluid. These previously designed bladed assemblies were
then converted for use in windmills and then, more recently, the
hydrokinetic field of energy conversion.
[0005] Someone who is familiar with a standard propeller is aware
that the propeller blade's contact footprint is a small fraction of
the propeller blade's rotational area, often called the blade's
swept area. This small blade footprint on the moving fluid's swept
area by the standard propeller assembly, at any given second in
time, is why prior bladed assemblies convert little of the moving
fluid's kinetic energy into mechanical rotational torque
energy.
[0006] What is needed and disclosed in this invention is a
different design approach to the problem of small amounts of
kinetic energy conversion achieved by standard propeller bladed
assemblies. The wide faced propeller/turbine blade assembly is
designed to contact and redirect more of the moving fluid. The
disclosed wide faced propeller/turbine blade assembly physically
covers more of the swept blade area of the moving fluid with an
expanded blade footprint. This superior interaction with the moving
fluid will result in greater rotational torque movement of the
blade assembly and thus generate greater rotational torque
energy.
[0007] The disclosed wide faced propeller/turbine blade assembly
will accomplish this more efficient energy conversion in a number
of new and novel ways, as discussed below:
[0008] The first design goal of the wide faced propeller/turbine
blade assembly's design is to have the blades interact with as many
square inches of the swept blade area of the moving fluid as
possible. A major portion of this goal is accomplished by starting
with the disclosed wide faced blade. These assemblies are made up
of multiple blades attached to a central hub which will receive a
rotational shaft. Each blade is wider than the pie shaped section
of the propeller/turbine assembly swept blade area in which it is
fitted. This design allows the wide blade assembly, as viewed from
the front, to cover more swept blade area than previous
propeller/turbine blade assemblies.
[0009] The second design goal was to design the blade with varying
blade twist angles the further from the center of rotation that a
section of blade was located. These blade twist angle requirements
were based on the design considerations of: the blade internal
structural resistance capacity, maximizing the overall area of the
blade frontal surface presented to the oncoming moving fluid,
slimming the profile of the leading edge that rotates horizontally
into the moving fluid, manipulating the positive and negative
pressure areas on the frontal and rearward surfaces of the blade,
curving the fluid directing contours of the frontal and rearward
surfaces of the blade and anticipating the designed rotational
speed of the blade.
[0010] The next design goal for the wide based propeller/turbine
blade assembly is to retain and redirect more the moving fluid
across the face of each individual blade than with other blade
designs, This longer fluid retention and redirection of the fluid
on the blade is accomplished by extending the trailing edge of each
blade to end behind and under the following blade's leading edge,
thus overlapping the blades. This blade overlap forces the retained
fluid on the surface of the blade to travel a longer distance to
exit the trailing edge of the blade.
[0011] The final design element also involves longer retention of
the fluid on the blades. In conventional bladed designs a portion
of the available moving fluid is lost by spillage over the leading
edge of the blade. The wide faced blade reduces the lost fluid
spillage by incorporating the internal spine curvature separation
line on the frontal surface of the blade. This isolation between
the leading edge and trailing edge surfaces of the blade presents a
physical barrier to the movement of the fluid towards the leading
edge of the blade and thus retains more of the fluid on the
trailing edge surface of the blade. The longer the fluid is
retained on the blade in this beneficial part of the blade, the
more time it is being pushed opposite to the designed rotational
direction by the following moving fluid. This pushing action forces
more fluid to exit the trailing edge of the blade and thus imparts
additional forward rotational thrust to the blade.
BRIEF DESCRIPTIONS OF THE DRAWINGS
[0012] FIG. 1 is a frontal view of a wide faced propeller/turbine
blade assembly enhanced with a nose cone.
[0013] FIG. 2 is a side view of a wide faced propeller/turbine
blade assembly enhanced with a nose cone.
[0014] FIG. 3 is a front view of an individual wide faced
propeller/turbine blade.
[0015] FIG. 4 is a 3/4 outline view of an individual wide faced
propeller/turbine blade showing the section lines A-A to D-D, and
the percentage of blade length to blade twist at segmented lengths
along the blade.
[0016] FIG. 5 is a 3/4 outline view of an individual wide faced
propeller/turbine blade showing the blade's internal components and
connection plates.
[0017] FIG. 6 is the cut through sections at A-A to D-D, complete
with the proportionate wide faced blade twist angles at those
segmented section lines.
[0018] FIG. 7 is a 3/4 outline view of the structural metal mesh
internal layer of the typical wide faced propeller/turbine
blade.
[0019] FIG. 8 is the section through the wide faced
propeller/turbine blade along section line M-M showing the internal
metal mesh structural layer and the typical closed cell insulation
center of the typical wide faced blade.
DETAILED DESCRIPTION OF THE DRAWINGS
[0020] The Wide Faced Propeller/Turbine Blade Assembly Drawing
Codes are listed below in order to help in understanding the
following detailed description of the drawings.
1) Individual Wide Faced Propeller/Turbine Blade Assembly.
2) Center Nose Cone on a Wide Faced Propeller/Turbine Blade
Assembly.
3) Wide Faced Propeller/Turbine Blade's Internal Spine Curvature
Separation Line.
4) Wide Faced Propeller/Turbine Blade's Trailing Edge.
5) Wide Faced Propeller/Turbine Blade's Leading Edge.
6) Wide Faced Propeller/Turbine Blade's Tip.
7) Wide Faced Propeller/Turbine Blade's Frontal Facing Surface.
10) Wide Faced Propeller/Turbine Blade's Assembly Hub.
11) Wide Faced Propeller/Turbine Blade's Rearward Facing
Surface.
12) Wide Faced Propeller/Turbine Blade's Root.
19) Wide Faced Propeller/Turbine Blade's Connection to the Assembly
Hub.
21) Wide Faced Propeller/Turbine Blade's Root to Hub Mounting
Angle.
22) Wide Faced Propeller/Turbine Blade's First Segment Twist
Angle.
23) Wide Faced Propeller/Turbine Blade's Second Segment Twist
Angle.
24) Wide Faced Propeller/Turbine Blade's Third Segment Twist
Angle.
25) Wide Faced Propeller/Turbine Blade's Tip Segment Twist
Angle.
26) Wide Faced Propeller/Turbine Blade's Internal Center Spine
Support.
27) Wide Faced Propeller/Turbine Blade's Internal Rib Supports.
28) Wide Faced Propeller/Turbine Blade's Root Hub Connection
Plate.
29) Wide Faced Propeller/Turbine Blade's Tip Spine Curve Support
Plate.
30) Wide Faced Propeller/Turbine Blade's Metal Mesh Structural
Layer.
31) Wide Faced Propeller/Turbine Blade's Closed Cell Center
Insulation.
L) Wide Faced Propeller/Turbine Blade's Overall Length, From Root
to Tip.
L1) Wide Faced Propeller/Turbine Blade's First Segment of Length,
as a Percentage of the Overall Length (L).
L2) Wide Faced Propeller/Turbine Blade's Second Segment of Length,
as a Percentage of the Overall Length (L).
L3) Wide Faced Propeller/Turbine Blade's Third Segment of Length,
as a Percentage of the Overall Length (L).
L4) Wide Faced Propeller/Turbine Blade's Forth Segment of Length,
as a Percentage of the Overall Length (L).
L5) Wide Faced Propeller/Turbine Blade's Fifth Segment of Length,
as a Percentage of the Overall Length (L).
WA) Wide Faced Propeller/Turbine Blade's Cross Section at Section
Line A-A.
WB) Wide Faced Propeller/Turbine Blade's Cross Section at Section
Line B-B.
WC) Wide Faced Propeller/Turbine Blade's Cross Section at Section
Line C-C.
WD) Wide Faced Propeller/Turbine Blade's Cross Section at Section
Line D-D.
MM) Wide Faced Propeller/Turbine Blade's Cross Section at Section
Line M-M.
[0021] FIG. 1 is the frontal view of a wide faced propeller/turbine
blade assembly (1) showing the individual blade's features, the
blade's frontal facing surface (7), the blade's Internal Spine
Curvature Separation Line as the dashed line (3), the blade's
trailing edge (4), the blade's leading edge (5), the relationship
and overlap of the following blade's leading edge over the
preceding blade's trailing edge, the blade's tip (6), the
rotational direction is counter clockwise and that this assembly
has the enhanced blade assembly nose cone (2).
[0022] FIG. 2 is the side view of a wide faced propeller/turbine
blade assembly (1), showing the individual blade's features, the
Internal Spine Curvature Separation Line, which is the dashed line
(3), the blade's trailing edge (4), blade's leading edge (5), the
relationship and overlap of each following blade's leading edge
over the preceding blade's trailing edge, the blade's tip (6), the
blade's frontal facing surface (7), the blade assembly hub (10),
the blade's rearward facing surface (11), the blade's root (12),
the rotational direction is counter clockwise and that this
assembly has the enhanced blade assembly nose cone (2).
[0023] FIG. 3 is the front of an individual wide faced
propeller/blade showing the Internal Spine Curvature Separation
Line, dashed line (3), the blade's trailing edge (4), the blade's
leading edge (5), the blade's tip (6), the blade's frontal facing
surface (7), the blade's root (12), and that the rotational
direction is counter clockwise.
[0024] FIG. 4 is an outline 3/4 frontal view of an individual wide
faced propeller/blade. It was drawn in this manner in order to more
clearly show the mounting angle to the blade array hub (10), the
Internal Spine Curvature Separation Line (3), the blade's trailing
edge (4), the blade's leading edge (5), the blade's tip (6), the
blade's frontal facing surface (7), the assembly hub (10) and the
blade's root (12). This drawing further shows the section lines
A-A, B-B, C-C, and D-D through the blade. Along the length of the
blade are shown the segmented lengths L1, L2, L3, L4, and L5. They
are a percentage of the blade's overall length L. This drawing also
shows the root to hub mounting angle (21) and that the blades are
offset from perpendicular in relationship to the assembly hub (10).
L1 is the segmented length from the hub mounting surface to the
section line A-A, looking back towards the blade assembly hub (10).
This length is between 10 and 15% of the overall blade length L.
Continuing along the blade, L2 is the segmented length from the
section line A-A to the section line B-B. This length is between 20
and 30% of the overall blade length L. Continuing along the blade,
L3 is the segmented length from the section line B-B to the section
line C-C. This length is between 25 and 35% of the overall blade
length L. Continuing along the blade, L4 is the segmented length
from the section line C-C to the section line D-D. This distance is
between 20 and 30% of the overall blade length L. The end length L5
is the segmented length from the section line D-D to the blade tip
(6). This length is between 10 and 15% of the overall blade length
L.
[0025] FIG. 5 is also a 3/4 outline frontal view of an individual
wide faced propeller/blade. It was drawn in this manner in order to
more clearly show the relationship and location of the blade's
internal skeleton components. At the blade root (12), connection
(19), to the assembly hub (10), is found the root hub connection
plate, (28). Connected to root hub connection plate is the root end
of the internal center spine support (26). Along the internal
center spine support starting above the root hub connection plate
is a series of internal rib supports, (27). These internal rib
supports are pairs of horizontal blade body supports that span from
the internal center spine support to the blade's leading and
trailing edges. At the end of the internal center spine support is
the blade's tip spine curve support plate, (29). This tip spine
curve support plate adds rigidity to the blade's tip and allows the
internal spine curvature separation line to make the required curve
at the tip of the blade, thus allowing the blade to shed the fluid
retained on the blade in the designed direction.
[0026] FIG. 6 is composed of four different drawings showing the
detailed section views at section lines A-A through D-D of a
typical wide faced turbine blade, the views also include the
corresponding blade twist angles (22) through (25), as the sections
views progress from the blade's root (12) to the blade's tip (6).
The blade twist angles are taken clockwise from a perpendicular
angle to the blade array hub (10), which corresponds to the axis of
the longitudinal rotational shaft for the assembly and therefore
the perpendicular angle would be our base line of 0 degrees. The
sectional view drawings also show the blade's widths at the section
lines A-A through D-D, as the section lines progress from the
blade's root (12) to the blade's tip (6), these changing blade's
widths at the section lines A-A through D-D are noted on the
sectional views as WA, WB, WC and WD. Starting with Sec. A-A, which
shows the blade's width WA that is a percentage of the blade's
overall length L. The blade's width WA at the section line A-A is
between 24 and 29% of the blade's overall length L. The blade twist
angle (22) at the section line A-A is very similar to the root to
hub mounting angle (21) of an individual blade's root (12), mounted
to the blade assembly hub (10). The similar angles (21) and (22)
are between 30 and 40 degrees clockwise from our base line of 0
degrees. The angle of attack of each blade section into the
oncoming moving fluid is described as the clockwise angle from the
perpendicular angle to the blade assembly hub (10), which is our
base line, 0 degrees, which is also the longitudinal axis of the
rotational shaft of the blade assembly. The section view at the
section line B-B shows the blade's width WB that is a percentage of
the blade's overall length L. The blade's width WB at section line
B-B is between 60 and 70% of the wide faced blade's overall length
L. The blade twist angle (23) has the same clock wise relationship
to a perpendicular angle to the blade assembly hub (10). The blade
twist angle (23) is between 60 and 70 degrees clockwise from the
base line, 0 degrees. Continuing on, the section view at the
section line C-C shows the blade's width WC that is a percentage of
the blade's overall length L. The blade's width WC at section line
C-C is between 63 and 72% of the blade's overall length L. The
blade twist angle (24) has the same relationship to a perpendicular
angle to the blade array hub (10). The blade twist angle (24) is
between 70 and 80 degrees clockwise from the base line, 0 degrees.
The end section view D-D shows the blade's width WD that is a
percentage of the blade's overall length L. The blade's width WD at
D-D is between 40 and 47% of the blade's overall length L. The
blade twist angle (25) is in the same relationship to a
perpendicular angle to the blade array hub (10). The blade twist
angle (25) is between 80 and 90 degrees clockwise from the base
line, 0 degrees. These section views also show the internal blade
support components. Starting with the blade root hub connection
plate, (28) shown in section view A-A. The internal center spine
support, (26) and the internal rib supports, (27) are shown in both
section views B-B and C-C. The final section view D-D, shows the
internal center spine support (26), the internal rib supports (27)
and the tip spine curve support plate, (29). As shown, all of the
internal structural support components are contained within the
body of the blades starting from the blade root (12) and ending at
the blade tip (6), including the structural metal mesh layer (30)
and the closed cell center insulation (31).
[0027] FIG. 7 is the 3/4 view of the wide faced propeller/turbine
blade showing the blade's root (12), the assembly hub (10), the
blade's tip (6), the blades frontal face (7), the Internal Spine
curvature Separation Line (3), the section line M-M and the Blade
length L. This view primarily shows the internal metal mesh
structural layer (30), on both the front and rear of the typical
blade,
[0028] FIG. 8 is the section MM of a wide face blade that occurs
along the section line of M-M in FIG. 7. This figure shows the
internal parts of a typical wide faced blade including:
[0029] The internal center spine support, (26) and the internal rib
supports, (27) the internal metal mesh structural layer, (30) and
the internal closed cell center insulation (31), also shown in this
drawing is the: Internal Spine Curvature Separation Line, which is
the dashed line (3), the blade's trailing edge (4), blade's leading
edge (5), the blade's tip (6), the blade's frontal facing surface
(7), the blade assembly hub (10) and the blade's rearward facing
surface (11).
* * * * *