U.S. patent number 3,744,927 [Application Number 05/117,988] was granted by the patent office on 1973-07-10 for yieldable blades for propellers.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to Henry J. Bernaerts.
United States Patent |
3,744,927 |
Bernaerts |
July 10, 1973 |
YIELDABLE BLADES FOR PROPELLERS
Abstract
A blade design for propellers of watercraft wherein the blades
of the proler are weakened in the line of impact but retain
substantially all of their strength along the line of hydrodynamic
load. Such a weakening permits the blades of a propeller to shear
off or yield upon impact with an object without damage to the
motor, shaft or pitch changing mechanism.
Inventors: |
Bernaerts; Henry J. (Amberley,
MD) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (Washington,
DC)
|
Family
ID: |
22375888 |
Appl.
No.: |
05/117,988 |
Filed: |
February 23, 1971 |
Current U.S.
Class: |
416/2; 415/9;
416/131; 416/205 |
Current CPC
Class: |
B63H
1/20 (20130101) |
Current International
Class: |
B63H
1/00 (20060101); B63H 1/20 (20060101); B63h
001/20 () |
Field of
Search: |
;416/2,207,206,241A,131,135,140,142,143,228,205 ;415/9 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
238,027 |
|
Oct 1959 |
|
AU |
|
976,790 |
|
Nov 1950 |
|
FR |
|
624,166 |
|
Jul 1961 |
|
CA |
|
2,013,481 |
|
Oct 1970 |
|
DT |
|
Primary Examiner: Powell, Jr.; Everette A.
Claims
What is claimed is:
1. A propeller for watercraft, comprising:
a hub;
a series of blade assemblies attached to the hub, wherein the
assemblies are weakened along a longitudinal axis extending through
the leading and trailing edges thereof without weakening the blade
at an oblique angle to said axis wherein hydrodynamic loads
occur;
each blade assembly has a blade portion and a base for attaching
the assemblies to the hub;
the assemblies are attached to the hub by bolts extending through
the base wherein said bolts are spaced rearwardly of the leading
edge and outwardly of the longitudinal axis;
the lower surface of the base is tapered rearwardly of the bolts to
leave a gap between said surface and the hub; and
each blade is mounted to extend outwardly from its respective base
to rotate relative to the hub about an axis normal to the base.
Description
The invention described herein may be manufactured and used by or
for the Government of the United States of America for Governmental
purposes without the payment of any royalties thereon or
therefor.
BACKGROUND OF THE INVENTION
The propellers of watercraft are relatively unprotected and while
underway the blades can impact on obstructions. Such an impact
usually causes extensive damage extending from the prime mover
through the power transmission system to the propeller itself. The
instant stopping of the propeller with the inertia load of the rest
of the rotating parts of the propulsion system is the primary cause
of damage to propulsion machinery. A secondary cause of damage is
the eccentric load imposed by the stopping of one blade which
impacts on the obstruction.
The problem is particularly acute in Hazelton or tandem propulsion
systems wherein the propeller hub is an annular ring the size and
contour of the hull on which it is mounted. The blades mounted on
such a hull protrude beyond the hull contour and are therefore more
susceptible to impact. Also, the diameter of the propeller hub
being so large the impacting blade forms a lever arm with the
centerline of the propeller thus magnifying any forces generated
therein. This force becomes important in a Hazelton propeller as
the blade pitch changing mechanism and power transmission
assemblies, as shown in U.S. Pat. Nos. 3,010,066 and 3,450,083, to
Hazelton, are carried with the hub and susceptible to any impact
loads thereon.
DESCRIPTION OF THE PRIOR ART
The prior art, as represented by current propeller technology, does
not appear to include the concept of yieldable or breakaway blades.
The concept of yieldable devices to absorb shock is well developed,
with specific areas being yieldable bushings or clutches in the
propeller hub, or mounted in the drive shaft. These devices have
met with some success in that they protect the propulsion system
beyond the resilient member. For example, a flexible coupling in
the drive shaft would not protect the propeller, its hub, and that
portion of the shaft before the coupling. Also, such devices lend
themselves to conventional screw propellers with their relatively
small diameter hubs and drive shafts attached thereto. The Hazelton
type propellers with annular hubs and a multiplicity of relatively
small blades spaced therearound do not lend themselves to an
adaptation of current screw-propeller technology.
SUMMARY OF THE INVENTION
This invention utilizes the principle of weakening a propeller
blade so that upon impact with an obstruction the blade will break
off the propeller hub without damaging the propulsion system. The
blades are weakened in a plane along which collision would normally
occur, i.e. along the centerline of the blade in a fore and aft
direction. The blade is not weakened in a plane along its
hydrodynamic load axis which is at an acute angle to the
aforementioned plane of collision. In this way the blade is not
weakened, or nominally weakened, for its primary function of
propulsion but is sufficiently weakened to shear off the propeller
hub upon impact.
BRIEF DESCRIPTION OF THE DRAWING
FIG. 1 is a top plan view showing a Hazelton propeller blade
embodying the subject invention.
FIG. 2 is a side view of the Hazelton propeller blade of FIG.
1.
FIG. 3 is a side view of another embodiment of the subject
invention.
FIG. 4 is a side view, with parts cut away for clarity, of yet
another embodiment of the subject invention.
DESCRIPTION OF THE INVENTION
Referring now to the drawing, FIGS. 1 and 2 show a Hazelton type
propeller blade assembly 10, which is mounted on the annular hub
assembly 12, that is common to this type of propeller. The blade
10, is mounted on the hub 12, for rotational movement relative
thereto to permit pitch changing of the blades. The pitch changing
mechanism is not shown as it does not form a part of the invention
and is mentioned herein to adequately describe the environment in
which the subject invention is to be used.
The blades 10, have a general cross-section of an airfoil or
teardrop as shown in FIG. 1. Therefore, the leading edge 14 will
always cut into the water first and be subject to any collision
with an obstruction. The blade assembly 10 has a base 16, with
bolts 18, extending therethrough to attach the blade 10 to the
pitch changing mechanism. Due to the entrance of leading edge 14,
into the water to create the forward motion of a vehicle the
hydrodynamic loads on the blade 10 will occur generally along the
lines indicated at B. As can be seen, these lines of loading, B,
occur on the side of and at an angle to the longitudinal axis of
the blade 10. Therefore, the collision on the leading edge 14
causes a moment around moment axis D and the hydrodynamic loads
cause a moment which has a major component around moment axis
C.
The collision moment will cause a relatively high tension load on
bolts 18 because of the short lever arm distance between line D and
the trailing edge of base 16. The hydrodynamic moment will cause a
relative small tension load on bolts 18 because of the long lever
arm distance which is at least equal to the distance between the
centers of bolts 18.
As the leading edge 14 of the blade 10, cuts through the water
first, any collision will occur along a plane through axis C, and
pivot the blade 10, relative to the hub 12, about the trailing edge
of base 16. In order to aid the pivoting of the blade 10, about the
trailing edge of base 16, with respect to the hub 12 upon
collision, the base 16 can be tapered as shown at 20, rearward of
the bolts 18 and their axis D. The bolts might also be made of a
metal having a low specific strain to facilitate their breaking on
excessive exertion. Thus on impact with an obstruction the blade
will more readily pivot about the axis D and break the bolts
18.
In operation when the blade 10 is cutting through the water and the
leading edge 14 thereof strikes an obstruction the load imposed by
the collision will occur along a plane through axis C. There are no
fastening bolts along this axis so a pivotal moment will be created
about the axis D formed by bolts 18. The taper 20, will facilitate
the pivotal movement and the bolts 18 will break. Thus the blade 10
will fall off without transmitting the large shock load of a
collision to the pitch changing mechanism and/or power transmission
system.
Referring now to FIG. 3, a Hazelton propeller blade 22 is shown
utilizing another embodiment of the subject invention. The blade
22, has the same cross section as the blade 10, as shown in FIG. 1.
The blade 22, has a base 24, with a shaft 26, extending therefrom
to connect the blade to the pitch changing mechanism. The axis of
rotation of the blade 22, for its pitch changing mechanism, is
shown by axis A', extending through the line of the shaft 26. As in
the previous embodiment, the blade 22 has a leading edge 28 that
will incurr a collision with an obstruction as it always cuts
through the water first. Thus, a cut 30 is made through the blade
from the leading edge 28, extending toward the axis A'. The cut 30,
is filled with a filler, such as a plastic compound, as at 32, to
fill the cut and maintain the contour and fairing of the blade 22.
Similarly, a wedge-shaped cut 34, is made through the blade 22,
from the rear of the blade toward the axis A'. This cut is also
filled with a filler 35 to restore the contour of the blade 22.
In operation, as the blade 22 cuts through the water, if a
collision with an obstruction should occur, the leading edge 28 of
the blade will receive the impact. The cut 30, which weakens the
blade 22, along its axis, will initiate and insure a rearward
pivoting of the blade about an axis running through the axis of
rotation A'. This will force out the filler 35, and permit the
blade to completely pivot downwardly and shear off at the base 24.
Thus, any load imposed by an impact of blade 22, on an obstruction
will be absorbed and dissipated in the bending and breaking of the
weakened blade. Any destructive forces normally transmitted through
the propeller to the pitch-changing mechanism or propulsion system
will be avoided.
Referring now to FIG. 4, a still further embodiment of a Hazelton
blade assembly 36, embodying the subject invention is shown. The
blade assembly 36, has a blade 38 attached to a shaft 40 which
extends from a pitch-change mechanism. The shaft 40, is rotatably
received through the usual Hazelton annular hub 42.
The shaft 40, at the end extending outwardly of the hub 42, has a
cylindrical recess 44, with a narrow opening 46 extending
thereinto. A groove or seat 48, with rounded edges extends
diametrally across the end of the shaft, at a right angle to the
longitudinal axis of the blade, to form a seat for the blade 38,
and establish a pivot along an axis extending along this diametral
axis. For example, the groove or seat 48 could extend completely
across the shaft 40 or be a slot at the center thereof.
The blade 38, has a base 50, with a rounded longitudinal boss 52,
on the bottom thereof with a contour adapted to be received in the
groove or seat 48, whether it be a complete transverse opening or a
slot as mentioned hereinabove. The blade 38, has a cross section
like the blade shown in FIG. 1, with a leading edge 54. A high
strength cable 56, is embedded in the blade 38 and attached to an
anchor plate 57, along a line coinciding with the shaft 40. The
cable 56, extends downwardly into the cylindrical recess 44, and
has a piston 58 attached to the free end thereof. The piston 58 has
a cross section to permit sliding movement within recess 44. A
compression spring 60, is placed in the recess 44, extending
between the piston 58 and the narrow opening 46 to drive the piston
58, downward and place the cable 56 in tension to maintain the
blade 38 in an erect position by seating boss 50 in seat 48. Thus,
the blade 38 is held rigid along a transverse direction but can
rock in a fore and aft direction if the blade should impact on an
obstruction. The blade can withstand the hydrodynamic loads, as
shown in FIG. 1, at B, since these forces are not aligned with the
longitudinal axis of the blade to pivot it about the boss 52 and
seat 48.
In operation, as the leading edge 54 of the blade 38, cuts through
the water, if the blade should impact on an obstruction the impact
will occur at the leading edge 54. The force of the impact will
pivot the blade 38 about the axis created by the seat 48 and the
boss 52. The pivoting of the blade 38, will pull the cable 56
upward and compress the spring 60, between the piston 58 and the
opening 46, thereby absorbing the shock of impact. After the impact
load is removed from the blade 38, the spring 60, will drive the
piston 58 back to its original position thereby pulling the cable
56, and re-erecting the blade 38, into its original position. The
generally semi-cylindrical shape of the seat 48, and boss 52,
assure that the blade 30, returns to the exact position relative to
the shaft 40, as before the collision. It also insures the proper
positioning of the blade with respect to the pitch changing
mechanism when the shaft 40 rotates.
As can be seen, a simple but unique means to protect the propulsion
system of a water vehicle has been developed wherein the blades
absorb the shock and damage of collision and the propulsion system
remains relatively undamaged.
Obviously many modifications and variations of the present
invention are possible in the light of the above teachings. It is
therefore to be understood that within the scope of the appended
claims the invention may be practiced otherwise than as
specifically described.
* * * * *